U.S. patent application number 11/823699 was filed with the patent office on 2009-01-01 for investment casting cores and methods.
This patent application is currently assigned to United Technologies Corporation. Invention is credited to Justin D. Piggush.
Application Number | 20090000754 11/823699 |
Document ID | / |
Family ID | 39731087 |
Filed Date | 2009-01-01 |
United States Patent
Application |
20090000754 |
Kind Code |
A1 |
Piggush; Justin D. |
January 1, 2009 |
Investment casting cores and methods
Abstract
A method involves forming a core assembly. The forming includes
deforming a wire, the deforming including increasing a transverse
linear dimension along at least one portion of the wire. The wire
is assembled to a ceramic core
Inventors: |
Piggush; Justin D.;
(Hartford, CT) |
Correspondence
Address: |
BACHMAN & LAPOINTE, P.C. (P&W)
900 CHAPEL STREET, SUITE 1201
NEW HAVEN
CT
06510-2802
US
|
Assignee: |
United Technologies
Corporation
|
Family ID: |
39731087 |
Appl. No.: |
11/823699 |
Filed: |
June 27, 2007 |
Current U.S.
Class: |
164/15 ; 164/271;
164/361 |
Current CPC
Class: |
Y02T 50/676 20130101;
B22C 9/103 20130101; F05D 2230/211 20130101; Y02T 50/673 20130101;
F01D 5/186 20130101; Y02T 50/60 20130101 |
Class at
Publication: |
164/15 ; 164/271;
164/361 |
International
Class: |
B22C 9/10 20060101
B22C009/10; B22D 29/00 20060101 B22D029/00; B22C 9/04 20060101
B22C009/04 |
Claims
1. A method comprising: forming a casting core assembly, the
forming including: deforming a wire, the deforming including
increasing a transverse linear dimension along at least one portion
of the wire; and assembling the wire to a ceramic core.
2. The method of claim 1 wherein the increasing includes:
increasing a transverse cross-sectional area along said
portion.
3. The method of claim 1 wherein the increasing includes:
decreasing a transverse cross-sectional area along said
portion.
4. The method of claim 1 wherein the increasing includes:
melting.
5. The method of claim 1 wherein the assembling comprises:
inserting an end portion of the wire into a compartment of the
ceramic core.
6. The method of claim 1 wherein the assembling comprises:
inserting an intermediate portion of the wire into a compartment of
the ceramic core.
7. The method of claim 6 wherein: the intermediate portion is a
single intermediate portion and first and second ends of the wire
are left out of the compartment.
8. The method of claim 1 wherein the forming further comprises:
molding the ceramic core.
9. The method of claim 1 wherein the forming further comprises:
machining the compartment into the ceramic core.
10. The method of claim 1 wherein the deforming includes: spiraling
the wire.
11. The method of claim 1 further comprising: molding a
pattern-forming material at least partially over the core assembly
for forming a pattern; shelling the pattern; removing the
pattern-forming material from the shelled pattern for forming a
shell; introducing molten alloy to the shell; and removing the
shell and core assembly.
12. The method of claim 11 used to form a gas turbine engine
component.
13. The method of claim 11 used to form a gas turbine engine
airfoil wherein the wire casts an outlet passageway.
14. The method of claim 13 wherein: the ceramic core casts a feed
cavity; and first and second portions of the wire cast respective
first and second outlet passageways.
15. An investment casting core combination comprising: a metallic
wire casting core; and a ceramic feedcore in which an intermediate
portion of the metallic wire casting core is embedded.
16. The investment casting core combination of claim 15 further
comprising: a plurality of additional metallic wire casting cores,
each comprising: an intermediate portion in a compartment of the
ceramic core; and first and second end portions protruding from the
compartment.
17. An investment casting pattern comprising: the investment
casting core combination of claim 15; and a wax material at least
partially encapsulating the metallic wire casting core and the
feedcore and having: an airfoil contour surface including: a
leading edge portion; and pressure and suction side portions
extending from the leading edge portion, first and second end
portions of the metallic wire casting core protruding from at least
one of the pressure and suction side portions.
18. An investment casting shell comprising: the investment casting
core combination of claim 15; and a ceramic stucco at least
partially encapsulating the metallic wire core and the feedcore;
and an airfoil contour interior surface including: a leading edge
portion; and pressure and suction side portions extending from the
leading edge portion and formed by the ceramic stucco.
19. A method comprising: forming a core assembly, the forming
including: deforming a wire; and assembling the wire to a ceramic
core, including inserting an intermediate portion of the wire into
a compartment of the ceramic core.
20. The method of claim 19 wherein the forming further comprises:
molding the ceramic core.
21. The method of claim 19 wherein the forming further comprises:
machining the compartment into the ceramic core.
22. The method of claim 19 wherein: the intermediate portion is a
single intermediate portion and first and second ends of the wire
are left out of the compartment.
23. An investment casting core combination comprising: a metallic
wire casting core having a portion of increased transverse
dimension; and a ceramic feedcore in which a portion of the
metallic wire casting core is embedded.
24. The investment casting core combination of claim 23 wherein:
said transverse dimension distally increases along at least a
proximal region of the portion.
Description
BACKGROUND
[0001] The disclosure relates to investment casting. More
particularly, it relates to the investment casting of superalloy
turbine engine components.
[0002] Investment casting is a commonly used technique for forming
metallic components having complex geometries, especially hollow
components, and is used in the fabrication of superalloy gas
turbine engine components.
[0003] Gas turbine engines are widely used in aircraft propulsion,
electric power generation, and ship propulsion. In gas turbine
engine applications, efficiency is a prime objective. Improved gas
turbine engine efficiency can be obtained by operating at higher
temperatures, however current operating temperatures in the turbine
section exceed the melting points of the superalloy materials used
in turbine components. Consequently, it is a general practice to
provide air cooling. Cooling is provided by flowing relatively cool
air from the compressor section of the engine through passages in
the turbine components to be cooled. Such cooling comes with an
associated cost in engine efficiency. Consequently, there is a
strong desire to provide enhanced specific cooling, maximizing the
amount of cooling benefit obtained from a given amount of cooling
air. This may be obtained by the use of fine, precisely located,
cooling passageway sections.
[0004] The cooling passageway sections may be cast over casting
cores. Ceramic casting cores may be formed by molding a mixture of
ceramic powder and binder material by injecting the mixture into
hardened steel dies. After removal from the dies, the green cores
are thermally post-processed to remove the binder and fired to
sinter the ceramic powder together. The trend toward finer cooling
features has taxed core manufacturing techniques. The fine features
may be difficult to manufacture and/or, once manufactured, may
prove fragile. Commonly-assigned U.S. Pat. Nos. 6,637,500 of Shah
et al. and 6,929,054 of Beals et al (the disclosures of which are
incorporated by reference herein as if set forth at length)
disclose use of ceramic and refractory metal core combinations.
SUMMARY
[0005] One aspect of the disclosure involves a method wherein a
core assembly is formed. The forming includes deforming a wire, the
deforming including increasing a transverse linear dimension along
at least one portion of the wire. The wire is assembled to a
ceramic core.
[0006] Another aspect of the disclosure involves a method wherein a
core assembly is formed. The forming includes deforming a wire. The
wire is assembled to a ceramic core. The assembling includes
inserting an intermediate portion of the wire into a compartment of
the ceramic core.
[0007] The details of one or more embodiments are set forth in the
accompanying drawings and the description below. Other features,
objects, and advantages will be apparent from the description and
drawings, and from the claims.
BRIEF DESCRIPTION OF THE DRAWINGS
[0008] FIG. 1 is a view of a first core assembly.
[0009] FIG. 2 is a cutaway view of the assembly of FIG. 1.
[0010] FIG. 3 is a view of a shelled pattern including the assembly
of FIG. 2.
[0011] FIG. 4 is a sectional view of a casting formed from the
shelled pattern of FIG. 3.
[0012] FIG. 5 is a transverse sectional view of the casting of FIG.
4, taken along line 5-5.
[0013] FIG. 6 is a transverse sectional view of an alternate
casting.
[0014] FIG. 7 is a view of an RMC protuberance associated with the
alternate casting of FIG. 6.
[0015] FIG. 8 is a plan view of an alternate RMC.
[0016] FIG. 9 is a side cutaway view of a shelled pattern including
the RMC of FIG. 8.
[0017] FIG. 10 is a sectional view of a casting formed by the
shelled pattern of FIG. 9.
[0018] FIG. 11 is a view of a second alternate RMC.
[0019] FIG. 12 is a view of third alternate RMCs.
[0020] FIG. 13 is a view of further alternate RMCS.
[0021] FIG. 14 is a view of an alternate core assembly.
[0022] FIG. 15 is a sectional view of a shell including an
alternate core assembly.
[0023] Like reference numbers and designations in the various
drawings indicate like elements.
DETAILED DESCRIPTION
[0024] FIG. 1 shows a core assembly 20 including a molded ceramic
feedcore 22 and a plurality of refractory metal cores (RMCs--e.g.,
molybdenum-based alloys or essentially pure molybdenum) 24. FIG. 2
shows an RMC 24 as extending from a proximal end 26 to a distal end
28. A proximal end region 30 of the RMC is within a compartment 32
of the feedcore 22 with the remaining portion of the RMC protruding
beyond an adjacent surface 34 of the feedcore. The portion 30 may
be secured in the compartment 32 via a material 36 which may be an
adhesive and/or space-filling material (e.g., a ceramic
adhesive).
[0025] The exemplary RMC 24 has a distal end protuberance 38. A
remainder of the RMC may be of essentially uniform cross-section
(e.g., a circular section inherited from a wire precursor to the
RMC). The RMC may be manufactured in one or more steps by cutting
from a larger body (e.g., a roll) of wire, plastically deforming
the wire to form the convoluted shape, and forming the protuberance
38.
[0026] The protuberance 38 may be formed by a deforming to increase
at least one transverse dimension. Exemplary deforming may include
one or more of melting and stamping. An exemplary deforming may
locally increase cross-sectional area (e.g., a melting might form a
globular protuberance of increased dimension in two transverse
directions. An exemplary alternative wire cross-section is
rectangular or square.
[0027] Although an exemplary protuberance is of increased
cross-sectional area, other protuberances may have decreased areas
(e.g., potentially associated with a flattening/fanning so that the
cross-section increases in at least one linear dimension but may
decrease in another).
[0028] Before or after the forming of the RMC 24, the end portion
30 is inserted into the compartment 32 and, optionally, secured
thereto via the material 36. A sacrificial pattern-forming material
(e.g., a wax) may be molded at least partially over the feedcore 22
and RMC 24 so as to form a casting pattern. The casting pattern may
be shelled. FIG. 3 shows a shelled pattern 40 including the core
assembly 20, pattern wax 42, and a ceramic stucco shell 44. A
distal portion 46 of the protuberance 38 is embedded within the
shell 44 whereas the proximal portion 48 is embedded in the wax 42.
An end portion (not shown) of the feedcore 22 may also be embedded
in the shell 44. After dewaxing, the core assembly is left within
the shell 44, with the RMCs 24 extending within a cavity between
the feedcore and shell. Molten metal is then cast in the
cavity.
[0029] FIG. 4 shows the metal casting 50 after decoring/deshelling.
The casting 50 has an internal/interior surface 52 along an
internal/interior passageway 54 cast by the surface 34 of the
feedcore 22. The casting 50 has an external/exterior surface 56
cast by the shell interior surface. The casting 50 has an outlet
passageway 58 cast by the RMC 24. The passageway 58 has an inlet 60
at the surface 52 and an outlet 62 at the surface 56. At the outlet
62, the passageway 58 has a flared discharge end 64 cast by the
protuberance proximal portion 48.
[0030] FIG. 5 is a section transverse to the exemplary section of
FIG. 4 and showing the exemplary discharge end 64 as flared
(distally increasing in transverse dimension) in two
transverse/normal directions so as to increase in cross-sectional
area toward the outlet 62. FIG. 6 is a sectional view similar to
FIG. 5 of an alternate discharge end 64' which flares (distally
increases in transverse dimension) in one direction but tapers
(distally decreases in transverse dimension) in the direction
transverse thereto. The outlet may be cast by the correspondingly
shaped portion of a protuberance (e.g., the proximal portion of a
terminal/end protuberance). For example, such a discharge end may
be formed by the proximal portion of a flattened protuberance 38'
(FIG. 7) which may be formed by stamping or otherwise
compressing.
[0031] In an exemplary reengineering situation, the passageway 58
may replace a straight drilled passageway of a baseline
configuration. The convolution offered by casting may increase
specific heat transfer relative to the baseline. The flaring of the
discharge end may serve a similar function as chamfering of drilled
outlet passageways. The engineering or reengineering may configure
the flaring of the discharge end 64 (and thus of the protuberance
38, 38') to advantageously spread the cooling air film over the
surface of the component (e.g., of the casting after any further
machining/treatment/coating). In addition to providing better
airflow coverage, the diffuse introduction of cooling air may
improve attachment of the cooling film to prevent blow-off of air
into the gas flow over the component. The cross-sectional area and
shape of the outlet 62 may be configured to provide a desired flow
rate and velocity of the outlet flow. The RMC protuberance portion
38;38' and associated passageway discharge end 64;64' may be
configured to provide a transition from this shape to the
cross-section of the remaining portion of the RMC (e.g., a
circular-sectioned wire, square-sectioned wire, or the like). An
exemplary transition is an approximately linear transition over a
length of approximately 2-10 times the characteristic
cross-sectional dimension (e.g., diameter) of the undeformed main
portion of the RMC. Exemplary diameter (or other characteristic
cross-sectional dimension for non-circular wire) is 0.3-1.0 mm.
Exemplary flaring increases the cross-sectional dimension to 2-5
times this amount.
[0032] An intermediate portion 70 (FIG. 2) of the RMC 24 may be
formed with an appropriate convoluted shape (e.g., at bends 71, 72,
73, and 74) to provide increased flow path length for the resulting
passageway 58 (e.g., a length more than double the straight line
distance between the inlet 60 and the outlet 62 (e.g., 3-5
times)).
[0033] FIG. 8 is a plan view of an alternate RMC with an
out-of-plane bend 80 at the proximal portion 30 and an opposite
out-of-plane bend 82 inboard of a flattened protuberance 38''. The
serpentine intermediate portion 84 thus extends lengthwise within
the associated pattern material 42 (FIG. 9) to create a
corresponding passageway serpentine 86 (FIG. 10) extending
lengthwise within the casting. The protuberance 38'' casts a
corresponding flared discharge end 64''.
[0034] FIG. 11 shows an alternate RMC 100 wherein the intermediate
portion forms a spiral. The spiral configuration may help to manage
pressure drop and air flow while providing a desired amount of
convective cooling. Outlet passageways are often in locations where
there are large pressure differences between the internal feed
pressure and the external dump pressure. With a straight drilled
hole, hole length is essentially set by wall thickness and drilling
angle. A straight hole may result in small frictional losses and a
high outlet flow velocity thus causing cooling film blow-off.
Serpentine, spiral, or other convoluted configurations may allow
tailoring of frictional loss to achieve a desired flow of velocity
while providing desired cooling over the planform area occupied by
the passageway.
[0035] FIG. 12 shows an array of cores 120. Exemplary cores 120 may
be secured to each other by joints 122 which may be welds, brazes,
and the like. In the case of brazes, these joints may well be
effective only to maintain the core array as an assembly during
pattern formation and shelling. Casting may well undue the
braze.
[0036] FIG. 13 shows an alternative array of cores 130 wherein
joints 132 are formed by interwrapping, tying, or other mechanical
interfitting.
[0037] FIG. 14 shows an alternative core assembly 140 including a
ceramic feedcore 142 and a plurality of RMCs 144. Each exemplary
RMC has first and second ends 146 and 148 each with end
protuberances. The RMC has an intermediate portion 150 in a
slot-like compartment 152 (optionally secured by filler material
154). The exemplary intermediate portion 150 is a right U-shape and
fits securely in the compartment 152.
[0038] FIG. 15 shows an alternative core assembly 160 in a shell
162. The core assembly includes a ceramic feedcore 164 and an RMC
wire 166. The wire extends from a first end 170 to a second end
172. The wire has a plurality of portions 174 engaged to the
feedcore (e.g., embedded in ceramic adhesive or filler 176 in slots
178). The portions 174 are interspersed with portions protruding
from the feedcore. Each of the exemplary protruding portions
includes a portion 180 embedded in the shell and a pair of leg
portions 182 spanning the gap 184 to the adjacent portions 174.
Protuberances 186 are formed at junctions of the portions 180 and
182 for casting at least partially divergent outlets in the cast
part (e.g., as discussed above). Exemplary protuberances may be
formed by mechanical deformation (e.g., crimping). Via such a wire,
one or more rows of outlet passageways can be cast from a single
wire. Such a wire may be pre-bent and pre-crimped to define the
distinct portions and the protuberances. Alternatively, a
numerically-controlled machine could make the bends (and optionally
the crimps) during placement of the wire.
[0039] An exemplary location appropriate for particularly
long/convoluted (e.g., serpentine) outlet passageways is on the
suction side of a blade or vane airfoil. On the suction side there
is typically a large difference between the external (dump)
pressure and the internal (feed) pressure. Additionally dumping
coolant downstream of the gauge point (the location on the airfoil
nearest the adjacent airfoil) results in large aerodynamic losses
and is therefore undesirable. The inlet of the serpentine outlet
passageway could be downstream of the gauge point. The outlet
passageways could then be routed upstream through the wall of the
airfoil to an outlet upstream of the gauge point (thereby reducing
losses). The lengthening of the passageway caused by convolution
could be selected so that the frictional losses within the hole
provide an optimal flow rate at an optimal velocity. The pressure
loss through the hole roughly translates into heat transfer
coefficient. Therefore the convolutions would typically increase
the convective efficiency of the hole.
[0040] On the pressure side of an airfoil there are local
variations in the feed to dump pressure along the airfoil. On the
pressure side, the passageway length and degree of convolution may
be selected so that the frictional loss within the passageway
provide an optimal coolant exit flow rate at an optimal velocity
all along the pressure side of the airfoil.
[0041] One or more embodiments have been described. Nevertheless,
it will be understood that various modifications may be made. For
example, the principles may be implemented using modifications of
various existing or yet-developed processes, apparatus, or
resulting cast article structures (e.g., in a reengineering of a
baseline cast article to modify cooling passageway configuration).
In any such implementation, details of the baseline process,
apparatus, or article may influence details of the particular
implementation. Accordingly, other embodiments are within the scope
of the following claims.
* * * * *