U.S. patent application number 16/951031 was filed with the patent office on 2021-03-11 for additive-based electroforming manufacturing methods and metallic articles produced thereby.
This patent application is currently assigned to HONEYWELL INTERNATIONAL INC.. The applicant listed for this patent is HONEYWELL INTERNATIONAL INC.. Invention is credited to Gangmin Cao, Qiang Li.
Application Number | 20210071311 16/951031 |
Document ID | / |
Family ID | 1000005225994 |
Filed Date | 2021-03-11 |
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United States Patent
Application |
20210071311 |
Kind Code |
A1 |
Li; Qiang ; et al. |
March 11, 2021 |
ADDITIVE-BASED ELECTROFORMING MANUFACTURING METHODS AND METALLIC
ARTICLES PRODUCED THEREBY
Abstract
Additive-based electroforming manufacturing methods for
producing turbomachine components and other metallic articles are
provided, as are metallic articles manufactured utilizing such
manufacturing methods. In various embodiments, the method includes
providing a sacrificial tooling structure having a
component-defining surface region. A metallic body layer or shell
is deposited over the component-defining surface region utilizing
an electroforming process. The tooling structure is removed, while
the metallic body layer is left substantially intact. After tooling
structure removal, the metallic body layer is further processed to
complete fabrication of the metallic component.
Inventors: |
Li; Qiang; (Shanghai,
CN) ; Cao; Gangmin; (Shanghai, CN) |
|
Applicant: |
Name |
City |
State |
Country |
Type |
HONEYWELL INTERNATIONAL INC. |
Charlotte |
NC |
US |
|
|
Assignee: |
HONEYWELL INTERNATIONAL
INC.
Charlotte
NC
|
Family ID: |
1000005225994 |
Appl. No.: |
16/951031 |
Filed: |
November 18, 2020 |
Related U.S. Patent Documents
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Application
Number |
Filing Date |
Patent Number |
|
|
15653208 |
Jul 18, 2017 |
10900136 |
|
|
16951031 |
|
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Current U.S.
Class: |
1/1 |
Current CPC
Class: |
C25D 1/02 20130101; F01D
5/225 20130101; B33Y 10/00 20141201; F01D 9/02 20130101; B29C 64/40
20170801; C25D 1/20 20130101; F01D 5/288 20130101; B22F 2999/00
20130101; F01D 25/24 20130101; B22F 5/009 20130101; B23P 2700/13
20130101; B22F 2003/242 20130101; F05D 2220/32 20130101; B22F 10/00
20210101; C25D 1/00 20130101; B23P 15/02 20130101; B22F 2005/103
20130101; B22F 2998/10 20130101; B22F 2003/247 20130101; B29C
64/153 20170801; B33Y 80/00 20141201; C23F 1/00 20130101; F05D
2230/31 20130101; F23R 3/002 20130101 |
International
Class: |
C25D 1/02 20060101
C25D001/02; B29C 64/40 20060101 B29C064/40; C25D 1/20 20060101
C25D001/20; C25D 1/00 20060101 C25D001/00; B22F 3/105 20060101
B22F003/105; B29C 64/153 20060101 B29C064/153; B33Y 10/00 20060101
B33Y010/00; B33Y 80/00 20060101 B33Y080/00; B23P 15/02 20060101
B23P015/02 |
Claims
1. A method for manufacturing a metallic component, comprising:
providing a sacrificial tooling structure having a
component-defining surface region; forming an
electrically-conductive coating layer from an alloy predominately
composed of aluminum by weight percentage over the
component-defining surface region; depositing a metallic body layer
over the electrically-conductive coating layer utilizing an
electroforming process; removing the sacrificial tooling structure
to form an internal void within the metallic body layer, and the
electrically-conductive coating layer lines the internal void; and
further processing the metallic body layer to complete fabrication
of the metallic component, the further processing including heat
treating the electrically-conductive coating layer substantially
concurrently with the removing of the sacrificial tool structure to
form an aluminide coating on the metallic body layer.
2. The method of claim 1, wherein the method further comprises:
energizing the electrically-conductive coating layer during the
electroforming process to deposit the metallic body layer over the
electrically-conductive coating layer.
3. The method of claim 2, further comprising, during the
electroforming process, depositing the metallic body layer to have
a global average thickness exceeding that of the
electrically-conductive coating layer.
4. The method of claim 1, wherein the providing the sacrificial
tooling structure further comprises additively manufacturing the
sacrificial tooling structure.
5. The method of claim 1, wherein removing the sacrificial tooling
structure comprises removing the sacrificial tooling structure,
while leaving electrically-conductive coating layer substantially
intact.
6. The method of claim 1, further comprising applying a dielectric
masking material to the sacrificial tooling structure, the
dielectric masking material creating an opening in the metallic
body layer during the electroforming process, and the removing
comprises removing the sacrificial tooling structure through the
opening created in the metallic body layer.
7. The method of claim 1, wherein the removing comprises removing
the sacrificial tooling structure to form an internal void within
the metallic component, the metallic body layer forming a shell
substantially enclosing the internal void.
8. The method of claim 7, wherein the shell has a substantially
uniform wall thickness.
9. The method of claim 1, wherein the sacrificial tooling structure
further has a non-component-defining surface region; and wherein
the method further comprises producing the component-defining
surface region from an electrically-conductive material, while
producing the non-component-defining surface region from a
dielectric material by additive manufacturing.
10. The method of claim 1, wherein the metallic component comprises
an airfoil, and wherein the method further comprises shaping and
sizing the sacrificial tooling structure to create a void space
within the airfoil when the sacrificial tooling structure is
removed through an opening provided in the metallic body layer.
11. The method of claim 10, further comprising forming the opening
at a location radially inboard or radially outboard of the
airfoil.
12. The method of claim 1, wherein the metallic component comprises
a gas turbine engine component having a flow passage therethrough,
and wherein the method further comprises forming the flow passage,
at least in substantial part, by removal of the sacrificial tooling
structure.
13. A method for manufacturing a metallic article, comprising:
applying an electrically-conductive coating layer from an alloy
predominately composed of aluminum by weight percentage over a
portion of a sacrificial tooling structure; utilizing an
electroforming process to deposit a metallic shell encasing the
sacrificial tooling structure; removing the sacrificial tooling
structure to form an internal void within the metallic shell, and
the electrically-conductive coating layer lines the internal void;
and further processing the metallic shell to yield the metallic
article, the further processing including heat treating the
electrically-conductive coating layer substantially concurrently
with the removing of the sacrificial tool structure to form an
aluminide coating on the metallic body layer.
14. The method of claim 13, further comprising: applying a
dielectric masking material to the sacrificial tooling structure;
and in conjunction with the electroforming process, creating at
least one opening in the metallic shell with the dielectric masking
material through which the sacrificial tooling structure is
exposed.
15. The method of claim 14, wherein the removing the sacrificial
tooling structure further comprises removing the sacrificial
tooling structure through the at least one opening in the metallic
shell to form the internal void within the metallic shell.
16. The method of claim 13 wherein the metallic article comprises a
Gas Turbine Engine (GTE) component, and wherein the method further
comprises: selecting the sacrificial tooling structure to have an
airfoil-defining region; forming the metallic shell to extend over
the airfoil-defining region and define at least one airfoil
contained within the GTE component.
17. The method of claim 13 wherein the metallic article comprises a
GTE component, and wherein the method further comprises: selecting
the sacrificial tooling structure to have a flow passage-defining
region; and forming the metallic shell to extend over the flow
passage-defining region and impart the metallic shell with a flow
passage section through which gas flow is conducted when the GTE
component is utilized within a GTE.
Description
CROSS-REFERENCE TO RELATED APPLICATION
[0001] This application is a continuation of U.S. patent
application Ser. No. 15/653,208 filed on Jul. 18, 2017. The
relevant disclosure of the above application is incorporated herein
by reference.
TECHNICAL FIELD
[0002] The present invention relates generally to electroforming
and, more particularly, additive-based electroforming manufacturing
methods for producing metallic articles, as well as to turbomachine
components and other metallic articles manufactured by such
processes.
Abbreviations
[0003] AM--Additive Manufacturing or Additively Manufactured;
[0004] CAD--Computer Aided Design;
[0005] CMP--Chemical Mechanical Planarization or Polishing;
[0006] CVD--Chemical Vapor Deposition;
[0007] DMLS--Direct Metal Laser Sintering;
[0008] EBC--Environmental Barrier Coating;
[0009] FFF--Fused Filament Fabrication;
[0010] GTE--Gas Turbine Engine;
[0011] IGV--Inlet Guide Vane;
[0012] MCrAlY--a material containing chromium, aluminum, yttrium,
and "M" as its primary constituents by weight, wherein "M" is
nickel, cobalt, or a combination thereof;
[0013] SLA--Stereolithography;
[0014] TBC--Thermal Barrier Coating;
[0015] USD--United States Dollars;
[0016] vol %--volume percentage;
[0017] wt %--weight percentage;
[0018] YSZ--Yttria-Stabilized Zirconia; and
[0019] 3D--three dimensional.
BACKGROUND
[0020] Turbomachine components are often characterized by
relatively complex, thin-walled geometries. Extensive efforts have
been expended in optimizing the geometries of turbomachine
components, while satisfying critical mission requirements,
prolonging operational lifespans, and maintaining lightweight
designs for flight applications. Turbomachine components are
commonly fabricated from superalloy materials having enhanced
properties at elevated temperatures found within the
chemically-harsh turbomachine environment. Additionally,
specialized coatings or multilayer coating systems may be formed
over selected component surfaces for added thermal or environmental
barrier protection, particularly when such surface are exposed to
core gas flow during turbomachine operation. Examples of high
temperature coating and coating systems include EBCs, TBCs, and
aluminide coatings of the type commonly formed over the
aerodynamically-streamlined or contoured surfaces of rotor blades,
nozzle vanes, rotor shrouds, and other GTE components. The
stringent design parameters and demanding performance requirements
placed on GTE components and, more broadly, on turbomachine
components, taken in conjunction with low volume production, often
result in undesirably high manufacturing costs and lengthy
production cycles during component manufacture.
[0021] A continued industry demand thus exists for the development
of methods by which turbomachine components can be manufactured in
more efficient and cost effective manners, even when such
components are produced in relatively low quantities. Embodiments
of such manufacturing methods would ideally support the precision
production of GTE components and other turbomachine components
having relatively complex, thin-walled constructions. Additionally,
it would be desirable for such manufacturing methods to enable
turbomachine component fabrication from superalloy materials and to
facilitate the formation of high temperature coatings over selected
component surfaces, as desired. Finally, and more generally, it
would be desirable for such manufacturing methods to be amenable to
the production of various other types of metallic articles
including, but not limited to, other types of aerospace components.
Embodiments of such manufacturing methods are provided herein, as
are metallic components produced in accordance with such
manufacturing methods. Other desirable features and characteristics
of embodiments of the present invention will become apparent from
the subsequent Detailed Description and the appended Claims, taken
in conjunction with the accompanying drawings and the foregoing
Background.
BRIEF SUMMARY
[0022] Methods for manufacturing metallic components, such as
turbomachine components having relatively thin-walled
constructions, are provided. The disclosed manufacturing method
combine additive manufacturing techniques and electroforming
processes to fabricate metallic components at reduced manufacturing
costs and abbreviated production cycle times, particularly in the
context of low volume production. In various embodiments, the
component manufacturing method includes the step or process of
additively manufacturing a sacrificial tooling structure having a
component-defining surface region. A metallic body layer is
deposited over the component-defining surface region utilizing an
electroforming process, with the geometry or shape of the surface
region transferred to the metallic body layer. At a suitable
juncture following deposition of the metallic body layer, the
sacrificial tooling structure is chemically dissolved, thermally
decomposed, or otherwise removed, while the metallic body layer is
left substantially intact. The metallic body layer is then further
processed to complete fabrication of the metallic component, which
may predominately consist of the metallic body layer by vol % in
embodiments. In certain implementations, such as when the
sacrificial tooling structure is fabricated from a dielectric
material or a material having relatively poor electrical
conductivity, the component manufacturing method may further
include the step or process of depositing an
electrically-conductive base coat over the component-defining
surface region of the sacrificial tooling structure for usage in
plating the metallic body layer during the subsequently-performed
electroforming process.
[0023] In other embodiments, the component manufacturing method
includes the step or process of applying an electrically-conductive
coating layer over a portion of a sacrificial tooling structure.
The electrically-conductive coating layer is then energized during
a subsequently-performed electroforming process, which is utilized
to deposit or plate a metallic shell over the sacrificial tooling
structure and onto the coating layer. The metallic shell encases,
surrounds, or coats the sacrificial tooling structure, in whole or
in substantial part. After deposition of the metallic shell, the
sacrificial tooling structure is removed through at least one
opening in the metallic shell. The metallic shell is then further
processed to yield the completed metallic article. The
electrically-conductive coating layer may or may not be stripped
and, thus, may or may not be present in the completed metallic
article. In implementations in which the metallic article assumes
the form of a turbomachine or GTE component, the component
manufacturing method may further include: (i) selecting the
sacrificial tooling structure to have an airfoil-defining region;
and (ii) forming the metallic shell to extend over the
airfoil-defining region and thereby define at least one airfoil
contained in the completed GTE component. In other implementations
in which the metallic article assumes the form of a GTE component,
the method may further include: (i) selecting the sacrificial
tooling structure to have a flow passage-defining region; and (ii)
forming the metallic shell to extend over the flow passage-defining
region and thereby impart the metallic shell with a flow passage
through which gas flow is conducted when the GTE component is
utilized within a GTE.
[0024] Embodiments of metallic components or workpieces are further
provided, which are fabricated in accordance with the disclosed
manufacturing methods. In embodiments, the metallic component
includes a plated body layer; a central void, such as an unfilled
air cavity or flow passage, substantially surrounded and defined by
the plated body layer; and an opening formed in the plated body
layer through which the central void is exposed from the exterior
of the metallic component. The metallic component may be
predominately composed of the plated body layer by vol % in at
least some implementations. Furthermore, in certain instances, the
metallic component may further include an electrically-conductivity
coating layer, which lines interior surfaces of the plated body
layer defining the central voids. The metallic body layer is
usefully, but not necessarily formed to have a global average
thickness at least twice the global average thickness of the
electrically-conductive coating layer, when present. In further
implementations, the metallic component may also contain an airfoil
portion defined, in whole or in substantial part, by the plated
body layer. In such implementations, the central void may assume
the form of an internal cavity within the metallic component. The
internal cavity may be surrounded by the airfoil portion, as taken
about a longitudinal axis of the airfoil portion, while the opening
may be formed inboard or outboard of the airfoil portion, as
further taken along the longitudinal axis.
[0025] Various additional examples, aspects, and other useful
features of embodiments of the present disclosure will also become
apparent to one of ordinary skill in the relevant industry given
the additional description provided below.
BRIEF DESCRIPTION OF THE DRAWINGS
[0026] At least one example of the present invention will
hereinafter be described in conjunction with the following figures,
wherein like numerals denote like elements, and:
[0027] FIG. 1 is a flowchart setting-forth an exemplary
additive-based electroforming process for manufacturing a metallic
component, such as a turbomachine component having a relatively
thin-walled or hollow construction, as illustrated in accordance
with an exemplary embodiment of the present disclosure;
[0028] FIGS. 2-6 are simplified cross-sectional views illustrating
a generalized metallic component, as fabricated in accordance with
the exemplary component manufacturing method set-forth in FIG. 1
and shown at various stages of completion; and
[0029] FIG. 7 is a cross-sectional view of a GTE (partially shown),
which contains several components usefully fabricated utilizing the
component manufacturing method of FIG. 1, as illustrated in
accordance with an exemplary embodiment of the present
disclosure.
[0030] For simplicity and clarity of illustration, the drawing
figures illustrate the general manner of construction, and
descriptions and details of well-known features and techniques may
be omitted to avoid unnecessarily obscuring the exemplary and
non-limiting embodiments described in the subsequent Detailed
Description. It should further be understood that features or
elements appearing in the accompanying figures are not necessarily
drawn to scale unless otherwise stated. For example, the dimensions
of certain elements or regions in the figures may be exaggerated
relative to other elements or regions to improve understanding of
embodiments of the disclosure.
DETAILED DESCRIPTION
[0031] The following Detailed Description is merely exemplary in
nature and is not intended to limit the invention or the
application and uses of the invention. Furthermore, there is no
intention to be bound by any theory presented in the preceding
Background or the following Detailed Description. The term
"exemplary," as appearing throughout this document, is synonymous
with the term "example" and is utilized repeatedly below to
emphasize that the following description provides only multiple
non-limiting examples of the invention and should not be construed
to restrict the scope of the invention, as set-out in the Claims,
in any respect. Finally, as appearing herein, the terms "on" and
"over" generally describe a spatial relationship between a first
structural element (e.g., a deposited or plated layer) that
overlies, underlies, or is otherwise generally supported by a
second structural element (e.g., another deposited layer or a
component body). Such terms do not require intimate or direct
physical contact between the first and second structural elements
unless otherwise expressly stated.
Overview
[0032] The following describes additive-based electroforming
manufacturing methods for fabricating articles of manufacture,
structures, or workpieces predominately composed of metallic
materials. Such articles of manufacture, structures, or workpieces
are broadly referred to herein as "metallic components," with this
term encompassing all articles of manufacture predominately
composed of one or more metallic materials by wt %. The term
"metallic component" thus does not preclude the possibility that
the below-described components may include certain regions or
portions composed of non-metallic materials, such as ceramic or
organic materials utilized for cavity backfill or coating formation
purposes. In many instances, the below-described metallic
components will be characterized by a hollow or partially hollow
construction. In this case, the metallic component may include a
wall or shell, which extends in three dimensions around a flow
passage, an internal cavity, or other void that is centrally
located within the component, generally considered (herein, a
"central void"). The below-described manufacturing methods may be
particularly useful in the fabrication of aerospace and
turbomachine components, which have relatively thin-walled or
shell-like constructions and which are predominately composed of
superalloy materials. This notwithstanding, embodiments of the
manufacturing method are not restricted to usage within any
particular industry or to the production of any particular type of
metallic component.
[0033] The below-described manufacturing methods leverage unique
combinations AM processes and electroforming techniques to produce
metallic components. The AM processes are employed to initially
fabricate a consumable or sacrificial tooling structure, which has
at least one surface region generally defining the desired geometry
of the completed metallic component (herein, "component-defining
surface regions"). Comparatively, electroforming is utilized to
plate or deposit a metallic body layer or metallic shell over the
sacrificial tooling structure and, specifically, over the
component-defining surface region(s) of the tooling structures.
Post electroforming, the sacrificial tooling structure is
chemically dissolved, thermally decomposed, or otherwise removed,
while the metallic body layer is left substantially intact. Final
processing is then performed to complete fabrication of the
metallic component. Final processing can include, for example,
machining to define the more detailed structural features of the
completed metallic component, polishing or grinding to thin or
refine the surface finish of selected component regions, the
formation of high temperature coatings or multilayer coating
systems over selected component surfaces, the performance of heat
treatment processes, and so on. The end result is a metallic
component having relatively thin-walled, lightweight, and
structurally-robust construction, which can be produced with
abbreviated cycle times and at reduced production costs as compared
to conventional manufacturing methods, such as investment
casting.
[0034] In certain embodiments, such as when the sacrificial tooling
structure is composed of a dielectric material or another material
having relatively poor electrical conductivity, an
electrically-conductive coating layer may be applied to selected
surfaces of the sacrificial tooling structure prior to
electroforming. In this manner, the electrically-conductive coating
layer can serve as an electrode (e.g., cathode) layer during the
subsequently-performed electroforming process; e.g., the
electrically-conductive coating layer may be energized during
electroforming along with one or more anodes, while the sacrificial
tooling structure is at least partially submerged in plating
solution to gradually compile or plate the metallic body layer over
non-masked regions of the coating layer. After electroforming, the
electrically-conductive coating layer may then be stripped away by,
for example, contact with a suitable etchant. Alternatively, the
electrically-conductive coating layer may be left intact for the
duration of the manufacturing process and consequently remain in
the completed metallic component. In such embodiments, the
electrically-conductive coating layer can potentially contribute
additional functionality to the completed metallic component. For
example, the coating layer can be formulated and/or further
processed to form or help form a high temperature coating or
multilayer coating system over selected surfaces of the metallic
component. This may be particularly useful when the metallic
component assumes the form of a turbomachine component, such as a
GTE component bathed in core gas flow during engine operation, as
discussed more fully below in conjunction with FIG. 7. An exemplary
embodiment of the additive-based electroforming manufacturing
method will now be described in conjunction with FIGS. 1-6.
[0035] Examples of the Additive-Based Electroforming Manufacturing
Method
[0036] FIG. 1 is a flowchart providing an additive-based
electroforming manufacturing method 10 for fabricating metallic
components, as illustrated in accordance with an exemplary and
non-limiting embodiment of the present disclosure. As can be seen,
additive-based electroforming manufacturing method 10 includes a
number of sequentially-performed process steps identified as "STEPS
12, 14, 16, 18, 20, 22, 24." Depending upon the particular manner
in which additive-based electroforming manufacturing method 10 is
implemented, each step generically illustrated in FIG. 1 may entail
a single process or multiple sub-processes. Furthermore, the
process steps illustrated in FIG. 1 and described below are
provided by way of non-limiting example only. In alternative
embodiments of manufacturing method 10, additional process steps
may be performed, certain steps may be omitted, and/or the
illustrated steps may be performed in alternative sequences.
[0037] Additive-based electroforming manufacturing method 10
commences at STEP 12 (FIG. 1) with the additive production of a
consumable or sacrificial tooling structure. As appearing herein,
the term "additive manufacturing" and the corresponding
abbreviation "AM" refer to computer-controlled manufacturing
methods during which articles of manufacture are gradually built-up
or compiled on a layer-by-layer basis in accordance with
computer-readable design data, such as a computer-generated CAD
model. The term "AM processes" thus encompasses 3D printing
processes including, but not limited to, SLA, FFF, and targeted
sintering (e.g., DMLS) processes. An example of a consumable or
sacrificial tooling structure, which may be fabricated during STEP
12 of manufacturing method 10, is shown in FIG. 2 and identified by
reference numeral "26." In this relatively simple example,
sacrificial tooling structure 26 is shown in cross-section and is
generally axisymmetric about a centerline 28. In further
embodiments, sacrificial tooling structure 26 may assume various
other forms and may or may not be axisymmetric about centerline
28.
[0038] As shown in FIG. 2, sacrificial tooling structure 26 is
purposefully depicted in highly generalized manner to emphasize
that tooling structure 26 can assume a wide range of geometric
shapes and dimensions. Generally, the shape and dimensions of
tooling structure 26 (or at least those regions of structure 26
have surface geometries desirably imparted to the completed
metallic component) will be determined, at least in substantial
part, by the established design of the metallic components to be
fabricated utilizing manufacturing method 10 (FIG. 1). As indicated
above, and as discussed more fully below, at least a portion of
outer surface 30 of sacrificial tooling structure 26 has a surface
geometry, contour, or topology desirably transferred to the
completed metallic component fabricated via method 10. Such
portions of outer surface 30 are referred to herein as the
"component-defining surface regions" of sacrificial tooling
structure 26. In various embodiments, a majority and, perhaps, the
substantial entirety of outer surface 30 of sacrificial tooling
structure 26, as measured by surface area, may serve as one or more
component-defining surface regions of tooling structure 26. The
particular regions of outer surface 30 that serve as the
component-defining surface regions in the present example will
become apparent from the following description and the accompanying
drawing figures (particularly, FIGS. 2-6).
[0039] Sacrificial tooling structure 26 can be fabricated utilizing
various different AM techniques and, in certain instances, a
combination of AM techniques. Broadly stated, sacrificial tooling
structure 26 can be fabricated utilizing various different
processes capable of gradually compiling or building-up tooling
structure 26 on a layer-by-layer basis in accordance with CAD data
files or other computer-readable object data. A non-exhaustive list
of suitable processes includes FFF AM processes, SLA processes, and
targeted sintering (e.g., DMLS) processes. In many cases, the
chosen AM process involves heating a source material supplied as a
filament (wire), powder bed, or actively-flowed powder utilizing
one or more sources of targeted heat input, such a laser or an
electron beam. The heat source may be controlled to fuse targeted
regions of the source material in accordance with the
computer-readable object data (e.g., CAD) files to gradually
build-up or successively compile tooling structure 26 in accordance
with a pre-established design. If desired, and depending upon the
capabilities of the AM machine or apparatus employed to carry-out
the AM process, multiple sacrificial tooling structures may be
fabricated in parallel; e.g., a two dimensional grid or array of
tooling structures can be fabricated concurrently for increased
process efficiency.
[0040] Sacrificial tooling structure 26 can be produced from
various different materials. It is generally advantageous for the
selected material or materials to be commercially available at
relatively low cost, well-suited for usage with chosen AM process,
and to lend well to selective removal (e.g., chemical dissolution
or thermal decomposition) during the removal process conducted at
STEP 22 of manufacturing method 10 (FIG. 1). Candidate materials
include organic polymers, such as plastics and waxes, which are
amenable to removal by thermal decomposition. Other candidate
materials include metallic materials, which can be preferentially
removed with high selectivity by etching or chemical dissolution.
Such materials may include aluminum-based materials (that is,
materials consisting essentially of aluminum or containing aluminum
as a primary constituent by wt %) and zinc-based materials (that
is, materials consisting essentially of zinc or containing zinc as
a primary constituent by wt %). In certain implementations,
sacrificial tooling structure 26 may be fabricated utilizing
multiple materials, which include at least one dielectric material
and at least one co-deposited electrically-conductive material. For
example, a 3D printer capable of dual material printing may be
utilized to produce sacrificial tooling structure 26 in at least
some implementations. In this manner, sacrificial tooling structure
26 can be printed to contain electrically-conductive regions over
which plating occurs, as well as dielectric regions over which
plating does not occur (or at least occurs to a lesser extent)
during the below-described electroforming process.
[0041] Referring jointly to FIGS. 1 and 2, additive-based
electroforming manufacturing method 10 continues with the
preparation of sacrificial tooling structure 26 for electroforming
(STEP 14, FIG. 1). Preparation of sacrificial tooling structure 26
can involve the application of one or more electrically-conductive
coating layers onto tooling structure 26, the application of
masking layers over selected regions of tooling structure 26 and/or
the below-described electrically-conductive coating layers, surface
treatment steps for improved surface finish or smoothness, and/or
other process steps. Addressing first the application of masking
layers, a selected masking material may be applied to the selected
regions of outer surface 30 of sacrificial tooling structure 26 to
prevent or at least minimize the accumulation of plating material
(as forming the below-described metallic body layer) during
electroforming. In such cases, the masking material may composed of
a dielectric material, which can be applied utilizing any various
different deposition techniques. Further, in implementations in
which one or more electrically-conductive coating layers are formed
over sacrificial tooling structure 26, as described below in
conjunction with STEP 14 of manufacturing method 10, masking may be
applied to similarly prevent or at least deter deposition of the
coating layers over selected regions of tooling structure 26.
[0042] During STEP 14 of additive-based electroforming
manufacturing method 10 (FIG. 1), one or more
electrically-conductive coating layers may be deposited to
facilitate the subsequently-performed electroforming process. In
this case, an electrically-conductive coating layers may be
deposited over at least the component-defining surface regions of
sacrificial tooling structure 26 when tooling structure 26 is
composed of a dielectric material, a material having a relatively
low electrical conductivity, or a material that is otherwise poorly
suited for usage as an electrode (cathode) layer during
electroforming. Again, when it is desired to apply such a coating
layer, the electrically-conductive coating layer is applied over at
least the component-defining surface regions of sacrificial tooling
structure 26 (STEP 16). Suitable deposition techniques include, but
are not limited to, spray deposition techniques, painting, vapor
deposition techniques, and electroless plating of metallic
materials. Suitable materials include copper-based materials and
nickel-based materials; that is, materials containing or consisting
essentially of copper and nickel, respectively, as considered by wt
%. The average global thickness of the electrically-conductive
coating layer, when applied, can vary from about 0.2 microns
(.mu.m) to about 50 .mu.m and, perhaps, between about 0.5 and about
10 .mu.m in implementations; the term "about," as appearing
throughout this document, denoting a disparity of less than 10%. In
further implementations, the coating thickness may be greater than
or less than the aforementioned range.
[0043] In embodiments in which an electrically-conductive coating
layer is formed over sacrificial tooling structure 26 for usage as
an electrode layer during electroforming, the coating layer may or
may not be stripped during subsequent stages of manufacturing and,
therefore, may or may not be present in the completed metallic
component ultimately fabricated utilizing manufacturing method 10
(FIG. 1). When such an electrically-conductive coating layer is
desirably formed over sacrificial tooling structure 26 and is not
subsequently removed, there arises an opportunity to leverage the
coating layer to contribute additional structural or functional
characteristics to the completed metallic component. This may be
useful in the context of turbomachine components, such as GTE
components, having surfaces over which high temperature coatings or
multilayer coating systems are desirably produced. Thus, when
manufacturing method 10 is utilized to fabricate such GTE
components, the electrically-conductive coating layer may be
deposited to have a composition suitable for usage in the formation
of such high temperature coatings or multilayer coating systems. As
a first example, the electrically-conductive coating layer may be
composed of an aluminum-based material and utilized in the
formation of an aluminide coating over gas-exposed surfaces of the
GTE component. As a second example, the electrically-conductive
coating layer may be composed of a MCrAlY alloy and serve as a bond
coat for a subsequently-deposited EBC or TBC, such as a YSZ topcoat
layer. Further description in this regard is provided below in
conjunction with FIG. 7.
[0044] With reference to FIG. 3, sacrificial tooling structure 26
is illustrated after deposition of an electrically-conductive
coating layer 32 and a dielectric masking layer 34 over selected
surfaces of tooling structure 26, as applied in accordance with
STEP 14 of manufacturing method 10 (FIG. 1). Although tooling
structure 26, coating layer 32, and dielectric masking layer 34 are
only partially shown in FIG. 3, all such structure elements or
features may be assumed to be generally axisymmetric about
centerline 28 for the purposes of the instant example. As can be
seen, electrically-conductive coating layer 32 is deposited over
the majority and, indeed, the substantial entirety of outer surface
30 of tooling structure 26, as considered by surface area.
Additionally, coating layer 32 is deposited in intimate physical
contact with the component-defining surface regions of sacrificial
tooling structure 26. Comparatively, dielectric masking layer 34 is
deposited over a relatively limited region of sacrificial tooling
structure 26, which does not contribute in a direct manner to the
final geometry of the completed metallic component. Dielectric
masking layer 34 is composed of a dielectric material and defines a
plating keep-out or prevention region, which creates an opening in
the metallic body layer post electroforming to facilitate removal
of tooling structure 26, as described more fully below. In further
embodiments, dielectric masking layer 34 need not be applied and
such an opening may be created by material removal following
electroforming. An electrically-conductive coating layer may not be
applied in alternative implementations, such as when sacrificial
tooling structure 26 is at least partially composed of an
electrically-conductive material suitable for usage as an electrode
during electroforming.
[0045] Turning next to STEP 16 of additive-based electroforming
manufacturing method 10 (FIG. 1), an electroforming process is
carried-out to deposit or electroplate a metallic body layer over
sacrificial tooling structure 26. During electroforming,
sacrificial tooling structure 26, electrically-conductive coating
layer 32 (if present), and dielectric masking layer 34 (if present)
are partially or wholly submerged in a plating solution or bath. At
least one consumable or non-consumable anode may be positioned in
proximity of sacrificial tooling structure 26, coating layer 32,
and/or dielectric masking layer 34. An electrical potential is
applied to gradually deposit the plated metallic layer over the
appropriate surfaces of sacrificial tooling structure 26. Although
this need not be the case in all embodiments, the plated metallic
layer will often constitute the volumetric majority of the metallic
component in its completed form and is consequently referred to
herein as a "metallic body layer." The electroforming process may
be continued until the metallic body layer is built-up to a global
average thickness sufficient to enable the body layer to be
self-supporting or freestanding after removal tooling structure 26,
noting that some degree of physical support may also be provided
electrically-conductive coating layer 32 when present.
[0046] FIG. 4 illustrates sacrificial tooling structure 26 and
electrically-conductive coating layer 32 after deposition of a
metallic body layer 36 over selected regions of tooling structure
26. Here, metallic body layer 36 does not directly or intimately
contact sacrificial tooling structure 26, but rather is deposited
onto and intimately contacts electrically-conductive coating layer
32. Nonetheless, as the outer geometry of the component-defining
surface regions of tooling structure 26 is imparted to
electrically-conductive coating layer 32, so too is the geometry of
the component-defining surface regions of tooling structure 26
transferred to metallic body layer 36. In alternative embodiments
in which electrically-conductive coating layer 32 is absent,
metallic body layer 36 may be deposited directly onto and
intimately contact outer surface 30 of tooling structure 26.
Metallic body layer 36 is formed around sacrificial tooling
structure 26 in the illustrated example such that body layer 36
substantially encases, encloses sheathes tooling structure 26, as
well as electrically-conductive coating layer 32. In such
embodiments, metallic body layer 36 may be referred to as a
"metallic shell," which is formed over and around tooling structure
26.
[0047] The composition and thickness of metallic body layer/shell
36 will vary amongst embodiments. In embodiments in which
manufacturing method 10 is utilized to produce aerospace or
turbomachine (e.g., GTE) components, metallic body layer/shell 36
may be composed of a superalloy material, such as a nickel-based
and cobalt-based superalloy. As indicated above, metallic body
layer/shell 36 may be deposited to a thickness that is sufficiently
robust so as to be self-supporting following removal of sacrificial
tooling structure 26 and, perhaps, removal of
electrically-conductive coating layer 32. In one embodiment, and by
way of non-limiting only, metallic body layer/shell 36 may have a
global average thickness that is greater than and, perhaps, at
least twice that of coating layer 32. In certain implementations,
metallic body layer/shell 36 may be deposited to have a global
average thickness ranging between about 100 .mu.m and about 10
millimeters (mm). In other implementations, the global average
thickness of layer/shell 36 may be thicker or thinner than the
aforementioned range. Metallic body layer/shell 36 may be deposited
to have a substantially uniform or constant wall thickness or,
instead, a variable wall thickness. In the latter regard, targeted
regions of the metallic body layer/shell 36 may be imparted with a
varied wall thickness by application of masking, through shaping or
contouring of the anodes, and utilizing similar techniques
affecting the local rate of plating deposition during
electroforming. Additionally or alternatively, selected regions of
metallic body layer/shell 36 may be locally thinned after
electroforming by, for example, CMP, grinding, lapping, or the
like.
[0048] At a suitable juncture following electroforming, sacrificial
tooling structure 26 is removed in the manner indicated by STEPS
18, 20, 22 of manufacturing method 10 (FIG. 1). In instances in
which metallic body layer/shell 36 surrounds or encases sacrificial
tooling structure 26, one or more openings are desirably provided
in body layer/shell 36 to permit physical access to tooling
structure 26 facilitating tooling structure removal. Thus, as
indicated in FIG. 1 at STEPS 18, 20, if such an opening or openings
are not present in metallic body layer/shell 36 following
electroforming, such openings may be created by laser drilling,
targeted etching, or utilizing another material removal process.
Alternatively, such an opening or openings may be created during
the electroforming process in implementations in which build-up of
the plating material over selected regions of sacrificial tooling
structure 26 is prevented. Again, this may be accomplished by
forming sacrificial tooling structure 26 (or portions thereof) from
a dielectric material, by masking selected regions of tooling
structure 26 or electrically-conductive coating layer 32 (when
present), and/or by only partially submerging tooling structure 26
in the plating bath during electroforming. An example of such an
opening 38, which is created during electroforming due to the
presence of dielectric masking layer 34, is shown in FIG. 4.
[0049] At STEP 22 of additive-based electroforming manufacturing
method 10 (FIG. 1), sacrificial tooling structure 26 is removed
through opening 38 in metallic body layer/shell 36. Various
different techniques can be employed for removing sacrificial
tooling structure 26, as appropriate depending upon the composition
of sacrificial tooling structure 26, the composition of metallic
body layer/shell 36, the composition of electrically-conductive
coating layer 32 (if present), the thermal tolerances of body
layer/shell 36 and coating layer 32, and other such factors. If
composed of an organic flammable material, sacrificial tooling
structure 26 can be removed by controlled burning or thermal
decomposition. Such a thermal decomposition can be carried-out
within a furnace, oven, or the like and performed in an open air or
controlled environment in accordance with a pre-established heating
schedule. Alternatively, if composed of a chemically-dissolvable
material, sacrificial tooling structure 26 can be chemically
dissolved by treatment with a wet etchant, a dry etchant, or liquid
solvent. In such embodiments, the selected etchant or solvent is
usefully chosen to have a chemistry selective to the material of
tooling structure 26 over the material of metallic body layer/shell
36 (if contacted by the etchant) and/or electrically-conductive
coating layer 32 (if present). Agitation, heating, and/or active
flushing can be applied to accelerate such a chemical dissolution
process, as desired.
[0050] With continued reference to FIG. 1, electrically-conductive
coating layer 32 may be stripped during STEP 22 of additive-based
electroforming manufacturing method 10 (FIG. 1) in certain
implementations. When desirably removed, and depending upon the
respective composition of coating layer 32 and tooling structure
26, electrically-conductive coating layer 32 may be removed
concurrently with sacrificial tooling structure 26 utilizing a
single treatment step for enhanced process efficiency.
Alternatively, a series of separate removal steps may be performed.
As a still further possibility, electrically-conductive coating
layer 32 may not be removed during manufacturing method 10 and may,
instead, remain in the completed metallic component. This is
indicated in FIG. 5, which illustrates metallic body layer 36 after
removal of sacrificial tooling structure 26 during STEP 22 of
manufacturing method 10 (FIG. 1). As can be seen, central void 40
has been created within metallic body layer/shell 36 due to the
removal of tooling structure 26. As coating layer 32 is left
substantially intact, electrically-conductive coating layer 32
lines central void 40. Stated differently, electrically-conductive
coating layer 32 overlies those internal surfaces of body
layer/shell 36 defining central void 40. As will be described more
fully below, central void 40 may form an internal cavity, which is
substantially enclosed by metallic body layer/shell 36, within the
completed metallic component; or void 40 may ultimately form a flow
passage through the completed metallic component.
[0051] Turning lastly to STEP 24 of additive-based electroforming
manufacturing method 10 (FIG. 1), additional processing steps are
performed to complete fabrication of the metallic component. Such
additional process steps can include one or more machining steps,
as indicated by symbol 42 in FIG. 6 wherein the metallic component
is shown in a completed or nearly completed state and is
consequently now identified by reference numeral "44." When
performed, machining may define the more detailed features of
metallic component 44, to bring certain dimensions of component 44
into conformance with design tolerances, to thin selected regions
of component 44 for weight savings, and/or to otherwise refine the
final geometry of component 44. Similarly, grinding, CMP, lapping,
or the like may be conducted to improve surface finish across
regions of metallic component 44, if desired. Various other
processing techniques may also be performed during STEP 24 of
manufacturing method 10 including, but not limited to, heat
treatment, additional coating formation processes, and/or potential
backfilling or sealing of central void 40. In certain embodiments,
a separately-fabricated structure or body may be installed within
void 40 to, for example, deliver cooling airflow to the interior of
component 44 during usage thereof.
[0052] As previously stated, electrically-conductive coating layer
32 (if present) may be removed during STEP 24 in certain
implementations of manufacturing method 10. Conversely, in
embodiments in which coating layer 32 is present and remains in
completed metallic component 44, and particularly when metallic
component 44 assumes the form of a turbomachine or GTE component,
electrically-conductive coating layer 32 may be utilized in the
formation of a high temperature coating or coating system. As a
specific example, when an aluminide coating is desirably formed
over metallic body layer/shell 36, electrically-conductive coating
layer 32 may be formed from an aluminum-based material. Following
or substantially concurrently with tooling structure removal, heat
treatment may be carried-out to diffuse aluminum, and possibly
other constituents contained in coating layer 32 (e.g., platinum),
into the parent material (e.g., superalloy) of metallic body
layer/shell 36 and thereby form the desired aluminide coating. In
other implementations in which metallic component 44 assumes the
form of a GTE component, electrically-conductive coating layer 32
may be utilized as a bond coat. In such embodiments, coating layer
32 may be composed of a MCrAlY alloy or another material, and
additional processes may be carried-out during STEP 24 of
manufacturing method 10 to produce one or more coating layers
(e.g., an EBC or TBC) over coating layer 32. In this case, such
additional coating layers may be formed over cavity-facing surface
46 of coating layer 32 (FIG. 6) opposite metallic body layer/shell
36, with surface 46 possibly facing high temperature gas flow
during engine operation, as discussed more fully below in
conjunction with FIG. 7.
[0053] With continued reference to FIG. 6, metallic component 44
has a relatively thin-walled, hollow construction and is
predominately composed of metallic body layer/shell 36 by vol %.
Metallic body layer/shell 36 substantially encloses or surrounds
central void 40, which is transected by and may be generally
centered about centerline 28. Central void 40 will often be left as
an unfilled air cavity in the finished component, although the
possibility that void 40 may be backfilled or additional devices,
bodies, or structures may be installed within void 40 is not
precluded. Void 40 is lined by electrically-conductive coating
layer 32 in the illustrated example and is accessible from the
exterior of component 44 via opening 38, which is formed through
metallic body layer/shell 36 and coating layer 32. In certain
implementations, such as when metallic component 44 assumes the
form of turbomachine component, metallic body layer/shell 36 may be
composed of a superalloy material. In such embodiments, coating
layer 32 may contain aluminum as a primary constituent by wt %.
Central void 40 may exist as an enclosed cavity or hollow interior,
which is substantially surrounded and enclosed by metallic body
layer/shell 36. Alternatively, central void 40 may define a flow
passage or conduit, which extends through metallic component 44 and
is perhaps substantially coaxial with centerline 28. Additional
discussion of GTE components beneficially produced utilizing
manufacturing method 10 will now be provided in connection with
FIG. 7.
[0054] Examples of GTE Components Usefully Fabricated in
Embodiments of the Manufacturing Method
[0055] FIG. 7 is a cross-sectional schematic of a GTE 50, which is
partially shown and which is illustrated in accordance with an
exemplary embodiment of the present disclosure. The illustrated
portion of GTE 50 contains several examples of metallic (e.g.,
superalloy) components potentially fabricated utilizing
additive-based electroforming manufacturing method 10, as described
above in conjunction with FIG. 1. These metallic GTE components
include: (i) a combustor liner 52, as included in a combustor 54
(only the outlet end of which is shown); (ii) a nozzle vane 56, as
included in a turbine nozzle 58; (iii) an outer annular endwall 60
and inner annular endwall 62, as further included in turbine nozzle
58; (iv) a rotor blade 64, as included in a turbine rotor 66; and
(v) a turbine rotor shroud 68 surrounding or circumscribing turbine
rotor 66. As will be appreciated, many of the foregoing components
(e.g., combustor liner 52, endwalls 60, 62, and shroud 68) are
generally axisymmetric about engine rotational axis or centerline
70, while other components are repeated multiple times within GTE
50 and angularly spaced about centerline 70 (e.g., vane 56 and
blade 64). The foregoing components are listed by way of
non-limiting example only, with the understanding that embodiments
of manufacturing method 10 can be utilized to produce various other
types of GTE components in addition to those listed above, such as
compressor blades, heat shields, IGV structures, and duct
members.
[0056] To provide a more specific example, consider the fabrication
of nozzle vane 56 and/or rotor blade 64 utilizing manufacturing
method 10 (FIG. 1). To produce vane 56 and/or blade 64, a
sacrificial tooling structure is initially fabricated generally
defining the desired shape and dimensions of the component. In the
case of vane 56 and blade 64, both of these components include an
airfoil structure or shape, which may be defined by a relatively
thin-walled construction extending or wrapping about the perimeter
of a central cavity within the airfoil. Thus, the contoured walls
of nozzle vane 56 and/or rotor blade 64 may be produced by plating
of the metallic body layer during electroforming, with the
sacrificial tooling structure additively built to have an
appropriate outer geometry defining the airfoil structures. After
electroforming, the sacrificial tooling structure may be removed to
form an internal cavity or void within nozzle vane 56 and/or rotor
blade 64, as previously described in connection with FIG. 1 and as
generally outlined in FIG. 7 by phantom line. The resulting vane 56
and blade 64 may each contain an airfoil portion that is defined,
at least in substantial part, by a plated body layer corresponding
to metallic body layer/shell 36 in FIGS. 4-6. The internal cavity
within each of nozzle vane 56 and rotor blade 64 (again shown in
phantom in FIG. 7) may be surrounded by the airfoil portion, as
taken along a longitudinal axis of the airfoil portion, which is
orthogonal to centerline 70 in FIG. 7. Such cavities may be left as
unfilled air cavities to impart the finished component (here, vane
56 and/or blade 64) with a substantially hollow, lightweight
construction well-suited for flight applications. Furthermore, if
desired, impingement tubes or similar devices can be inserted into
the cavities to provide targeted impingement cooling along, for
example, the leading edge regions of vane 56 and/or rotor blade
64.
[0057] With continued reference to FIG. 7, openings providing
access to the internal cavities contained in nozzle vane 56 and
rotor blade 64 may be located inboard or outboard of the airfoil
portion of vane 56 and/or blade 64, as taken along the longitudinal
axis of the airfoil portion. In this manner, the openings through
which the sacrificial tooling structures are removed do not
penetrate or interrupt the contoured or aerodynamically-streamlined
airfoil surfaces of nozzle vane 56 and rotor blade 64. In one
embodiment, the opening providing access to the interior of the
airfoil portion of nozzle vane 56 may be located in outer annular
endwall 62 of turbine nozzle 58, as generally indicated in FIG. 7.
Comparatively, the opening providing access to the interior of the
airfoil portion of turbine rotor blade 64 may be provided through
the platform or base portion of the rotor blade piece included in
turbine rotor 66. Finally, when present and left intact through the
performance of manufacturing method 10, the electrically-conductive
coating layers may line the internal cavities of nozzle vane 56 and
rotor blade 64, as further generically indicated by the dashed
phantom lines shown in FIG. 7. The other non-illustrated turbine
nozzle vanes and rotor blades contained within turbine nozzle 58
and turbine rotor 66, respectively, may be fabricated utilizing
manufacturing method 10 in a similar or identical manner.
[0058] The metallic component or components fabricated utilizing
manufacturing method 10 (FIG. 1) and contained within GTE 50 may
possess one or more surfaces exposed to high temperature gas flow
during engine operation (represented in FIG. 7 by arrows 72). In
this case, it may be desirable to protect such surfaces with high
temperature coatings, which afford added thermal barrier or
environmental barrier protection to the underlying component bodies
within the high temperature, chemically-harsh GTE environment. As
indicated above, manufacturing method 10 may be utilized to
fabricate GTE components including high temperature coatings, which
are formed, at least in part, utilizing the electrically-conductive
coating layers when present. To provide a more specific example in
this regard, when manufacturing method 10 is utilized to fabricate
a GTE component having a central opening serving as or defining one
or more flow passages created by removal of the sacrificial tooling
structure, the electrically-conductive coating layer can be
utilized to form or help a high temperature coating or multilayer
coating system over the surfaces of the GTE component defining or
bounding the flow passage. Further illustrating this point, turbine
rotor shroud 68 is shown in FIG. 7 as including such a high
temperature coating 74, which bounds a flow passage provided
through shroud 68 and which circumscribes turbine rotor 66. High
temperature coating 74 can be produced, in whole or in part, from
an electrically-conductive coating layer when manufacturing method
10 (FIG. 1) is utilized to produce turbine rotor shroud 68, as
described more fully below.
[0059] One manner in which manufacturing method 10 can be utilized
to produce turbine rotor shroud 68 is as follows. First, as
explained above in conjunction with STEP 12 of manufacturing method
10 (FIG. 1), an AM process is utilized to produce a sacrificial
tooling structure having a surface geometry generally defining the
geometry of rotor shroud 68. In this particular example, the
sacrificial tooling structure may be fabricated as a disc-shaped
structure, the outer peripheral surface of which may have a
geometry desirably transferred to the metallic body layer during
electroforming. The sacrificial tooling structure also possesses
flow passage-defining region in that removal of the tooling
structure results in the formation of the flow passage, which
extends through rotor shroud 68 in the manner generally shown in
FIG. 7. An electrically-conductive coating layer is deposited over
the outer periphery of the sacrificial tooling structure at a
location generally corresponding to coating 74.
[0060] During the subsequently-performed electroforming process,
the electrically-conductive coating layer is energized, while the
sacrificial tooling structure is at least partially submerged in a
plating bath to form a metallic body layer/shell, which extends
over the flow passage-defining region of the tooling structure. The
metallic body layer/shell and, more generally, the resulting
metallic component is imparted with a flow passage section through
which gas flow is conducted during GTE operation. Additional
tooling structure may also be positioned adjacent the central
tooling structure to define flanges 76 or, instead, flanges 76 may
be produced separately and subsequently attached to the annular
body of shroud 68. After electroforming, build-up of the annular
body of rotor shroud 68, and formation of the central opening or
flow passage extending through shroud 68, the sacrificial tooling
structure is thermally decomposed, chemically dissolved, or
otherwise removed. Additional heat treatment is then be carried-out
to transform the electrically-conductive coating layer into coating
74 (e.g., when assuming the form of an aluminide coating); or
additional coating layers may be deposited over coating layer when
serving as a (e.g., MCrAlY) bond coat to complete coating 74 (e.g.,
when assuming the form of a multilayer coating system).
CONCLUSION
[0061] The foregoing has thus provided unique, additive-based
electroforming manufacturing methods, which enable the manufacture
of metallic components with abbreviated cycle times and at reduced
production costs as compared to conventional manufacturing methods.
Advantageously, embodiments of the above-described manufacturing
methods are amenable to the precision production of GTE components
and other turbomachine components having relatively complex,
thin-walled, hollow constructions. Additionally, embodiments of the
above-described manufacturing methods facilitate the formation of
high temperature coatings over selected component surfaces.
Embodiments of the manufacturing methods may consequently be
particularly useful in the fabrication of aerospace and
turbomachine components, which have relatively thin-walled or
shell-like constructions and which are predominately composed of
superalloy materials; although the manufacturing methods described
herein is not restricted to usage within any particular industry or
to the production of any particular type of metallic component.
[0062] While multiple exemplary embodiments have been presented in
the foregoing Detailed Description, it should be appreciated that a
vast number of variations exist. It should also be appreciated that
the exemplary embodiment or exemplary embodiments are only
examples, and are not intended to limit the scope, applicability,
or configuration of the invention in any way. Rather, the foregoing
Detailed Description will provide those skilled in the art with a
convenient road map for implementing an exemplary embodiment of the
invention. It being understood that various changes may be made in
the function and arrangement of elements described in an exemplary
embodiment without departing from the scope of the invention as
set-forth in the appended Claims.
* * * * *