U.S. patent application number 16/261982 was filed with the patent office on 2020-07-30 for tooling assembly for decreasing powder usage in a powder bed additive manufacturing process.
The applicant listed for this patent is General Electric Company. Invention is credited to Jinjie Shi, Hongqing Sun, Andrew Ezekiel Wessman.
Application Number | 20200238386 16/261982 |
Document ID | 20200238386 / US20200238386 |
Family ID | 1000003867662 |
Filed Date | 2020-07-30 |
Patent Application | download [pdf] |
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United States Patent
Application |
20200238386 |
Kind Code |
A1 |
Sun; Hongqing ; et
al. |
July 30, 2020 |
Tooling Assembly for Decreasing Powder Usage in a Powder Bed
Additive Manufacturing Process
Abstract
A tooling assembly for mounting a plurality of components, such
as compressor blades, in a powder bed additive manufacturing
machine to facilitate a repair process is provided. The tooling
assembly includes component fixtures configured for receiving each
of the compressor blades, a mounting plate for receiving the
component fixtures, and a complementary fixture defining a
plurality of voids within which the compressor blades are received
when the complementary fixture is mounted to the mounting plate
such that less powder is required to fill the powder bed.
Inventors: |
Sun; Hongqing; (Rexford,
NY) ; Shi; Jinjie; (Mason, OH) ; Wessman;
Andrew Ezekiel; (Walton, KY) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
General Electric Company |
Schenectady |
NY |
US |
|
|
Family ID: |
1000003867662 |
Appl. No.: |
16/261982 |
Filed: |
January 30, 2019 |
Current U.S.
Class: |
1/1 |
Current CPC
Class: |
B22F 2003/1042 20130101;
B33Y 30/00 20141201; B23K 26/354 20151001; B22F 3/1055 20130101;
B33Y 50/02 20141201; B23K 26/34 20130101; B22F 7/062 20130101; B22F
2003/1057 20130101; B22F 2007/068 20130101; B33Y 10/00 20141201;
B22F 2003/1058 20130101; B22F 5/04 20130101 |
International
Class: |
B22F 7/06 20060101
B22F007/06; B22F 3/105 20060101 B22F003/105; B22F 5/04 20060101
B22F005/04; B33Y 10/00 20060101 B33Y010/00; B33Y 30/00 20060101
B33Y030/00; B33Y 50/02 20060101 B33Y050/02; B23K 26/34 20060101
B23K026/34; B23K 26/354 20060101 B23K026/354 |
Claims
1. A tooling assembly for supporting a component during a powder
bed additive manufacturing process, the tooling assembly
comprising: a mounting plate configured for receiving the component
such that a repair surface of the component is positioned within a
build plane; and a complementary fixture defining a void
corresponding to the component such that positioning the
complementary fixture over the mounting plate positions the
component within the void.
2. The tooling assembly of claim 1, wherein a clearance gap is
defined between the component and the complementary fixture when
the complementary fixture is positioned over the mounting
plate.
3. The tooling assembly of claim 2, wherein the clearance gap has a
width that is constant along a height of the complementary
fixture.
4. The tooling assembly of claim 3, wherein the clearance gap is
approximately 1 millimeter all the way around the component.
5. The tooling assembly of claim 1, wherein the clearance gap has a
width that increases gradually from a bottom of the complementary
fixture toward a top of the complementary fixture.
6. The tooling assembly of claim 1, wherein the void corresponds
substantially to the shape of a blade of a gas turbine engine.
7. The tooling assembly of claim 1, wherein a top surface of the
complementary fixture is positioned at or below the build plane
when the complementary fixture is positioned over the mounting
plate.
8. The tooling assembly of claim 1, wherein the complementary
fixture is formed from a metal, ceramic, or plastic material.
9. The tooling assembly of claim 1, wherein a layer of additive
material is deposited over the complementary fixture and the repair
surface of the component.
10. The tooling assembly of claim 9, wherein the layer of additive
material is a different material than the component.
11. The tooling assembly of claim 1, wherein the complementary
fixture is formed by: obtaining a component CAD model of the
component mounted to the mounting plate; and determining a fixture
model by removing the component CAD model from a CAD model of a
solid three-dimensional volume corresponding to a powder bed.
12. The tooling assembly of claim 11, wherein the complementary
fixture is formed by additively manufacturing the fixture
model.
13. The tooling assembly of claim 1, wherein the mounting plate is
configured for receiving a plurality of components and the
complementary fixture defines a plurality of voids, each of the
plurality of voids corresponding to one of the plurality of
components such that positioning the complementary fixture over the
mounting plate positions the plurality of components within the
plurality of voids.
14. A method of repairing a component using an additive
manufacturing machine, the method comprising: mounting the
component on a mounting plate such that a repair surface of the
component is positioned within a build plane; and positioning a
complementary fixture over the mounting plate, the complementary
fixture defining a void for receiving the component, and wherein a
clearance gap is defined between the component and the
complementary fixture.
15. The method of claim 14, further comprising: positioning the
mounting plate, the component, and the complementary fixture on a
build platform of the additive manufacturing machine; depositing a
layer of additive powder over the repair surface of the component
using a powder dispensing assembly; and selectively irradiating the
layer of additive powder to fuse the layer of additive powder onto
the repair surface of the component.
16. The method of claim 14, wherein the clearance gap has a width
that is constant along a height of the complementary fixture.
17. The method of claim 14, wherein the clearance gap has a width
that increases gradually from a bottom of the complementary fixture
toward a top of the complementary fixture.
18. The method of claim 14, wherein a top surface of the
complementary fixture is positioned at or below the build plane
when positioned over the mounting plate.
19. The method of claim 14, further comprising forming the
complementary fixture by: obtaining a component CAD model of the
component mounted to the mounting plate; and determining a fixture
model by removing the component CAD model from a CAD model of a
solid three-dimensional volume corresponding to a powder bed.
20. The method of claim 14, comprising: mounting a plurality of
components on the mounting plate such that a repair surface of each
of the plurality of components is positioned within the build
plane; and positioning the complementary fixture over the mounting
plate, the complementary fixture defining a plurality of voids,
each of the plurality of voids corresponding to one of the
plurality of components such that positioning the complementary
fixture over the mounting plate positions the plurality of
components within the plurality of voids.
Description
FIELD
[0001] The present subject matter relates generally to additive
manufacturing machines, and more particularly to tooling assemblies
for decreasing powder usage in a powder bed additive manufacturing
process.
BACKGROUND
[0002] Machine or device components frequently experience damage,
wear, and/or degradation throughout their service life. For
example, serviced compressor blades of a gas turbine engine show
erosion, defects, and/or cracks after long term use. Specifically,
for example, such blades are subject to significant stresses which
inevitably cause blades to wear over time, particularly near the
tip of the blade. For example, blade tips are susceptible to wear
or damage from friction or rubbing between the blade tips and
shrouds, from chemical degradation or oxidation from hot gasses,
from fatigue caused by cyclic loading and unloading, from diffusion
creep of crystalline lattices, etc.
[0003] Notably, worn or damaged blades may result in machine
failure or performance degradation if not corrected. Specifically,
such blades may cause a turbomachine to exhibit reduced operating
efficiency as gaps between blade tips and turbine shrouds may allow
gasses to leak through the turbine stages without being converted
to mechanical energy. When efficiency drops below specified levels,
the turbomachine is typically removed from service for overhaul and
refurbishment. Moreover, weakened blades may result in complete
fractures and catastrophic failure of the engine.
[0004] As a result, compressor blades for a gas turbine engine are
typically the target of frequent inspections, repairs, or
replacements. It is frequently very expensive to replace such
blades altogether, however, some can be repaired for extended
lifetime at relatively low cost (as compared to replacement with
entirely new blades). Nevertheless, existing repair processes tend
to be labor intensive and time consuming.
[0005] For example, a traditional compressor blade tip repair
process uses a welding/cladding technique where repair materials
are supplied, in either powder or wire form, to the blade tips. The
repair materials are melted by focused power source (e.g., laser,
e-beam, plasma arc, etc.) and bonded to blade tips. However, blades
repaired with such welding/cladding technique need tedious
post-processing to achieve the target geometry and surface finish.
Specifically, due to the bulky feature size of the welding/cladding
repair joint, the repaired blades require heavy machining to remove
the extra materials on the tip, and further require a secondary
polishing process to achieve a target surface finish. Notably, such
a process is performed on a single blade at a time, is very labor
intensive and tedious, and results in very large overall labor
costs for a single repair.
[0006] Alternatively, other direct-energy-deposition (DED) methods
may be used for blade repair, e.g., such as cold spray, which
directs high-speed metal powders to bombard the target or base
component such that the powders deform and deposit on the base
component. However, none of these DED methods are suitable for
batch processing or for repairing a large number of components in a
time efficient manner, thus providing little or no business
value.
[0007] Accordingly, novel systems and methods have been developed
and are presented herein for repairing or rebuilding worn
compressor blades (or any other components) using a powder bed
additive manufacturing process. Specifically, such a repair process
generally includes removing the worn portion of each of a plurality
of compressor blades, positioning the plurality of compressor
blades on a build platform of an additive manufacturing machine,
determining the precise location of each blade tip, and printing
repair segments directly onto the blade tips, layer by layer, until
the compressor blades reach their original dimensions or another
suitable target size and shape.
[0008] One of the key challenges with such a novel additive
manufacturing DMLM repair procedures described herein relates to
loading, unloading, and handling additive powder which is used to
fill the powder bed. In this regard, to perform a repair process on
the tip of a blade, the powder bed must first be loaded with
additive powder to the height of the blade tips. Such a process
generally includes manually loading the additive powder, which is
time-consuming and can also be costly especially for components
with large dimensions in the build orientation, e.g., the height of
the blades. Moreover, any unpacked additive powder might collapse
during printing, resulting in failure of recoating. In addition,
filling the entire volume of the powder bed which is not filled by
components to be repaired can require a large volume of powder,
which must be added prior to printing, removed after printing, and
filtered or screened prior to reuse during a subsequent additive
manufacturing process.
[0009] Accordingly, a system and method for repairing components
using an additive manufacturing machine would be useful. More
particularly, an additive manufacturing machine including a tooling
assembly for facilitating an additive repair process while
decreasing additive powder usage would be particularly
beneficial.
BRIEF DESCRIPTION
[0010] Aspects and advantages of the invention will be set forth in
part in the following description, or may be obvious from the
description, or may be learned through practice of the
invention.
[0011] In one exemplary embodiment of the present disclosure, a
tooling assembly for supporting a component during a powder bed
additive manufacturing process is provided. The tooling assembly
includes a mounting plate configured for receiving the component
such that a repair surface of the component is positioned within a
build plane and a complementary fixture defining a void
corresponding to the component such that positioning the
complementary fixture over the mounting plate positions the
component within the void.
[0012] In another exemplary aspect of the present disclosure, a
method of repairing a component using an additive manufacturing
machine is provided. The method includes mounting the component on
a mounting plate such that a repair surface of the component is
positioned within a build plane and positioning a complementary
fixture over the mounting plate, the complementary fixture defining
a void for receiving the component, and wherein a clearance gap is
defined between the component and the complementary fixture.
[0013] These and other features, aspects, and advantages of the
present invention will become better understood with reference to
the following description and appended claims. The accompanying
drawings, which are incorporated in and constitute a part of this
specification, illustrate embodiments of the invention and,
together with the description, serve to explain the principles of
the invention.
BRIEF DESCRIPTION OF THE DRAWINGS
[0014] A full and enabling disclosure of the present invention,
including the best mode thereof, directed to one of ordinary skill
in the art, is set forth in the specification, which makes
reference to the appended figures.
[0015] FIG. 1 shows a schematic representation of an additive
repair system that may be used for repairing or rebuilding
components according to an exemplary embodiment of the present
subject matter.
[0016] FIG. 2 depicts certain components of a controller according
to example embodiments of the present subject matter.
[0017] FIG. 3 shows a schematic view of an additive manufacturing
machine that may be used as part of the exemplary additive
manufacturing system of FIG. 1 according to an exemplary embodiment
of the present subject matter.
[0018] FIG. 4 shows a close-up schematic view of a build platform
of the exemplary additive manufacturing machine of FIG. 3 according
to an exemplary embodiment of the present subject matter.
[0019] FIG. 5 is a schematic cross sectional view of a tooling
assembly for supporting a component during a powder bed additive
manufacturing process according to an exemplary embodiment of the
present subject matter.
[0020] FIG. 6 is a top perspective view of the exemplary tooling
assembly of FIG. 5 according to an exemplary embodiment of the
present subject matter.
[0021] FIG. 7 is a bottom perspective view of the exemplary tooling
assembly of FIG. 5 according to an exemplary embodiment of the
present subject matter.
[0022] FIG. 8 is a perspective cross sectional view of the
exemplary tooling assembly of FIG. 5 positioned over a plurality of
components according to an exemplary embodiment of the present
subject matter.
[0023] FIG. 9 is a method of mounting a plurality of components in
a powder bed additive manufacturing machine according to an
exemplary embodiment of the present subject matter.
[0024] Repeat use of reference characters in the present
specification and drawings is intended to represent the same or
analogous features or elements of the present invention.
DETAILED DESCRIPTION
[0025] Reference now will be made in detail to embodiments of the
invention, one or more examples of which are illustrated in the
accompanying drawings. Each example is provided by way of
explanation of the invention, not limitation of the invention. In
fact, it will be apparent to those skilled in the art that various
configurations, modifications, and variations can be made in the
present invention without departing from the scope or spirit of the
invention. For instance, features illustrated or described as part
of one embodiment can be used with another embodiment to yield a
still further embodiment. Thus, it is intended that the present
invention covers such modifications and variations as come within
the scope of the appended claims and their equivalents.
[0026] As used herein, the terms "first," "second," and "third" may
be used interchangeably to distinguish one component from another
and are not intended to signify location or importance of the
individual components. In addition, the terms "upstream" and
"downstream" refer to the relative direction with respect to the
motion of an object or a flow of fluid. For example, "upstream"
refers to the direction from which the object has moved or fluid
has flowed, and "downstream" refers to the direction to which the
object is moving or the fluid is flowing. Furthermore, as used
herein, terms of approximation, such as "approximately,"
"substantially," or "about," refer to being within a ten percent
margin of error.
[0027] Aspects of the present subject matter are directed to a
system and method for repairing one or more components using an
additive manufacturing process. The method includes securing the
components in a tooling assembly such that a repair surface of each
component is positioned within a single build plane, determining a
repair toolpath corresponding to the repair surface of each
component using a vision system, depositing a layer of additive
powder over the repair surface of each component using a powder
dispensing assembly, and selectively irradiating the layer of
additive powder along the repair toolpath to fuse the layer of
additive powder onto the repair surface of each component.
[0028] Specifically, aspects of the present subject matter provide
a tooling assembly for mounting a plurality of components, such as
compressor blades, in a powder bed additive manufacturing machine
to facilitate such a repair process. The tooling assembly includes
component fixtures configured for receiving each of the compressor
blades, a mounting plate for receiving the component fixtures, and
a complementary fixture defining a plurality of voids within which
the compressor blades are received when the complementary fixture
is mounted to the mounting plate such that less powder is required
to fill the powder bed.
[0029] As described in detail below, exemplary embodiments of the
present subject matter involve the use of additive manufacturing
machines or methods. As used herein, the terms "additively
manufactured" or "additive manufacturing techniques or processes"
refer generally to manufacturing processes wherein successive
layers of material(s) are provided on each other to "build-up,"
layer-by-layer, a three-dimensional component. The successive
layers generally fuse together to form a monolithic component which
may have a variety of integral sub-components.
[0030] Although additive manufacturing technology is described
herein as enabling fabrication of complex objects by building
objects point-by-point, layer-by-layer, typically in a vertical
direction, other methods of fabrication are possible and within the
scope of the present subject matter. For example, although the
discussion herein refers to the addition of material to form
successive layers, one skilled in the art will appreciate that the
methods and structures disclosed herein may be practiced with any
additive manufacturing technique or manufacturing technology. For
example, embodiments of the present invention may use
layer-additive processes, layer-subtractive processes, or hybrid
processes.
[0031] Suitable additive manufacturing techniques in accordance
with the present disclosure include, for example, Fused Deposition
Modeling (FDM), Selective Laser Sintering (SLS), 3D printing such
as by inkjets and laserjets, Sterolithography (SLA), Direct
Selective Laser Sintering (DSLS), Electron Beam Sintering (EBS),
Electron Beam Melting (EBM), Laser Engineered Net Shaping (LENS),
Laser Net Shape Manufacturing (LNSM), Direct Metal Deposition
(DMD), Digital Light Processing (DLP), Direct Selective Laser
Melting (DSLM), Selective Laser Melting (SLM), Direct Metal Laser
Melting (DMLM), and other known processes.
[0032] In addition to using a direct metal laser sintering (DMLS)
or direct metal laser melting (DMLM) process where an energy source
is used to selectively sinter or melt portions of a layer of
powder, it should be appreciated that according to alternative
embodiments, the additive manufacturing process may be a "binder
jetting" process. In this regard, binder jetting involves
successively depositing layers of additive powder in a similar
manner as described above. However, instead of using an energy
source to generate an energy beam to selectively melt or fuse the
additive powders, binder jetting involves selectively depositing a
liquid binding agent onto each layer of powder. The liquid binding
agent may be, for example, a photo-curable polymer or another
liquid bonding agent. Other suitable additive manufacturing methods
and variants are intended to be within the scope of the present
subject matter.
[0033] The additive manufacturing processes described herein may be
used for forming components using any suitable material. For
example, the material may be plastic, metal, concrete, ceramic,
polymer, epoxy, photopolymer resin, or any other suitable material
that may be in solid, liquid, powder, sheet material, wire, or any
other suitable form. More specifically, according to exemplary
embodiments of the present subject matter, the additively
manufactured components described herein may be formed in part, in
whole, or in some combination of materials including but not
limited to pure metals, nickel alloys, chrome alloys, titanium,
titanium alloys, magnesium, magnesium alloys, aluminum, aluminum
alloys, iron, iron alloys, stainless steel, and nickel or cobalt
based superalloys (e.g., those available under the name
Inconel.RTM. available from Special Metals Corporation). These
materials are examples of materials suitable for use in the
additive manufacturing processes described herein, and may be
generally referred to as "additive materials."
[0034] In addition, one skilled in the art will appreciate that a
variety of materials and methods for bonding those materials may be
used and are contemplated as within the scope of the present
disclosure. As used herein, references to "fusing" may refer to any
suitable process for creating a bonded layer of any of the above
materials. For example, if an object is made from polymer, fusing
may refer to creating a thermoset bond between polymer materials.
If the object is epoxy, the bond may be formed by a crosslinking
process. If the material is ceramic, the bond may be formed by a
sintering process. If the material is powdered metal, the bond may
be formed by a melting or sintering process. One skilled in the art
will appreciate that other methods of fusing materials to make a
component by additive manufacturing are possible, and the presently
disclosed subject matter may be practiced with those methods.
[0035] In addition, the additive manufacturing process disclosed
herein allows a single component to be formed from multiple
materials. Thus, the components described herein may be formed from
any suitable mixtures of the above materials. For example, a
component may include multiple layers, segments, or parts that are
formed using different materials, processes, and/or on different
additive manufacturing machines. In this manner, components may be
constructed which have different materials and material properties
for meeting the demands of any particular application. In addition,
although the components described herein are constructed entirely
by additive manufacturing processes, it should be appreciated that
in alternate embodiments, all or a portion of these components may
be formed via casting, machining, and/or any other suitable
manufacturing process. Indeed, any suitable combination of
materials and manufacturing methods may be used to form these
components.
[0036] An exemplary additive manufacturing process will now be
described. Additive manufacturing processes fabricate components
using three-dimensional (3D) information, for example a
three-dimensional computer model, of the component. Accordingly, a
three-dimensional design model of the component may be defined
prior to manufacturing. In this regard, a model or prototype of the
component may be scanned to determine the three-dimensional
information of the component. As another example, a model of the
component may be constructed using a suitable computer aided design
(CAD) program to define the three-dimensional design model of the
component.
[0037] The design model may include 3D numeric coordinates of the
entire configuration of the component including both external and
internal surfaces of the component. For example, the design model
may define the body, the surface, and/or internal passageways such
as openings, support structures, etc. In one exemplary embodiment,
the three-dimensional design model is converted into a plurality of
slices or segments, e.g., along a central (e.g., vertical) axis of
the component or any other suitable axis. Each slice may define a
thin cross section of the component for a predetermined height of
the slice. The plurality of successive cross-sectional slices
together form the 3D component. The component is then "built-up"
slice-by-slice, or layer-by-layer, until finished.
[0038] In this manner, the components described herein may be
fabricated using the additive process, or more specifically each
layer is successively formed, e.g., by fusing or polymerizing a
plastic using laser energy or heat or by sintering or melting metal
powder. For example, a particular type of additive manufacturing
process may use an energy beam, for example, an electron beam or
electromagnetic radiation such as a laser beam, to sinter or melt a
powder material. Any suitable laser and laser parameters may be
used, including considerations with respect to power, laser beam
spot size, and scanning velocity. The build material may be formed
by any suitable powder or material selected for enhanced strength,
durability, and useful life, particularly at high temperatures.
[0039] Each successive layer may be, for example, between about 10
.mu.m and 200 .mu.m, although the thickness may be selected based
on any number of parameters and may be any suitable size according
to alternative embodiments. Therefore, utilizing the additive
formation methods described above, the components described herein
may have cross sections as thin as one thickness of an associated
powder layer, e.g., 10 .mu.m, utilized during the additive
formation process.
[0040] In addition, utilizing an additive process, the surface
finish and features of the components may vary as need depending on
the application. For example, the surface finish may be adjusted
(e.g., made smoother or rougher) by selecting appropriate laser
scan parameters (e.g., laser power, scan speed, laser focal spot
size, etc.) during the additive process, especially in the
periphery of a cross-sectional layer which corresponds to the part
surface. For example, a rougher finish may be achieved by
increasing laser scan speed or decreasing the size of the melt pool
formed, and a smoother finish may be achieved by decreasing laser
scan speed or increasing the size of the melt pool formed. The
scanning pattern and/or laser power can also be changed to change
the surface finish in a selected area.
[0041] After fabrication of the component is complete, various
post-processing procedures may be applied to the component. For
example, post processing procedures may include removal of excess
powder by, for example, blowing or vacuuming. Other post processing
procedures may include a stress relief process. Additionally,
thermal, mechanical, and/or chemical post processing procedures can
be used to finish the part to achieve a desired strength, surface
finish, and other component properties or features.
[0042] Notably, in exemplary embodiments, several aspects and
features of the present subject matter were previously not possible
due to manufacturing restraints. However, the present inventors
have advantageously utilized current advances in additive
manufacturing techniques to improve various components and the
method of additively manufacturing such components. While the
present disclosure is not limited to the use of additive
manufacturing to form these components generally, additive
manufacturing does provide a variety of manufacturing advantages,
including ease of manufacturing, reduced cost, greater accuracy,
etc.
[0043] Also, the additive manufacturing methods described above
enable much more complex and intricate shapes and contours of the
components described herein to be formed with a very high level of
precision. For example, such components may include thin additively
manufactured layers, cross sectional features, and component
contours. In addition, the additive manufacturing process enables
the manufacture of a single component having different materials
such that different portions of the component may exhibit different
performance characteristics. The successive, additive nature of the
manufacturing process enables the construction of these novel
features. As a result, components formed using the methods
described herein may exhibit improved performance and
reliability.
[0044] Referring now to FIG. 1, an exemplary additive repair system
50 will be described according to an exemplary embodiment of the
present subject matter. As illustrated, additive repair system 50
generally includes a tooling fixture or assembly 52, a material
removal assembly 54, a vision system 56, a user interface panel 58,
and an additive manufacturing machine or system 100. Furthermore, a
system controller 60 may be operably coupled with some or all parts
of additive repair system 50 for facilitating system operation. For
example, system controller 60 may be operably coupled to user
interface panel 58 to permit operator communication with additive
repair system 50, e.g., to input commands, upload printing
toolpaths or CAD models, initiating operating cycles, etc.
Controller 60 may further be in communication with vision system 56
for receiving imaging data and with AM machine 100 for performing a
printing process.
[0045] According to exemplary embodiments, tooling assembly 52 is
generally configured for supporting a plurality of components in a
desired position and orientation. According to exemplary
embodiments, tooling assembly 52 supports 20 high pressure
compressor blades 70 during an additive manufacturing repair
process. Specifically, the additive manufacturing process may be a
powder bed fusion process (e.g., a DMLM or DMLS process as
described above). Although the repaired components are illustrated
herein as compressor blades 70 of a gas turbine engine, it should
be appreciated that any other suitable component may be repaired,
such as turbine blades, other airfoils, or components from other
machines. In order to achieve proper recoating and to facilitate
the printing process, it may be desirable to position all blades 70
in the same orientation and at the same height such that a repair
surface 72 of each blade is in a single build plane. Tooling
assembly 52 is a fixture intended to secure blades 70 in such
desired position and orientation.
[0046] Material removal assembly 54 may include a machine or device
configured for grinding, machining, brushing, etching, polishing,
wire electrical discharge machining (EDM), cutting, or otherwise
substantively modifying a component, e.g., by subtractive
modification or material removal. For example, material removal
assembly 54 may include a belt grinder, a disc grinder, or any
other grinding or abrasive mechanism. According to an exemplary
embodiment, material removal assembly 54 may be configured for
removing material from a tip of each blade 70 to obtain a desirable
repair surface 72. For example, as explained briefly above,
material removal assembly 54 may remove at least a portion of
blades 70 that has been worn or damaged, e.g., which may include
microcracks, pits, abrasions, defects, foreign material,
depositions, imperfections, and the like. According to an exemplary
embodiment, each blade 70 is prepared using material removal
assembly 54 to achieve the desired repair surface 72, after which
the blades 70 are all mounted in tooling assembly 52 and leveled
appropriately. However, according to alternative embodiments,
material removal assembly 54 may grind each blade 70 as it is fixed
in position in tooling assembly 52.
[0047] After the blades are prepared, vision system 56 may be used
to obtain an image or digital representation of the precise
position and coordinates of each blade 70 positioned in tooling
assembly 52. In this regard, according to exemplary embodiments,
vision system 56 may include any suitable camera or cameras 80,
scanners, imaging devices, or other machine vision device that may
be operably configured to obtain image data that includes a digital
representation of one or more fields of view. Such a digital
representation may sometimes be referred to as a digital image or
an image; however, it will be appreciated that the present
disclosure may be practiced without rendering such a digital
representation in human-visible form. Nevertheless, in some
embodiments, a human-visible image corresponding to a field of view
may be displayed on the user interface 58 based at least in part on
such a digital representation of one or more fields of view.
[0048] Vision system 56 allows the additive repair system 50 to
obtain information pertaining to one or more blades 70 onto which
one or more repair segments 74 (see FIG. 4) may be respectively
additively printed. In particular, the vision system 56 allows the
one or more blades 70 to be located and defined so that the
additive manufacturing machine 100 may be instructed to print one
or more repair segments 74 on a corresponding one or more blades 70
with suitably high accuracy and precision. According to an
exemplary embodiment, the one or more blades 70 may be secured to
tooling assembly 52, a mounting plate, a build platform, or any
other fixture with repair surface 72 of the respective blades 70
aligned to a single build plane 82.
[0049] The one or more cameras 80 of the vision system 56 may be
configured to obtain two-dimensional or three-dimensional image
data, including a two-dimensional digital representation of a field
of view and/or a three-dimensional digital representation of a
field of view. Alignment of the repair surface 72 of the blades 70
with the build plane 82 allows the one or more cameras 80 to obtain
higher quality images. For example, the one or more cameras 80 may
have a focal length adjusted or adjustable to the build plane 82.
With the repair surface 72 of one or more blades 70 aligned to the
build plane 82, the one or more cameras may readily obtain digital
images of the repair surface 72. The one or more cameras 80 may
include a field of view that encompasses all or a portion of the
one or more blades 70 secured to the tooling assembly 52. For
example, a single field of view may be wide enough to encompass a
plurality of components, such as each of the plurality of blades 70
secured to tooling assembly 52. Alternatively, a field of view may
more narrowly focus on an individual blade 70 such that digital
representations of respective blades 70 are obtained separately. It
will be appreciated that separately obtained digital images may be
stitched together to obtain a digital representation of a plurality
of components or blades 70. In some embodiments, the camera 80 may
include a collimated lens configured to provide a flat focal plane,
such that blades 70 or portions thereof located towards the
periphery of the field of view are not distorted. Additionally, or
in the alternative, the vision system 56 may utilize a distortion
correction algorithm to address any such distortion.
[0050] Image data obtained by the vision system 56, including a
digital representation of one or more blades 70 may be transmitted
to a control system, such as controller 60. Controller 60 may be
configured to determine a repair surface 72 of each of a plurality
of blades 70 from one or more digital representations of one or
more fields of view having been captured by the vision system 56,
and then determine one or more coordinates of the repair surface 72
of respective ones of the plurality of blades 70. Based on the one
or more digital representations, controller 60 may generate one or
more print commands (e.g., corresponding to one or more repair
toolpaths, e.g., the path of a laser focal point), which may be
transmitted to an additive manufacturing machine 100 such that the
additive manufacturing machine 100 may additively print a plurality
of repair segments 74 on respective ones of the plurality of blades
70. The one or more print commands may be configured to additively
print a plurality of repair segments 74 with each respective one of
the plurality of repair segments 74 being located on the repair
surface 72 of a corresponding blade 70.
[0051] Each of the components and subsystems of additive repair
system 50 are described herein in the context of an additive blade
repair process. However, it should be appreciated that aspects of
the present subject matter may be used to repair or rebuild any
suitable components. The present subject matter is not intended to
be limited to the specific repair process described. In addition,
FIG. 1 illustrates each of the systems as being distinct or
separate from each other and implies the process steps should be
performed in a particular order, however, it should be appreciated
that these subsystems may be integrated into a single machine,
process steps may be swapped, and other changes to the build
process may be implemented while remaining within the scope of the
present subject matter.
[0052] For example, vision system 56 and additive manufacturing
machine 100 may be provided as a single, integrated unit or as
separate stand-alone units. In addition, controller 60 may include
one or more control systems. For example, a single controller 60
may be operably configured to control operations of the vision
system 56 and the additive manufacturing machine 100, or separate
controllers 60 may be operably configured to respectively control
the vision system 56 and the additive manufacturing machine
100.
[0053] Operation of additive repair system 50, vision system 56,
and AM machine 100 may be controlled by electromechanical switches
or by a processing device or controller 60 (see, e.g., FIGS. 1 and
2). According to exemplary embodiments, controller 60 may be
operatively coupled to user interface panel 58 for user
manipulation, e.g., to control the operation of various components
of AM machine 100 or system 50. In this regard, controller 60 may
operably couple all systems and subsystems within additive repair
system 50 to permit communication and data transfer therebetween.
In this manner, controller 60 may be generally configured for
operating additive repair system 50 or performing one or more of
the methods described herein.
[0054] FIG. 2 depicts certain components of controller 60 according
to example embodiments of the present disclosure. Controller 60 can
include one or more computing device(s) 60A which may be used to
implement methods as described herein. Computing device(s) 60A can
include one or more processor(s) 60B and one or more memory
device(s) 60C. The one or more processor(s) 60B can include any
suitable processing device, such as a microprocessor,
microcontroller, integrated circuit, an application specific
integrated circuit (ASIC), a digital signal processor (DSP), a
field-programmable gate array (FPGA), logic device, one or more
central processing units (CPUs), graphics processing units (GPUs)
(e.g., dedicated to efficiently rendering images), processing units
performing other specialized calculations, etc. The memory
device(s) 60C can include one or more non-transitory
computer-readable storage medium(s), such as RAM, ROM, EEPROM,
EPROM, flash memory devices, magnetic disks, etc., and/or
combinations thereof.
[0055] The memory device(s) 60C can include one or more
computer-readable media and can store information accessible by the
one or more processor(s) 60B, including instructions 60D that can
be executed by the one or more processor(s) 60B. For instance, the
memory device(s) 60C can store instructions 60D for running one or
more software applications, displaying a user interface, receiving
user input, processing user input, etc. In some implementations,
the instructions 60D can be executed by the one or more
processor(s) 60B to cause the one or more processor(s) 60B to
perform operations, e.g., such as one or more portions of methods
described herein. The instructions 60D can be software written in
any suitable programming language or can be implemented in
hardware. Additionally, and/or alternatively, the instructions 60D
can be executed in logically and/or virtually separate threads on
processor(s) 60B.
[0056] The one or more memory device(s) 60C can also store data 60E
that can be retrieved, manipulated, created, or stored by the one
or more processor(s) 60B. The data 60E can include, for instance,
data to facilitate performance of methods described herein. The
data 60E can be stored in one or more database(s). The one or more
database(s) can be connected to controller 60 by a high bandwidth
LAN or WAN, or can also be connected to controller through one or
more network(s) (not shown). The one or more database(s) can be
split up so that they are located in multiple locales. In some
implementations, the data 60E can be received from another
device.
[0057] The computing device(s) 60A can also include a communication
module or interface 60F used to communicate with one or more other
component(s) of controller 60 or additive manufacturing machine 100
over the network(s). The communication interface 60F can include
any suitable components for interfacing with one or more
network(s), including for example, transmitters, receivers, ports,
controllers, antennas, or other suitable components.
[0058] Referring now to FIG. 3, an exemplary laser powder bed
fusion system, such as a DMLS or DMLM system 100, will be described
according to an exemplary embodiment. Specifically, AM system 100
is described herein as being used to build or repair blades 70. It
should be appreciated that blades 70 are only an exemplary
component to be built or repaired and are used primarily to
facilitate description of the operation of AM machine 100. The
present subject matter is not intended to be limited in this
regard, but instead AM machine 100 may be used for printing repair
segments on any suitable plurality of components.
[0059] As illustrated, AM system 100 generally defines a vertical
direction V or Z-direction, a lateral direction L or X-direction,
and a transverse direction T or Y-direction (see FIG. 1), each of
which is mutually perpendicular, such that an orthogonal coordinate
system is generally defined. As illustrated, system 100 includes a
fixed enclosure or build area 102 which provides a contaminant-free
and controlled environment for performing an additive manufacturing
process. In this regard, for example, enclosure 102 serves to
isolate and protect the other components of the system 100. In
addition, enclosure 102 may be provided with a flow of an
appropriate shielding gas, such as nitrogen, argon, or another
suitable gas or gas mixture. In this regard, enclosure 102 may
define a gas inlet port 104 and a gas outlet port 106 for receiving
a flow of gas to create a static pressurized volume or a dynamic
flow of gas.
[0060] Enclosure 102 may generally contain some or all components
of AM system 100. According to an exemplary embodiment, AM system
100 generally includes a table 110, a powder supply 112, a scraper
or recoater mechanism 114, an overflow container or reservoir 116,
and a build platform 118 positioned within enclosure 102. In
addition, an energy source 120 generates an energy beam 122 and a
beam steering apparatus 124 directs energy beam 122 to facilitate
the AM process as described in more detail below. Each of these
components will be described in more detail below.
[0061] According to the illustrated embodiment, table 110 is a
rigid structure defining a planar build surface 130. In addition,
planar build surface 130 defines a build opening 132 through which
build chamber 134 may be accessed. More specifically, according to
the illustrated embodiment, build chamber 134 is defined at least
in part by vertical walls 136 and build platform 118. In addition,
build surface 130 defines a supply opening 140 through which
additive powder 142 may be supplied from powder supply 112 and a
reservoir opening 144 through which excess additive powder 142 may
pass into overflow reservoir 116. Collected additive powders may
optionally be treated to sieve out loose, agglomerated particles
before re-use.
[0062] Powder supply 112 generally includes an additive powder
supply container 150 which generally contains a volume of additive
powder 142 sufficient for some or all of the additive manufacturing
process for a specific part or parts. In addition, powder supply
112 includes a supply platform 152, which is a plate-like structure
that is movable along the vertical direction within powder supply
container 150. More specifically, a supply actuator 154 vertically
supports supply platform 152 and selectively moves it up and down
during the additive manufacturing process.
[0063] AM system 100 further includes recoater mechanism 114, which
is a rigid, laterally-elongated structure that lies proximate build
surface 130. For example, recoater mechanism 114 may be a hard
scraper, a soft squeegee, or a roller. Recoater mechanism 114 is
operably coupled to a recoater actuator 160 which is operable to
selectively move recoater mechanism 114 along build surface 130. In
addition, a platform actuator 164 is operably coupled to build
platform 118 and is generally operable for moving build platform
118 along the vertical direction during the build process. Although
actuators 154, 160, and 164 are illustrated as being hydraulic
actuators, it should be appreciated that any other type and
configuration of actuators may be used according to alternative
embodiments, such as pneumatic actuators, hydraulic actuators, ball
screw linear electric actuators, or any other suitable vertical
support means. Other configurations are possible and within the
scope of the present subject matter.
[0064] As used herein, "energy source" may be used to refer to any
device or system of devices configured for directing an energy beam
of suitable power and other operating characteristics towards a
layer of additive powder to sinter, melt, or otherwise fuse a
portion of that layer of additive powder during the build process.
For example, energy source 120 may be a laser or any other suitable
irradiation emission directing device or irradiation device. In
this regard, an irradiation or laser source may originate photons
or laser beam irradiation which is directed by the irradiation
emission directing device or beam steering apparatus.
[0065] According to an exemplary embodiment, beam steering
apparatus 124 includes one or more mirrors, prisms, lenses, and/or
electromagnets operably coupled with suitable actuators and
arranged to direct and focus energy beam 122. In this regard, for
example, beam steering apparatus 124 may be a galvanometer scanner
that moves or scans the focal point of the laser beam 122 emitted
by energy source 120 across the build surface 130 during the laser
melting and sintering processes. In this regard, energy beam 122
can be focused to a desired spot size and steered to a desired
position in plane coincident with build surface 130. The
galvanometer scanner in powder bed fusion technologies is typically
of a fixed position but the movable mirrors/lenses contained
therein allow various properties of the laser beam to be controlled
and adjusted. According to exemplary embodiments, beam steering
apparatus may further include one or more of the following: optical
lenses, deflectors, mirrors, beam splitters, telecentric lenses,
etc.
[0066] It should be appreciated that other types of energy sources
120 may be used which may use an alternative beam steering
apparatus 124. For example, an electron beam gun or other electron
source may be used to originate a beam of electrons (e.g., an
"e-beam"). The e-beam may be directed by any suitable irradiation
emission directing device preferably in a vacuum. When the
irradiation source is an electron source, the irradiation emission
directing device may be, for example, an electronic control unit
which may include, for example, deflector coils, focusing coils, or
similar elements. According to still other embodiments, energy
source 120 may include one or more of a laser, an electron beam, a
plasma arc, an electric arc, etc.
[0067] Prior to an additive manufacturing process, recoater
actuator 160 may be lowered to provide a supply of powder 142 of a
desired composition (for example, metallic, ceramic, and/or organic
powder) into supply container 150. In addition, platform actuator
164 may move build platform 118 to an initial high position, e.g.,
such that it substantially flush or coplanar with build surface
130. Build platform 118 is then lowered below build surface 130 by
a selected layer increment. The layer increment affects the speed
of the additive manufacturing process and the resolution of a
components or parts (e.g., blades 70) being manufactured. As an
example, the layer increment may be about 10 to 100 micrometers
(0.0004 to 0.004 in.).
[0068] Additive powder is then deposited over the build platform
118 before being fused by energy source 120. Specifically, supply
actuator 154 may raise supply platform 152 to push powder through
supply opening 140, exposing it above build surface 130. Recoater
mechanism 114 may then be moved across build surface 130 by
recoater actuator 160 to spread the raised additive powder 142
horizontally over build platform 118 (e.g., at the selected layer
increment or thickness). Any excess additive powder 142 drops
through the reservoir opening 144 into the overflow reservoir 116
as recoater mechanism 114 passes from left to right (as shown in
FIG. 3). Subsequently, recoater mechanism 114 may be moved back to
a starting position.
[0069] Therefore, as explained herein and illustrated in FIG. 3,
recoater mechanism 114, recoater actuator 160, supply platform 152,
and supply actuator 154 may generally operate to successively
deposit layers of additive powder 142 or other additive material to
facilitate the print process. As such, these components may
collectively be referred to herein as powder dispensing apparatus,
system, or assembly. The leveled additive powder 142 may be
referred to as a "build layer" 172 (see FIG. 4) and the exposed
upper surface thereof may be referred to as build surface 130. When
build platform 118 is lowered into build chamber 134 during a build
process, build chamber 134 and build platform 118 collectively
surround and support a mass of additive powder 142 along with any
components (e.g., blades 70) being built. This mass of powder is
generally referred to as a "powder bed," and this specific category
of additive manufacturing process may be referred to as a "powder
bed process."
[0070] During the additive manufacturing process, the directed
energy source 120 is used to melt a two-dimensional cross-section
or layer of the component (e.g., blades 70) being built. More
specifically, energy beam 122 is emitted from energy source 120 and
beam steering apparatus 124 is used to steer the focal point 174 of
energy beam 122 over the exposed powder surface in an appropriate
pattern (referred to herein as a "toolpath"). A small portion of
exposed layer of the additive powder 142 surrounding focal point
174, referred to herein as a "weld pool" or "melt pool" or "heat
effected zone" 176 (best seen in FIG. 4) is heated by energy beam
122 to a temperature allowing it to sinter or melt, flow, and
consolidate. As an example, melt pool 176 may be on the order of
100 micrometers (0.004 in.) wide. This step may be referred to as
fusing additive powder 142.
[0071] Build platform 118 is moved vertically downward by the layer
increment, and another layer of additive powder 142 is applied in a
similar thickness. The directed energy source 120 again emits
energy beam 122 and beam steering apparatus 124 is used to steer
the focal point 174 of energy beam 122 over the exposed powder
surface in an appropriate pattern. The exposed layer of additive
powder 142 is heated by energy beam 122 to a temperature allowing
it to sinter or melt, flow, and consolidate both within the top
layer and with the lower, previously-solidified layer. This cycle
of moving build platform 118, applying additive powder 142, and
then directed energy beam 122 to melt additive powder 142 is
repeated until the entire component (e.g., blades 70) is
complete.
[0072] Referring now generally to FIGS. 5 through 8, a tooling
assembly 200 that may be used with AM system 100 will be described
according to an exemplary embodiment of the present subject matter.
For example, tooling assembly 200 may replace tooling assembly 52
as described in relation to FIG. 1. Due to the similarity between
tooling assembly 200, tooling assembly 52, and the AM system 100 in
which they are configured for operating, like reference numerals
will be used in FIGS. 5 through 8 to refer to like features
described with respect to FIGS. 1 through 4.
[0073] Referring now specifically to FIG. 5, tooling assembly 200
will be described according to an exemplary embodiment of the
present subject matter. As explained above, tooling assembly 200 is
generally configured for receiving one or more components, e.g.,
shown here as blades 70, and securely mounting such components for
a subsequent additive manufacturing process. Specifically, tooling
assembly 200 may secure each of the plurality of blades 70 in a
desired position and orientation relative to AM machine 100.
[0074] Tooling assembly 200 generally includes a component fixture
202 configured for receiving one or more blades 70. According to
the illustrated embodiment, each component fixture 202 is
configured for receiving a single blade 70. In this regard, blade
70 may define a dovetail 204 which is configured for receipt in a
complementary slot 206 defined in component fixture 202. In this
regard, once blade 70 is installed into complementary slot 206 of
component fixture 202, blades 70 may not move or rotate relative to
component fixture 202. Component fixture 202 may generally be a
rectangular block with a flat bottom surface 208 which may sit
flush against another flat surface.
[0075] Tooling assembly 200 may further include a mounting plate
210 that is configured for receiving the plurality of component
fixtures 202. In this regard, mounting plate 210 may be a rigid
plate having a flat receiving surface 212 upon which component
fixtures 202 may be seated. Notably, as described briefly above, it
is desirable to fix the position and orientation of blades 70 prior
to an additive manufacturing process. In this regard, as used
herein, the "position" of a blade 70 may refer to the coordinates
of a centroid of blade 70 in the X-Y plane. In addition, the
"orientation" of a blade 70 may refer to an angular position of
blade 70 about the Z-direction. In this regard, according to an
exemplary embodiment, the orientation of each blade 70 may be
defined according to the angular position of its chord line (not
shown). In this regard, for example, two blades 70 are said to have
the same "orientation" when their chord lines are parallel to each
other.
[0076] According to the exemplary embodiment described herein,
mounting plate 210 is configured for receiving a plurality of
component fixtures 202 before being positioned at a known location
on build platform 118. However, it should be appreciated that
according to alternative embodiments build platform 118 may be used
directly as a mounting plate 210. In this regard, for example,
mounting plate 210 may be removed altogether and component fixtures
202 may be positioned, oriented, and secured where desired directly
on build platform 118.
[0077] Thus, as explained above, tooling assembly 200 is generally
configured for supporting a plurality of blades 70 within a powder
bed of additive manufacturing machine 100. In addition, according
to an exemplary embodiment, each blade 70 is mounted into a
component fixture 202 and positioned on mounting plate 210 or
directly on build platform 118 such that the repair surface 72 of
each blade 70 is positioned within a build plane 82. In this
manner, a layer of additive powder (e.g., build layer 172) may be
deposited over each repair surface 72 at a desired thickness for
forming a first layer of repair segments 74 (FIG. 4) on the tip of
each blade 70.
[0078] Notably, however, due to the height of each blade 70
relative to a height of repair segments 74, conventional additive
manufacturing processes require a substantial amount of additive
powder 142. Specifically, a substantial volume of additive powder
142 must typically be provided into build chamber 134 to form a
powder bed that supports the top layer of additive powder or build
layer 172. As explained above, the powder loading process is
typically a manual process that takes a significant amount of time
and can result in recoating or print errors when pockets or voids
collapse within the additive powder 142. In addition, additive
manufacturing machine 100, or build platform 118 more specifically,
is typically configured for only supporting a specific volume or
weight of additive powder 142 during the build process, thus
introducing process limitations when powder bed is filled with
additive powder 142. Finally, even to the extent some unfused
additive powder 142 may be reused during subsequent additive
manufacturing processes, such used additive powder 142 must be
carefully screened, filtered, or otherwise reconditioned prior to
reuse.
[0079] As a result, according to exemplary embodiments, tooling
assembly 200 may further include a complementary fixture 220 that
defines one or more voids 222 which correspond to the components
being repaired, e.g., blades 70. Complementary fixture 220 is
mountable to mounting plate 210 or over build platform 118 such
that each of the components being repaired is positioned within one
of the voids 222. Specifically, according to the illustrated
embodiment, complementary fixture 220 defines twenty (20) voids 222
which correspond in shape, position, and orientation with blades 70
as mounted to mounting plate 210 or build platform 118. In this
regard, for example, voids 222 may have a curved cross sectional
profile corresponding to an airfoil of each blade 70, the cross
sectional profile of voids 222 may vary along the height 234 of
complementary fixture to correspond to the varying cross sectional
profile of the corresponding airfoil, etc. It should be appreciated
that according to alternative embodiments, complementary fixture
220 may define voids 222 corresponding to any other suitable
component or components to facilitate an additive repair
process.
[0080] Notably, in order to facilitate mounting of complementary
fixture 220 prior to a build and the removal of complementary
fixture 220 after a build, it may be desirable to allow some
clearance between complementary fixture 220 and blades 70 when
complementary fixture 220 is mounted to mounting plate 210.
Specifically, tooling assembly 200 may define a clearance gap 230
between the components and complementary fixture 220 when
complementary fixture 220 is positioned over mounting plate 210 or
build platform 118. In this regard, voids 222 may be slightly
oversized such that blades 70 slide into voids 222 during a
mounting process without contacting complementary fixture 220.
[0081] In addition, clearance gap 230 may generally permit blades
70 to be surrounded by additive powders 142 during a print process
such that the presence of complementary fixture 220 has little or
no effect on the additive print process, the recoating process,
etc. In this regard, additive powder may be loaded into clearance
gap 230 to facilitate the print process without requiring a
substantial amount of additive powder or powder loading time.
[0082] According to the illustrated embodiment, clearance gap 230
defines a width 232 which is substantially constant along a height
234 of complementary fixture 220. In this regard, the space between
complementary fixture 220 and both blades 70 and the corresponding
component fixtures 202 in which they are mounted may have a
constant thickness such that the additive powder surrounding blades
70 is substantially equivalent along all sides of blades 70. For
example, according to an exemplary embodiment, clearance gap 230
may be approximately 1 mm all the way around the component. In this
manner, the powder loading process may be minimized while the print
process and the recoating process remain unchanged relative to a
conventional powder bed print process.
[0083] According to still other embodiments, clearance gap 230 may
define a width 232 that increases gradually from a bottom 236 of
complementary fixture 220 toward a top 238 complementary fixture
220. In this regard, for example, the width 232 of clearance gap
230 may start substantially small (e.g., less than 1 mm, 0.1 mm or
smaller) or even be in contact with component fixture 202 proximate
bottom 236 of complementary fixture 220. However, the width 232 may
increase or taper gradually away from blades 70 proximate top 238
of complementary fixture 220. In this manner, the loading of
additive powders may be further simplified, e.g., due to a larger
opening at top 238 of complementary fixture 220 and the likelihood
of voids or clogging of additive powder 142 is minimized due to the
slanted surface or funnel shape of clearance gap 230. For example,
according to an exemplary embodiment, the width 232 of clearance
gap 230 proximate top 238 of complementary fixture 220 may two
times, three times, or even ten times greater than width 232
proximate bottom 236 of complementary fixture 220.
[0084] Moreover, in order to facilitate the recoating process, top
238 of complementary fixture 220 is positioned at or below the
build plane 82 when positioned over mounting plate 210 or build
platform 118. Specifically, for example, blades 70 may extend above
top 238 of complementary fixture 220 by approximately half a
millimeter, 1 mm, or greater in order to prevent contact with a
recoater mechanism 114 or to otherwise facilitate a proper
recoating of additive powder or the print process.
[0085] Component fixture 202, mounting plate 210, and complementary
fixture 220 may generally be formed from any suitable material and
may have any suitable shape. According to the illustrated
embodiment, these components are formed from metal such that they
may be reused for multiple repair and rebuild processes.
Specifically, once blades 70 have been repaired using a powder bed
additive manufacturing process as described below, each blade 70
may be removed from the corresponding component fixture 202 and
each of component fixture 202, mounting plate 210, and
complementary fixture 220 may be used to mount different blades 70
in a subsequent repair process.
[0086] According to exemplary embodiment of the present subject
matter, complementary fixture 220 may be designed and formed in any
suitable manner for receiving blades 70. For example, according to
the illustrated embodiment, complementary fixture 220 is formed by
obtaining a component CAD model of all components mounted to
mounting plate 210. In this regard, a CAD model may be generated
which includes mounting plate 210 and each of blades 70 mounted to
mounting plate 210 in the desired position and orientation. A
fixture model, e.g., which may be used to form complementary
fixture 220, is determined by removing the component CAD model from
a CAD model of a solid three-dimensional volume corresponding to
the size of build chamber 134 or the powder bed. In this manner,
complementary fixture 220 generally defines a mirror image or a
negative image of mounting plate 210 and/or blades 70 within build
chamber 134. In other words, complementary fixture 220 corresponds
substantially to the empty space or void volume within powder bed
after blades 70 are fixed therein prior to an additive repair
procedure.
[0087] According to exemplary embodiments, complementary fixture
220 may be formed using any suitable method and from any suitable
material. For example, complementary fixture 220 may be formed from
a metal, ceramic, or plastic material suitable for reuse in
multiple repair procedures. In addition, complementary fixture 220
may be formed by casting, machining, or by additive manufacturing,
e.g., using AM machine 100. According still other embodiments,
complementary fixture 220 may be formed from plastic, e.g. via
injection molding, or may be formed in any other suitable manner or
from any other suitable material.
[0088] After complementary fixture 220 is formed and positioned
over build platform 118 or mounting plate 210 as desired, additive
powder 142 may be loaded into powder bed and a recoating assembly,
e.g., such as recoater mechanism 114, may spread a layer of
additive material (e.g., build layer 172) over top 238 of
complementary fixture 220 and the repair surfaces 72 of each
component being repaired, e.g., blades 70.
[0089] Notably, use of the additive manufacturing methods described
above along with tooling assembly 200 facilitates the use of
multiple different additive materials, e.g., different compositions
of additive powders 142 during a single print process. In this
regard, for example, the additive powder 142 used may be a
different composition than blades 70 and complementary fixture 220.
Moreover, each layer of additive material may differ from
previously deposited and fused additive layers. In this regard,
tooling assembly 200 may provide for precisely controlled
transition locations between the two materials, e.g., between
blades 70 and build layer 172. Using the methods described herein,
the additive manufacturing process may be performed in multiple
steps, in one or more additive manufacturing machines 100 to
achieve repair segments 74 that may include a plurality of layers
formed from multiple different types of additive powders having
different compositions, physical properties, etc.
[0090] Notably, complementary fixture 220 is generally configured
for filling volume of build chamber 134 or powder bed which is
otherwise not occupied by blades 70, component fixtures 202, or
other mounting structures for supporting these components. In this
manner, the process for supplying or loading additive powder 142
into powder bed is simplified. For example, an operator need only
fill the gaps between the components to be repaired, e.g., blades
70, and complementary fixture 220. In this manner, the time
required to prepare the additive manufacturing machine 100 for the
print process is reduced, as is the amount of additive powder 142
that must be used and the required time for post processing of
blades 70 and additive powder 142.
[0091] Now that the construction and configuration of additive
repair system 50 has been described according to exemplary
embodiments of the present subject matter, an exemplary method 300
for mounting a plurality of components for a repair or rebuild
process using an additive repair system will be described according
to an exemplary embodiment of the present subject matter. Method
300 can be used to repair blades 70 using additive repair system
50, AM machine 100, and tooling assembly 200, or to repair any
other suitable component using any other suitable additive
manufacturing machine or system. In this regard, for example,
controller 60 may be configured for implementing some or all steps
of method 300. Further, it should be appreciated that the exemplary
method 300 is discussed herein only to describe exemplary aspects
of the present subject matter, and is not intended to be
limiting.
[0092] Referring now to FIG. 9, method 300 includes, at step 310,
mounting a component on a mounting plate such that a repair surface
of the component is positioned within a build plane. In this
regard, a plurality of blades 70 which need to be repaired may be
positioned in corresponding component fixtures 202, e.g., by
sliding dovetails 204 of each blade 70 in a complementary slot 206
of each component fixture 202. Component fixtures 202 may then be
mounted to build platform 118 or mounting plate 210 in the desired
position and orientation.
[0093] Step 320 includes positioning a complementary fixture over
the mounting plate. As described above, complementary fixture 220
defines one or more voids 222 for receiving the component (or a
plurality of components) such that a clearance gap 230 is defined
between the component and complementary fixture 220. In addition,
clearance gap 230 may be designed such that the process of loading
additive powder 142 is simplified and a top 238 of complementary
fixture may be positioned below repair surface 72 of blades 70 such
that the recoating process simplified and the additive
manufacturing process proceeds without contacting complementary
fixture 220.
[0094] Step 330 includes positioning the mounting plate, the
component, and the complementary fixture on a build platform of an
additive manufacturing machine. According to alternative
embodiments, mounting plate 210 may be removed altogether,
component fixtures 202 and blades 70 may be mounted directly to
build platform 118, and complementary fixture 220 may be configured
for mounting directly to build platform 118 over blades 70. In this
manner, the plurality of blades 70 which need to be repaired are
positioned within build chamber 134 or the powder bed such that the
blades 70 and complementary fixture 220 substantially fill the
powder bed (e.g., greater than 95% of the total volume) to simplify
powder loading and the printing process.
[0095] According to an exemplary embodiment, method 300 may further
include additively printing repair segments 74 onto repair surfaces
72 of each blade 70 using AM machine 100. In this regard, step 340
includes depositing a layer of additive powder over the repair
surface of the component using a powder dispensing assembly and
step 350 includes selectively irradiating the layer of additive
powder to fuse the layer of additive powder onto the repair surface
of the component. In this manner, an energy source may fuse
additive powder onto each blade tip layer by layer until the
component is repaired to an original CAD model or to another
suitable geometry.
[0096] FIG. 9 depicts an exemplary control method having steps
performed in a particular order for purposes of illustration and
discussion. Those of ordinary skill in the art, using the
disclosures provided herein, will understand that the steps of any
of the methods discussed herein can be adapted, rearranged,
expanded, omitted, or modified in various ways without deviating
from the scope of the present disclosure. Moreover, although
aspects of the methods are explained using additive repair system
50, AM machine 100, and tooling assembly 200 as an example, it
should be appreciated that these methods may be applied to
repairing or rebuilding any other number, type, and configuration
of components using any suitable tooling fixture or additive
manufacturing machine or system.
[0097] This written description uses examples to disclose the
invention, including the best mode, and also to enable any person
skilled in the art to practice the invention, including making and
using any devices or systems and performing any incorporated
methods. The patentable scope of the invention is defined by the
claims, and may include other examples that occur to those skilled
in the art. Such other examples are intended to be within the scope
of the claims if they include structural elements that do not
differ from the literal language of the claims, or if they include
equivalent structural elements with insubstantial differences from
the literal languages of the claims.
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