US20170173673A1 - Method including fiber reinforced casting article - Google Patents
Method including fiber reinforced casting article Download PDFInfo
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- US20170173673A1 US20170173673A1 US15/448,267 US201715448267A US2017173673A1 US 20170173673 A1 US20170173673 A1 US 20170173673A1 US 201715448267 A US201715448267 A US 201715448267A US 2017173673 A1 US2017173673 A1 US 2017173673A1
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- fibers
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- casting article
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22C—FOUNDRY MOULDING
- B22C9/00—Moulds or cores; Moulding processes
- B22C9/10—Cores; Manufacture or installation of cores
- B22C9/106—Vented or reinforced cores
-
- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D29/00—Removing castings from moulds, not restricted to casting processes covered by a single main group; Removing cores; Handling ingots
- B22D29/001—Removing cores
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- B—PERFORMING OPERATIONS; TRANSPORTING
- B22—CASTING; POWDER METALLURGY
- B22D—CASTING OF METALS; CASTING OF OTHER SUBSTANCES BY THE SAME PROCESSES OR DEVICES
- B22D29/00—Removing castings from moulds, not restricted to casting processes covered by a single main group; Removing cores; Handling ingots
- B22D29/001—Removing cores
- B22D29/002—Removing cores by leaching, washing or dissolving
Definitions
- Gas turbine engines include various components, such as blades, vanes, and blade outer air seals (BOASs), that are exposed to relatively hot gases during operation of the engine. These components often include internal passageways for routing a flow of cooling fluid within the component.
- BOASs blade outer air seals
- Components having relatively complex internal passageways are manufactured using a number of techniques.
- One example technique is investment casting.
- casting articles are used to form internal passageways.
- molten metal is poured around the casting articles, and, after the metal is allowed to cool, the casting articles are removed from the interior of the components using a leaching technique, for example.
- a method of forming an engine component according to an exemplary aspect of the present disclosure includes, among other things, introducing molten metal into a cavity between a shell and a casting article in the shell.
- the casting article includes a ceramic portion and a plurality of fibers.
- the method further includes separately removing the ceramic portion and the fibers from an interior of the component.
- the foregoing method includes cooling the molten metal, and the plurality of fibers and the ceramic portion are removed after the molten metal cools.
- the ceramic portion is removed from the component using a first leaching fluid
- the fibers are removed from the component using a second leaching fluid different in chemical composition than the first leaching fluid
- the ceramic portion is removed from the component using a leaching fluid, and the fibers are mechanically removed from the component.
- the fibers are blown out of the component using a pressurized fluid.
- the pressurized fluid is pressurized air.
- a maximum length of the fibers is less than a smallest orifice formed in the engine component.
- the fibers dissolve during the introducing step.
- the fibers fully dissolve during the introducing step.
- the remainder of the casting article is removed from the component using a leaching fluid.
- the size and chemical composition of the fibers is selected such that the fibers will intentionally dissolve during the introducing step.
- the fibers are randomly oriented within the ceramic portion.
- the ceramic portion includes alumina (Al 2 O 3 ).
- the fibers are provided by one of (1) silicon (Si) fibers, (2) carbon (C) fibers, and (3) metal fibers.
- a method of forming an engine component according to another exemplary aspect of this disclosure includes, among other things, introducing molten metal into a cavity between a shell and a casting article.
- the casting article includes a ceramic portion and a plurality of fibers.
- the method further includes dissolving the fibers during the introducing step, and removing the remainder of the casting article from the interior of the component using a leaching fluid.
- the size and material of the fibers is selected such that the fibers will intentionally dissolve during the introducing step.
- the fibers completely dissolve during the introducing step.
- the ceramic portion includes alumina (Al 2 O 3 ).
- the fibers are provided by one of (1) silicon (Si) fibers, (2) carbon (C) fibers, and (3) metal fibers.
- a method of forming an engine component according to yet another exemplary aspect of this disclosure includes, among other things, providing a ceramic shell and a casting article.
- the casting article includes a ceramic portion and a plurality of fibers.
- the method further includes sintering the ceramic shell and the casting article, wherein the plurality of fibers are dissolved by the sintering step, introducing a molten metal between the shell and the casting article, and removing the remainder of the casting article from the interior of the component.
- FIG. 1 schematically illustrates an example gas turbine engine.
- FIG. 2 illustrates an example engine component in phantom, and further illustrates an example casting article.
- FIG. 3 is a close-up of the encircled area in FIG. 2 .
- FIG. 4 is a flow chart representing an example method for forming a casting article.
- FIG. 5 is a flow chart representing an example method for forming an engine component.
- FIG. 1 schematically illustrates a gas turbine engine 20 .
- the gas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates a fan section 22 , a compressor section 24 , a combustor section 26 and a turbine section 28 .
- Alternative engines might include an augmentor section (not shown) among other systems or features.
- the fan section 22 drives air along a bypass flow path B in a bypass duct defined within a nacelle 15
- the compressor section 24 drives air along a core airflow path C for compression and communication into the combustor section 26 then expansion through the turbine section 28 .
- the exemplary engine 20 generally includes a low speed spool 30 and a high speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an engine static structure 36 via several bearing systems 38 . It should be understood that various bearing systems 38 at various locations may alternatively or additionally be provided, and the location of bearing systems 38 may be varied as appropriate to the application.
- the low speed spool 30 generally includes an inner shaft 40 that interconnects a fan 42 , a first (or low) pressure compressor 44 and a first (or low) pressure turbine 46 .
- the inner shaft 40 is connected to the fan 42 through a speed change mechanism, which in exemplary gas turbine engine 20 is illustrated as a geared architecture 48 to drive the fan 42 at a lower speed than the low speed spool 30 .
- the high speed spool 32 includes an outer shaft 50 that interconnects a second (or high) pressure compressor 52 and a second (or high) pressure turbine 54 .
- a combustor 56 is arranged in exemplary gas turbine 20 between the high pressure compressor 52 and the high pressure turbine 54 .
- a mid-turbine frame 57 of the engine static structure 36 is arranged generally between the high pressure turbine 54 and the low pressure turbine 46 .
- the mid-turbine frame 57 further supports bearing systems 38 in the turbine section 28 .
- the inner shaft 40 and the outer shaft 50 are concentric and rotate via bearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes.
- the core airflow is compressed by the low pressure compressor 44 then the high pressure compressor 52 , mixed and burned with fuel in the combustor 56 , then expanded over the high pressure turbine 54 and low pressure turbine 46 .
- the mid-turbine frame 57 includes airfoils 59 which are in the core airflow path C.
- the turbines 46 , 54 rotationally drive the respective low speed spool 30 and high speed spool 32 in response to the expansion.
- gear system 48 may be located aft of combustor section 26 or even aft of turbine section 28
- fan section 22 may be positioned forward or aft of the location of gear system 48 .
- FIG. 2 illustrates an example engine component 60 in phantom.
- the engine component 60 is a blade, such as a blade for use within the turbine section 28 of the engine 20 .
- this disclosure extends to other engine components, including vanes and blade outer air seals (BOASs), as examples. It should be understood that this disclosure is not limited to components in the turbine section 28 , and extends to other sections of the engine 20 .
- BOASs blade outer air seals
- the component 60 includes an airfoil section 62 , a platform 64 , and a root section 66 .
- An example casting article, or core, is illustrated at 68 .
- the casting article 68 is used during an investment casting process to form an internal passageway within the component 60 .
- the shape of the casting article 68 is a negative of the intended shape of the internal passageway.
- the casting article 68 may be shaped differently than the specific casting article 68 illustrated in FIG. 2 .
- additional casting articles may be used to provide the component 60 with the intended internal passageway configuration.
- the component 60 may include internal passageways that direct fluid to an exterior surface of the component 60 for film cooling.
- FIG. 3 illustrates the detail of the casting article 68 .
- the casting article 68 includes a plurality of fibers 70 incorporated into a ceramic material 72 .
- the fibers 70 may be randomly oriented within the ceramic portion 72 or introduced in an ordered structure.
- the fibers 70 increase the strength of the casting article 68 .
- FIG. 4 illustrates an example method 74 of forming the casting article 68 .
- a slurry (or mix) of ceramic material is provided.
- the slurry may include a carrier fluid or media and ceramic particles.
- the carrier fluid can be any known type of carrier fluid, such as a solvent, water, alcohol, or solid or semi-solid media such as wax.
- the ceramic particles may be provided by any known type of ceramic material, including but not limited to alumina (Al 2 O 3 ), silica (SiO 2 ), aluminosilicate (Al 2 SiO 4 ), and zircon (ZrAl 2 O 4 ).
- the slurry may also contain smaller quantities of the elemental oxides for modification of specific properties.
- the slurry provided at 76 will ultimately form the ceramic portion 72 of the casting article 68 .
- the fibers 70 are added into the slurry.
- the fibers may be silicon (Si) fibers, alumina (Al 2 O 3 ), organic fibers such as carbon (C) fibers, or metal fibers, to name a few examples.
- the volumetric ratio of the fibers to slurry might range from 1% to 50%, depending on casting requirements.
- the fibers may be relatively evenly dispersed, randomly dispersed, or may be preferentially dispersed within the casting article. Fibers may take various shapes and sizes from nanoparticle to microfibers that extend through the components. The fibers may be random or oriented to maximize physical properties in a desired direction.
- the slurry which now includes the fibers 78 , is introduced into a die, and the casting article 68 is formed.
- FIG. 5 illustrates an example method 82 for forming an engine component having an internal passageway.
- the method 82 is an investment casting technique.
- a wax pattern of the engine component which includes the casting article 68 , is provided.
- a ceramic shell is formed around the wax pattern and the casting article 68 .
- wax is removed from the ceramic shell leaving a hollow cavity in the ceramic shell containing the integral ceramic casting article.
- the ceramic shell is heated to sinter the ceramic.
- molten metal is introduced (e.g., poured) into the ceramic shell, at 88 , and replaces the place of the wax pattern. The molten metal is allowed to cool, and the casting article 68 is removed at 94 .
- the casting article 68 may not withstand the thermal stresses from the molten metal.
- the fibers 70 reinforce the casting article 68 , and increase the overall mechanical properties of the casting article 68 .
- the size (including the length L and thickness) of the fibers 68 , as well as the chemical composition of the fibers, may be adjusted such that the fibers either survive the ceramic shell sintering at step 92 (“option 1” at 96 ), or are removed (e.g., dissolved) by heat (“option 2” at 96 ).
- fibers comprised of, for example, silicon would likely remain post-pour and fibers comprised of, for example, carbon would likely be consumed during the pour and cooling process.
- the fibers 70 survive long enough to keep the casting article 68 intact during the hot pour of molten metal. Further, by dissolving the fibers, the ease of removing the casting article at 94 increases.
- the casting article 68 may be removed chemically or thermally from out of the component 60 .
- At least the ceramic portion 72 of the casting article 68 is leachable using a known leaching fluid (e.g., Sodium Hydroxide).
- the fibers 70 depending on their material, may also be leachable. In one example, the fibers 70 are leached using a different fluid (e.g., a fluid having a different chemical composition) than the fluid used to leach the ceramic portion 72 (“option 1” at 98 ).
- the ceramic portion 72 is leachable, but the fibers 70 are not.
- the fibers 70 may be mechanically removed from the component 60 .
- mechanical removal includes blowing out (i.e., purging) the fibers 70 using a pressurized fluid that carries the fibers out of the internal passageway, such as pressurized air (“option 2” at 98 ).
- pressurized air such as pressurized air
- the maximum allowable length L of the fibers 70 is less than the smallest orifice formed in the component 60 .
- the ceramic portion 72 can be leached and no further removal of fibers is required (“option 3” at 98 ).
- This disclosure provides a casting article having increased structural integrity, which leads to higher quality components. Further, the disclosed techniques increase the reliability and repeatability of the process for removing the casting article 68 from the interior of the component. This reduces cleaning time and streamlines manufacturing overall.
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- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
- Manufacture Of Alloys Or Alloy Compounds (AREA)
- Mold Materials And Core Materials (AREA)
- Molds, Cores, And Manufacturing Methods Thereof (AREA)
Abstract
Description
- Gas turbine engines include various components, such as blades, vanes, and blade outer air seals (BOASs), that are exposed to relatively hot gases during operation of the engine. These components often include internal passageways for routing a flow of cooling fluid within the component.
- Components having relatively complex internal passageways are manufactured using a number of techniques. One example technique is investment casting. In this technique, casting articles are used to form internal passageways. In particular, molten metal is poured around the casting articles, and, after the metal is allowed to cool, the casting articles are removed from the interior of the components using a leaching technique, for example.
- A method of forming an engine component according to an exemplary aspect of the present disclosure includes, among other things, introducing molten metal into a cavity between a shell and a casting article in the shell. The casting article includes a ceramic portion and a plurality of fibers. The method further includes separately removing the ceramic portion and the fibers from an interior of the component.
- In a further non-limiting embodiment, the foregoing method includes cooling the molten metal, and the plurality of fibers and the ceramic portion are removed after the molten metal cools.
- In a further non-limiting embodiment of the foregoing method, the ceramic portion is removed from the component using a first leaching fluid, and the fibers are removed from the component using a second leaching fluid different in chemical composition than the first leaching fluid.
- In a further non-limiting embodiment of the foregoing method, the ceramic portion is removed from the component using a leaching fluid, and the fibers are mechanically removed from the component.
- In a further non-limiting embodiment of the foregoing method, the fibers are blown out of the component using a pressurized fluid.
- In a further non-limiting embodiment of the foregoing method, the pressurized fluid is pressurized air.
- In a further non-limiting embodiment of the foregoing method, a maximum length of the fibers is less than a smallest orifice formed in the engine component.
- In a further non-limiting embodiment of the foregoing method, the fibers dissolve during the introducing step.
- In a further non-limiting embodiment of the foregoing method, the fibers fully dissolve during the introducing step.
- In a further non-limiting embodiment of the foregoing method, after the molten metal cools, the remainder of the casting article is removed from the component using a leaching fluid.
- In a further non-limiting embodiment of the foregoing method, the size and chemical composition of the fibers is selected such that the fibers will intentionally dissolve during the introducing step.
- In a further non-limiting embodiment of the foregoing method, the fibers are randomly oriented within the ceramic portion.
- In a further non-limiting embodiment of the foregoing method, the ceramic portion includes alumina (Al2O3).
- In a further non-limiting embodiment of the foregoing method, the fibers are provided by one of (1) silicon (Si) fibers, (2) carbon (C) fibers, and (3) metal fibers.
- A method of forming an engine component according to another exemplary aspect of this disclosure includes, among other things, introducing molten metal into a cavity between a shell and a casting article. The casting article includes a ceramic portion and a plurality of fibers. The method further includes dissolving the fibers during the introducing step, and removing the remainder of the casting article from the interior of the component using a leaching fluid.
- In a further non-limiting embodiment of the foregoing method, the size and material of the fibers is selected such that the fibers will intentionally dissolve during the introducing step.
- In a further non-limiting embodiment of the foregoing method, the fibers completely dissolve during the introducing step.
- In a further non-limiting embodiment of the foregoing method, the ceramic portion includes alumina (Al2O3).
- In a further non-limiting embodiment of the foregoing method, the fibers are provided by one of (1) silicon (Si) fibers, (2) carbon (C) fibers, and (3) metal fibers.
- A method of forming an engine component according to yet another exemplary aspect of this disclosure includes, among other things, providing a ceramic shell and a casting article. The casting article includes a ceramic portion and a plurality of fibers. The method further includes sintering the ceramic shell and the casting article, wherein the plurality of fibers are dissolved by the sintering step, introducing a molten metal between the shell and the casting article, and removing the remainder of the casting article from the interior of the component.
- The embodiments, examples and alternatives of the preceding paragraphs, the claims, or the following description and drawings, including any of their various aspects or respective individual features, may be taken independently or in any combination. Features described in connection with one embodiment are applicable to all embodiments, unless such features are incompatible.
- The drawings can be briefly described as follows:
-
FIG. 1 schematically illustrates an example gas turbine engine. -
FIG. 2 illustrates an example engine component in phantom, and further illustrates an example casting article. -
FIG. 3 is a close-up of the encircled area inFIG. 2 . -
FIG. 4 is a flow chart representing an example method for forming a casting article. -
FIG. 5 is a flow chart representing an example method for forming an engine component. -
FIG. 1 schematically illustrates agas turbine engine 20. Thegas turbine engine 20 is disclosed herein as a two-spool turbofan that generally incorporates afan section 22, acompressor section 24, a combustor section 26 and aturbine section 28. Alternative engines might include an augmentor section (not shown) among other systems or features. Thefan section 22 drives air along a bypass flow path B in a bypass duct defined within anacelle 15, while thecompressor section 24 drives air along a core airflow path C for compression and communication into the combustor section 26 then expansion through theturbine section 28. Although depicted as a two-spool turbofan gas turbine engine in the disclosed non-limiting embodiment, it should be understood that the concepts described herein are not limited to use with two-spool turbofans as the teachings may be applied to other types of turbine engines including three-spool architectures. - The
exemplary engine 20 generally includes alow speed spool 30 and ahigh speed spool 32 mounted for rotation about an engine central longitudinal axis A relative to an enginestatic structure 36 viaseveral bearing systems 38. It should be understood thatvarious bearing systems 38 at various locations may alternatively or additionally be provided, and the location ofbearing systems 38 may be varied as appropriate to the application. - The
low speed spool 30 generally includes aninner shaft 40 that interconnects afan 42, a first (or low) pressure compressor 44 and a first (or low)pressure turbine 46. Theinner shaft 40 is connected to thefan 42 through a speed change mechanism, which in exemplarygas turbine engine 20 is illustrated as a gearedarchitecture 48 to drive thefan 42 at a lower speed than thelow speed spool 30. Thehigh speed spool 32 includes anouter shaft 50 that interconnects a second (or high) pressure compressor 52 and a second (or high)pressure turbine 54. Acombustor 56 is arranged inexemplary gas turbine 20 between the high pressure compressor 52 and thehigh pressure turbine 54. Amid-turbine frame 57 of the enginestatic structure 36 is arranged generally between thehigh pressure turbine 54 and thelow pressure turbine 46. Themid-turbine frame 57 further supports bearingsystems 38 in theturbine section 28. Theinner shaft 40 and theouter shaft 50 are concentric and rotate viabearing systems 38 about the engine central longitudinal axis A which is collinear with their longitudinal axes. - The core airflow is compressed by the low pressure compressor 44 then the high pressure compressor 52, mixed and burned with fuel in the
combustor 56, then expanded over thehigh pressure turbine 54 andlow pressure turbine 46. Themid-turbine frame 57 includesairfoils 59 which are in the core airflow path C. Theturbines low speed spool 30 andhigh speed spool 32 in response to the expansion. It will be appreciated that each of the positions of thefan section 22,compressor section 24, combustor section 26,turbine section 28, and fandrive gear system 48 may be varied. For example,gear system 48 may be located aft of combustor section 26 or even aft ofturbine section 28, andfan section 22 may be positioned forward or aft of the location ofgear system 48. -
FIG. 2 illustrates anexample engine component 60 in phantom. In this example, theengine component 60 is a blade, such as a blade for use within theturbine section 28 of theengine 20. It should be understood that this disclosure extends to other engine components, including vanes and blade outer air seals (BOASs), as examples. It should be understood that this disclosure is not limited to components in theturbine section 28, and extends to other sections of theengine 20. - The
component 60 includes anairfoil section 62, aplatform 64, and aroot section 66. An example casting article, or core, is illustrated at 68. The castingarticle 68 is used during an investment casting process to form an internal passageway within thecomponent 60. The shape of thecasting article 68 is a negative of the intended shape of the internal passageway. In this respect, the castingarticle 68 may be shaped differently than thespecific casting article 68 illustrated inFIG. 2 . Further, while only onecasting article 68 is illustrated, additional casting articles may be used to provide thecomponent 60 with the intended internal passageway configuration. In particular, thecomponent 60 may include internal passageways that direct fluid to an exterior surface of thecomponent 60 for film cooling. -
FIG. 3 illustrates the detail of thecasting article 68. In this example, the castingarticle 68 includes a plurality offibers 70 incorporated into aceramic material 72. Thefibers 70 may be randomly oriented within theceramic portion 72 or introduced in an ordered structure. Thefibers 70 increase the strength of thecasting article 68. -
FIG. 4 illustrates anexample method 74 of forming thecasting article 68. At 76, a slurry (or mix) of ceramic material is provided. The slurry may include a carrier fluid or media and ceramic particles. The carrier fluid can be any known type of carrier fluid, such as a solvent, water, alcohol, or solid or semi-solid media such as wax. The ceramic particles may be provided by any known type of ceramic material, including but not limited to alumina (Al2O3), silica (SiO2), aluminosilicate (Al2SiO4), and zircon (ZrAl2O4). The slurry may also contain smaller quantities of the elemental oxides for modification of specific properties. The slurry provided at 76 will ultimately form theceramic portion 72 of thecasting article 68. At 78, thefibers 70 are added into the slurry. The fibers may be silicon (Si) fibers, alumina (Al2O3), organic fibers such as carbon (C) fibers, or metal fibers, to name a few examples. The volumetric ratio of the fibers to slurry might range from 1% to 50%, depending on casting requirements. In this embodiment, the fibers may be relatively evenly dispersed, randomly dispersed, or may be preferentially dispersed within the casting article. Fibers may take various shapes and sizes from nanoparticle to microfibers that extend through the components. The fibers may be random or oriented to maximize physical properties in a desired direction. At 80, the slurry, which now includes thefibers 78, is introduced into a die, and thecasting article 68 is formed. -
FIG. 5 illustrates anexample method 82 for forming an engine component having an internal passageway. Themethod 82 is an investment casting technique. At 84, a wax pattern of the engine component, which includes the castingarticle 68, is provided. At 86, a ceramic shell is formed around the wax pattern and thecasting article 68. At 88, wax is removed from the ceramic shell leaving a hollow cavity in the ceramic shell containing the integral ceramic casting article. At 90, the ceramic shell is heated to sinter the ceramic. At 92, molten metal is introduced (e.g., poured) into the ceramic shell, at 88, and replaces the place of the wax pattern. The molten metal is allowed to cool, and thecasting article 68 is removed at 94. - Without the
fibers 70, the castingarticle 68 may not withstand the thermal stresses from the molten metal. Thefibers 70 reinforce thecasting article 68, and increase the overall mechanical properties of thecasting article 68. - The size (including the length L and thickness) of the
fibers 68, as well as the chemical composition of the fibers, may be adjusted such that the fibers either survive the ceramic shell sintering at step 92 (“option 1” at 96), or are removed (e.g., dissolved) by heat (“option 2” at 96). In this example, fibers comprised of, for example, silicon would likely remain post-pour and fibers comprised of, for example, carbon would likely be consumed during the pour and cooling process. In the example where thefibers 68 do not dissolve during sintering, thefibers 70 survive long enough to keep the castingarticle 68 intact during the hot pour of molten metal. Further, by dissolving the fibers, the ease of removing the casting article at 94 increases. - At 94, the casting
article 68 may be removed chemically or thermally from out of thecomponent 60. At least theceramic portion 72 of thecasting article 68 is leachable using a known leaching fluid (e.g., Sodium Hydroxide). Thefibers 70, depending on their material, may also be leachable. In one example, thefibers 70 are leached using a different fluid (e.g., a fluid having a different chemical composition) than the fluid used to leach the ceramic portion 72 (“option 1” at 98). - In another example, the
ceramic portion 72 is leachable, but thefibers 70 are not. In that example, thefibers 70 may be mechanically removed from thecomponent 60. In one example, mechanical removal includes blowing out (i.e., purging) thefibers 70 using a pressurized fluid that carries the fibers out of the internal passageway, such as pressurized air (“option 2” at 98). In this example, it may be important to ensure that the length L of thefibers 70 is substantially small. In particular, in one example, the maximum allowable length L of thefibers 70 is less than the smallest orifice formed in thecomponent 60. Finally, in the example where thefibers 70 dissolve duringstep 90, theceramic portion 72 can be leached and no further removal of fibers is required (“option 3” at 98). - This disclosure provides a casting article having increased structural integrity, which leads to higher quality components. Further, the disclosed techniques increase the reliability and repeatability of the process for removing the
casting article 68 from the interior of the component. This reduces cleaning time and streamlines manufacturing overall. - It should be understood that terms such as “axial” and “radial” are used above with reference to the normal operational attitude of the
engine 20. Further, these terms have been used herein for purposes of explanation, and should not be considered otherwise limiting. Terms such as “generally,” “substantially,” and “about” are not intended to be boundaryless terms, and should be interpreted consistent with the way one skilled in the art would interpret the term. - Although the different examples have the specific components shown in the illustrations, embodiments of this disclosure are not limited to those particular combinations. It is possible to use some of the components or features from one of the examples in combination with features or components from another one of the examples.
- One of ordinary skill in this art would understand that the above-described embodiments are exemplary and non-limiting. That is, modifications of this disclosure would come within the scope of the claims. Accordingly, the following claims should be studied to determine their true scope and content.
Claims (19)
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US15/448,267 US20170173673A1 (en) | 2014-06-20 | 2017-03-02 | Method including fiber reinforced casting article |
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US10507515B2 (en) * | 2014-12-15 | 2019-12-17 | United Technologies Corporation | Ceramic core for component casting |
US20190060982A1 (en) | 2017-08-29 | 2019-02-28 | General Electric Company | Carbon fibers in ceramic cores for investment casting |
Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5126082A (en) * | 1988-11-30 | 1992-06-30 | Howmet Corporation | Method of making ceramic cores and other articles |
JPH09253792A (en) * | 1996-03-25 | 1997-09-30 | Nissan Motor Co Ltd | Paper core for casting and its manufacture |
US5778963A (en) * | 1996-08-30 | 1998-07-14 | United Technologies Corporation | Method of core leach |
US5779809A (en) * | 1995-12-26 | 1998-07-14 | General Electric Company | Method of dissolving or leaching ceramic cores in airfoils |
US5915452A (en) * | 1995-06-07 | 1999-06-29 | Howmet Research Corporation | Apparatus for removing cores from castings |
US6474348B1 (en) * | 1999-09-30 | 2002-11-05 | Howmet Research Corporation | CNC core removal from casting passages |
US6755238B1 (en) * | 1999-07-06 | 2004-06-29 | Technology Union Co., Ltd. | Disintegrative core for high pressure casting, method for manufacturing the same, and method for extracting the same |
Family Cites Families (14)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US3166808A (en) * | 1958-08-18 | 1965-01-26 | Pittsburgh Plate Glass Co | Core reinforcement means |
GB2086780B (en) * | 1980-11-12 | 1984-12-12 | Rolls Royce | Core or core part for use in the lost wax casting process |
JPS62296932A (en) * | 1986-06-18 | 1987-12-24 | Ryobi Ltd | Production of breakable core for high pressure casting |
US4989664A (en) | 1988-07-07 | 1991-02-05 | United Technologies Corporation | Core molding composition |
US5273104A (en) | 1991-09-20 | 1993-12-28 | United Technologies Corporation | Process for making cores used in investment casting |
DE4230970C1 (en) | 1992-09-16 | 1994-07-21 | Nolte Markus Dipl Ing Dipl Wir | Process for the production of investment castings |
US5947181A (en) * | 1996-07-10 | 1999-09-07 | General Electric Co. | Composite, internal reinforced ceramic cores and related methods |
US6029736A (en) * | 1997-08-29 | 2000-02-29 | Howmet Research Corporation | Reinforced quartz cores for directional solidification casting processes |
WO2001045876A1 (en) | 1999-12-21 | 2001-06-28 | Howmet Research Corporation | Crack resistant shell mold and method |
WO2001068291A2 (en) | 2000-03-17 | 2001-09-20 | Daniel James Duffey | Investment casting mould |
GB2350810B (en) | 2000-03-17 | 2001-04-25 | Daniel James Duffey | Improvements in and relating to investment casting |
US7243700B2 (en) * | 2005-10-27 | 2007-07-17 | United Technologies Corporation | Method for casting core removal |
US8828214B2 (en) * | 2010-12-30 | 2014-09-09 | Rolls-Royce Corporation | System, method, and apparatus for leaching cast components |
FR2989293B1 (en) * | 2012-04-16 | 2023-06-09 | C T I F Centre Technique Des Ind De La Fonderie | METHOD FOR MANUFACTURING A HOLLOW METALLIC PART BY FOUNDRY |
-
2015
- 2015-06-19 US US14/744,450 patent/US9649687B2/en active Active
- 2015-06-22 EP EP15173080.1A patent/EP2965837B1/en active Active
-
2017
- 2017-03-02 US US15/448,267 patent/US20170173673A1/en not_active Abandoned
Patent Citations (7)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
US5126082A (en) * | 1988-11-30 | 1992-06-30 | Howmet Corporation | Method of making ceramic cores and other articles |
US5915452A (en) * | 1995-06-07 | 1999-06-29 | Howmet Research Corporation | Apparatus for removing cores from castings |
US5779809A (en) * | 1995-12-26 | 1998-07-14 | General Electric Company | Method of dissolving or leaching ceramic cores in airfoils |
JPH09253792A (en) * | 1996-03-25 | 1997-09-30 | Nissan Motor Co Ltd | Paper core for casting and its manufacture |
US5778963A (en) * | 1996-08-30 | 1998-07-14 | United Technologies Corporation | Method of core leach |
US6755238B1 (en) * | 1999-07-06 | 2004-06-29 | Technology Union Co., Ltd. | Disintegrative core for high pressure casting, method for manufacturing the same, and method for extracting the same |
US6474348B1 (en) * | 1999-09-30 | 2002-11-05 | Howmet Research Corporation | CNC core removal from casting passages |
Also Published As
Publication number | Publication date |
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US20150367412A1 (en) | 2015-12-24 |
EP2965837A2 (en) | 2016-01-13 |
EP2965837A3 (en) | 2016-05-25 |
EP2965837B1 (en) | 2022-08-03 |
US9649687B2 (en) | 2017-05-16 |
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