EP2018917A1 - Procédés de moulage à injection pour fabriquer des composants capables de transporter des liquides - Google Patents

Procédés de moulage à injection pour fabriquer des composants capables de transporter des liquides Download PDF

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Publication number
EP2018917A1
EP2018917A1 EP08160360A EP08160360A EP2018917A1 EP 2018917 A1 EP2018917 A1 EP 2018917A1 EP 08160360 A EP08160360 A EP 08160360A EP 08160360 A EP08160360 A EP 08160360A EP 2018917 A1 EP2018917 A1 EP 2018917A1
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EP
European Patent Office
Prior art keywords
temperature
component
holding
minute
hours
Prior art date
Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
Withdrawn
Application number
EP08160360A
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German (de)
English (en)
Inventor
Marie Ann Mcmasters
David Edwin Budinger
Daniel L. Durstock
Current Assignee (The listed assignees may be inaccurate. Google has not performed a legal analysis and makes no representation or warranty as to the accuracy of the list.)
General Electric Co
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General Electric Co
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by General Electric Co filed Critical General Electric Co
Publication of EP2018917A1 publication Critical patent/EP2018917A1/fr
Withdrawn legal-status Critical Current

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/22—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip
    • B22F3/225—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces for producing castings from a slip by injection molding
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F3/00—Manufacture of workpieces or articles from metallic powder characterised by the manner of compacting or sintering; Apparatus specially adapted therefor ; Presses and furnaces
    • B22F3/10—Sintering only
    • B22F3/1017—Multiple heating or additional steps
    • B22F3/1021—Removal of binder or filler
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B22—CASTING; POWDER METALLURGY
    • B22F—WORKING METALLIC POWDER; MANUFACTURE OF ARTICLES FROM METALLIC POWDER; MAKING METALLIC POWDER; APPARATUS OR DEVICES SPECIALLY ADAPTED FOR METALLIC POWDER
    • B22F2998/00—Supplementary information concerning processes or compositions relating to powder metallurgy
    • B22F2998/10—Processes characterised by the sequence of their steps

Definitions

  • Embodiments described herein generally relate to methods of manufacturing components capable of transporting liquids. More specifically, embodiments described herein relate generally to metal injection molded components capable of transporting jet fuel.
  • gas turbine engines such as aircraft engines
  • air is drawn into the front of the engine and then compressed by a shaft-mounted compressor.
  • the compressed air is then transported to the combustor while fuel is concurrently transported from a fuel supply by a fuel distribution system to the combustor.
  • the fuel is introduced at the front end of a burner in a highly atomized spray from a fuel nozzle.
  • Compressed air flows in around the fuel nozzle and mixes with the fuel to form a fuel-air mixture, which is ignited by the burner.
  • the temperature of the ignited fuel-air mixture can reach an excess of 3500°F (1920°C). It is therefore important that the fuel supply and distribution systems are substantially leak free, as a leak in the fuel supply or distribution systems could be catastrophic.
  • macro-laminate technology generally involves shaping and coupling plies of material together using a series of bonded joints.
  • Surrounding the macro-laminate may be a variety of components that require numerous braze joints. Due largely to the number of braze joints required to construct fuel nozzles in this manner, the use of macro-laminate technology is not ideal.
  • braze joints can increase the time needed to fabricate such components and can also complicate the fabrication process for any of several reasons, including: the need for an adequate region to allow for braze alloy placement; the need for minimizing unwanted braze alloy flow; the need for an acceptable inspection technique to verify braze quality; and, the necessity of having several braze alloys available in order to prevent the re-melting of previous braze joints.
  • numerous braze joints can result in several braze runs, which can weaken the parent material of the component.
  • the presence of numerous braze joints can undesirably increase the weight and manufacturing cost of the component.
  • Embodiments herein generally relate to methods for manufacturing components capable of transporting a liquid involving providing a mold, placing at least one core made from a core material into the mold, injecting a component material into the mold about the core to produce a green component, heating the green component to burn out the core and produce a brown component, and sintering the brown component to produce a finished component capable of transporting a liquid wherein the finished component is from about 95% to about 99% dense.
  • Embodiments herein also generally relate to methods for manufacturing components capable of transporting a liquid involving providing a mold, placing at least one core made from a core material into the mod, injecting a component material into the mold about the core to produce a green component, heating the green component to burn out the core and produce a brown component, sintering the brown component to produce a finished component capable of transporting a liquid, and hipping the finished component to produce a densified component that is about 99.9% dense.
  • Embodiments herein also generally relate to methods for manufacturing components capable of transporting a liquid involving providing a mold, placing multiple non-linear cores made from a core material selected from the group consisting of stereolithography (SLA)-type resins, polycarbonates, polypropylene, and combinations thereof, into the mold, injecting a component material selected from the group consisting of nickel based alloys, cobalt based alloys, and combinations thereof, into the mold about the cores to produce a green component, heating the green component over a temperature range of from about 150°F (about 65°C) to about 500°F (about 260°C) to burn out the cores and produce a brown component, and sintering the brown component over a temperature range of from about 700°F (about 370°C) to about 2300°F (about 1260°C) to produce a finished component capable of transporting jet fuel wherein the finished component is a fuel nozzle comprising a fuel conduit and a fuel distributor ring and wherein the finished component is from about 9
  • Embodiments described herein generally relate to metal injection molding methods for fabricating components capable of transporting liquids. While embodiments herein may generally focus on methods for making components useful in the transport of jet fuel through the fuel systems of gas turbine engines, it will be understood by those skilled in the art that the description should not be limited to such. Indeed, as the following description explains, the methods described herein may be utilized to produce any component capable of being used to transport a liquid.
  • embodiments set forth herein relate to providing a mold, injecting a component material into the mold to produce a green component, heating the green component to produce a brown component, and sintering the brown component to produce a finished component capable of transporting a liquid.
  • a mold may be provided having the form of the desired finished component.
  • the mold may be any mold suitable for use with metal injection molding processes as set forth in greater detail herein below.
  • the mold may be constructed of steel or other comparable material.
  • the mold can have an internal space corresponding to the external shape of the component being fabricated.
  • At least one core may be placed inside the mold to form a cavity within the finished component.
  • the term "core" means at least one. It will be understood that the embodiments described herein may include more than one core.
  • the core may be fabricated from any core material having a lower melting point than the component material as described herein below to facilitate removal of the core.
  • the core may be fabricated from a core material selected from the group consisting of SLA-type resins, polycarbonates, polypropylene, and combinations thereof.
  • the core may be either linear or non-linear.
  • a component material may then be injected into the mold about the core using conventional injection molding practices, which can typically involve injecting the component material into the mold at a pressure of from about 200 psi to about 400 psi.
  • the mold into which the component material is injected may be heated to a temperature of about 90°C (about 200°F) to facilitate injection and dispersal of the component material in the mold.
  • the component material may comprise any material capable of being injection molded, in one embodiment the component material may be selected from the group consisting of nickel based alloys, cobalt based alloys, and combinations thereof. More specifically, the component material may comprise a metallic powder mixed with from about 3% to about 20% of a binder material, by weight.
  • the component material may comprise about 93% by weight Inconel 718 powder combined with about 7% by weight of a binder material. Any common binder material known to those skilled in the art is acceptable for use herein.
  • the component material can have a consistency that is capable of being injected under pressure into the mold without leaking out of the mold.
  • the component material may be allowed to firm up inside the mold to produce a green component.
  • the time necessary for this set up to occur will vary depending on the particular component material selected.
  • the mold may be pulled and the green component removed. If desired, the green component may be dried and/or cooled to make handling easier.
  • the green component may then be heated to produce a brown component, as well as to burn out any cores present.
  • the resulting brown component will be hardened and will have an internal cavity located where each core had been.
  • it is desirable that the cores are made from a material having a melting point that is lower than the melting point of the component material in order to facilitate burning-out of the cores.
  • the temperature to which the green component can be heated to produce the brown component, and to burn out any cores present may vary depending on the particular component material and core material used. However, in one embodiment, the green component can be heated to a temperature ranging from about 150°F to about 500°F (about 65°C to about 260°C). Core burnout can occur by transporting out several heating steps over the previously set forth temperature range wherein the temperature of the furnace containing the component can be increased by about twenty-five degrees over about five minutes, followed by holding the temperature constant for a defined length of time.
  • core burnout can include the following steps: the furnace can be heated to a temperature of about 300°F (about 148°C) and held constant for about one hour; the temperature can then be raised to about 325°F (about 162°C) over a period of about a five minutes and held constant for about two hours; the temperature can then be raised to about 350°F (about 176°C) over a period of about five minutes and held constant for about two additional hours; the temperature can then be raised to about 375°F (about 190°C) over a period of about five minutes and held constant for about two hours, the temperature can then be raised to about 400°F (about 204°C) over a period of about five minutes and held constant for about two hours during which time the core will start to liquefy and burn out of the component. The temperature can then be raised to about 425°F (about 218°C) over a period of about five minutes and held constant for about six to seven hours. After about six to seven hours, the resulting brown component can be inspected to ensure
  • this heating process can be used to remove any ash remaining in the resulting brown component and/or the air furnace in which the core burnout occurs. More particularly, after completion of the core burnout and while the brown component is still present inside, the furnace can be heated to about 625°F (about 329°C), to burn any residual ash content from within the brown component and the furnace. When satisfied that the core burnout is complete, the furnace can be turned off and the brown component allowed to cool.
  • partial debinding of the component material may occur.
  • at least a portion of the binder material used in the component material is burned out of the green component. Partial debinding provides ease of handling and transport of the resulting brown component from the air furnace to a vacuum furnace, where sintering occurs. It should be noted that complete debinding of the component material generally does not occur until completion of the sintering cycle as explained herein below.
  • Sintering involves heating the brown component to volatilize any remaining binder and densifying the remaining metal particles of the component material together to produce a finished component.
  • sintering can densify the brown component by eliminating the voids created during debinding.
  • sintering can shrink the finished component by about 3% to about 20% when compared to the size of the brown component.
  • sintering may be carried out in a series of cycles over a temperature range of from about 700°F to about 2300°F (about 370°C to about 1260°C). Sintering may be carried out in a vacuum furnace having partial pressure capability. In one embodiment, the furnace may be evacuated and then backfilled with argon or hydrogen gas to a pressure of about 600 microns of Hg. The gas may be intermittently or continuously flowed through the furnace to purge the volatized binder generated throughout the sintering process.
  • the sintering process may be initiated while the furnace is at ambient temperature.
  • the brown component may be placed into the furnace and the furnace heated at a temperature increase of about 5°F (about 2.7°C)/minute until the temperature reaches about 1200°F (about 648°C). Once a temperature of about 1200°F (about 648°C) is reached, it may be held constant for about one hour.
  • the furnace may then be cooled at a rate of about 5°F (about 2.7°C)/minute until a temperature of about 300°F (148°C) is reached. Cooling may be accomplished by, for example, controlled power reduction to the heating elements of the furnace.
  • the furnace may then be heated again at a rate of about 5°F (about 2.7°C)/minute to a temperature of about 1200°F (about 648°C) where it may be held constant for about two hours.
  • the furnace may then be cooled at a rate of about 5°F (about 2.7°C)/minute until a temperature of about 300°F (148°C) is reached.
  • the furnace may then be heated at a rate of about 5°F (about 2.7°C)/minute to a temperature of about 1200°F (about 648°C) where it may be held constant for about two hours.
  • the furnace may be cooled at a rate of about 5°F (about 2.7°C)/minute to a temperature of about 300°F (about 148°C), followed by heating one additional time at a rate of about 10°F (about 5°C)/minute to a temperature of about 1200°F (about 648°C).
  • the furnace may then be allowed to cool to ambient temperature.
  • the chamber of the vacuum furnace may then be evacuated to a pressure of less than about 1 micron of mercury. Heating may then be reinitiated by increasing the temperature at a rate of about 5°F (about 2.7°C)/minute to a temperature of about 1500°F (about 815°C) where it may be held constant for about two hours. The temperature may then be increased to about 2000°F (about 1093°C) at a rate of about 5°F (about 2.7°C)/minute. After holding the temperature constant for about two hours, it may again be increased, this time at a rate of about 35°F (about 19°C)/minute until it reaches a temperature of about 2300°F (about 1260°C).
  • the temperature may be held at this temperature for an additional two hours before being vacuum cooled at a rate of about 10°F (about 5°C)/minute until a temperature of about 2000°F (about 1093°C) is reached. Vacuum cooling may then be continued at an uncontrolled rate until the temperature reaches below about 1200°F (about 648°C), and in one embodiment, until the temperature reaches about 250°F (about 121°C).
  • the resulting finished component is capable of transporting a liquid, which in one embodiment, may be a flammable liquid such as liquid jet fuel. More specifically, sintering densifies the cavities resulting from the burned-out cores and reduces the porosity of the cavity walls to enable the transport of liquids. This reduction of porosity results in a finished component that can be from about 95% to about 99% dense.
  • the term "dense" refers to the percent of the finished component that is non-porous and can be measured using conventional image analysis techniques. For example, the finished component can be cut up and a piece of the finished component can be placed under a microscope. A microscopic photograph of the piece of the finished component can be taken and the area of any voids, or porous areas, present can be calculated with respect to the total area of the piece of the finished component shown in the photograph.
  • pressure may be applied to the finished product using a technique known in the art as Hot Isostatic Pressing, or HIP/"hipping.” More specifically, during hipping, any remaining voids within the finished component resulting from debinding can be removed by heating the finished component to a temperature of from about 2100°F (about 1149°C) to about 2200°F (about 1204°C), and in one embodiment about 2125°F (about 1163°C), under from about 10ksi to about 20ksi argon pressure, and in one embodiment about 15 ksi (about 1055 kgf/cm 2 ) argon pressure, and holding these parameters constant for about four hours.
  • the end result of the hipping process is a densified component that is at least about 99.9% dense.
  • Fuel nozzle 10 may include a fuel conduit supply 12 and a distributor ring 14.
  • fuel conduit supply 12 may comprise at least one pilot cavity 16 and at least one main cavity 18, each fabricated using the previously described cores during the injection molding process.
  • pilot cavity 16 and main cavity 18 may each be generally linear, non-linear, or some combination thereof.
  • main cavity 18 may branch into a main cavity right side 20 and a main cavity left side 22.
  • a distance D of at least about 0.02cm. Spacing the cavities by at least about 0.02cm can help ensure that the cores that form the cavities are adequately surrounded by the component material during fabrication, which can help to prevent leakage in the finished component.
  • Distributor ring 14 which may be operably coupled to at least one pilot cavity 16 and at least one main cavity 18, may have at least one injection post 24 extending outwardly therefrom.
  • distributor ring 14 includes a plurality of injection posts 24, which can help maintain the fuel velocity until the fuel is injected into a mixer cavity where the fuel mixes with air causing combustion.
  • injection post 24 can be integral with distributor ring 14. More specifically, prior to injection molding distributor ring 14 having injection post 24, one or more cores can be suspended within the mold as described previously to account for channels (not shown) within distributor ring 14 and injection post 24. This arrangement allows distributor ring 14 to be molded with integral injection posts 24 rather than the current practice of fabricating the distributor ring and then subsequently attaching one or more injection posts manually.
  • the previously detailed metal injection molding process may be used to separately fabricate fuel conduit supply 12 and distributor ring 14 up through the brown component portion of the process.
  • the brown fuel conduit and the brown distributor ring may then be coupled together by inserting the brown fuel conduit into at least one corresponding inlet 13, shown in FIG. 3 , of the distributor ring prior to carrying out the sintering and optional hipping processes such that the fuel conduit supply 12 and distributor ring 14 are fixed together during fabrication to form fuel nozzle 10.
  • This permanent coupling of fuel conduit supply 12 and distributor ring 14 can eliminate the use of braze joints and reduce the likelihood of leakage that may result therefrom.
  • Distributor ring 14 may also be enclosed by a forward heat shield 26 coupled to an aft heat shield 28 that together can form an insulation gap 30 about distributor ring 14, as shown in FIG. 3 .
  • Forward heat shield 26 and aft heat shield 28 may be constructed from, for example, Inconel 718, and can be fabricated using any of a variety of methods known to those skilled in the art, such as, for example, casting, metal injection molding or other machining method.
  • Heat shields 26, 28 can be brazed together around fuel distributor ring 14. Gap 30 insulates the fuel from the hot air that flows through cavities in fuel nozzle 10, which helps prevent the fuel from getting too hot and coking.
  • Fuel nozzle 10 may additionally comprise at least one pilot injector 32 as shown in FIG. 4 .
  • pilot injector 32 can be operably coupled to the pilot cavity where it can serve as the main fuel supply for ignition of the engine.
  • Pilot injector 32 may generally be a machined part that can be brazed to fuel conduit supply 12.
  • pilot injector 32 can be made from the same material as fuel conduit supply 12.
  • the fuel nozzle may be oriented either axially, as shown in FIG. 5 , or circumferentially as shown in FIG. 6 , in relation to the engine 34 in which it is placed.
  • Axial orientation may be desired to help reduce the weight and size of nozzle 10, however, those skilled in the art will understand that nozzle 10 must have low enough thermal stresses to meet part life requirements.
  • Circumferential orientation may be desired to reduce thermal stresses on nozzle 10. Either orientation is acceptable for use in conjunction with the embodiments set forth herein.

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  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Powder Metallurgy (AREA)
  • Injection Moulding Of Plastics Or The Like (AREA)
EP08160360A 2007-07-15 2008-07-14 Procédés de moulage à injection pour fabriquer des composants capables de transporter des liquides Withdrawn EP2018917A1 (fr)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US11/778,048 US20090014101A1 (en) 2007-07-15 2007-07-15 Injection molding methods for manufacturing components capable of transporting liquids

Publications (1)

Publication Number Publication Date
EP2018917A1 true EP2018917A1 (fr) 2009-01-28

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EP08160360A Withdrawn EP2018917A1 (fr) 2007-07-15 2008-07-14 Procédés de moulage à injection pour fabriquer des composants capables de transporter des liquides

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US (1) US20090014101A1 (fr)
EP (1) EP2018917A1 (fr)
JP (1) JP2009019275A (fr)
CN (1) CN101342593A (fr)
CA (1) CA2636745A1 (fr)
MX (1) MX2008008376A (fr)

Cited By (5)

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Publication number Priority date Publication date Assignee Title
FR2944720A1 (fr) * 2009-04-24 2010-10-29 Snecma Realisation de pieces a cavites en moulage par injection de poudres metalliques
US8991188B2 (en) 2011-01-05 2015-03-31 General Electric Company Fuel nozzle passive purge cap flow
WO2015050987A1 (fr) 2013-10-04 2015-04-09 United Technologies Corporation Âme de gicleur de carburant à fabrication additive pour un moteur à turbine à gaz
EP3245018A1 (fr) * 2015-01-14 2017-11-22 Digital Metal AB Procédé de fabrication additive, procédé de traitement de données d'objet, support de données, processeur de données d'objet et objet fabriqué
US11015808B2 (en) 2011-12-13 2021-05-25 General Electric Company Aerodynamically enhanced premixer with purge slots for reduced emissions

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WO2010115837A1 (fr) * 2009-04-09 2010-10-14 Basf Se Procédé de fabrication d'une roue de turbine pour un turbocompresseur à gaz d'échappement
JP2011143597A (ja) * 2010-01-14 2011-07-28 Ihi Corp 射出成形モールドのための組成物
US20120073303A1 (en) * 2010-09-23 2012-03-29 General Electric Company Metal injection molding process and components formed therewith
JP6403952B2 (ja) * 2013-12-27 2018-10-10 太盛工業株式会社 粉体焼結成形体の製造方法、流体素子の製造方法、粉体焼結成形体及び粉体焼結成形体製造用中子
GB201811899D0 (en) 2018-07-20 2018-09-05 Univ Liverpool Article and method
FR3096912B1 (fr) * 2019-06-07 2021-10-29 Safran Aircraft Engines Procédé de fabrication de pièce de turbomachine par moulage MIM
WO2022242847A1 (fr) * 2021-05-19 2022-11-24 Schunk Sintermetalltechnik Gmbh Procédé de fabrication d'une buse d'imprimante

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Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2944720A1 (fr) * 2009-04-24 2010-10-29 Snecma Realisation de pieces a cavites en moulage par injection de poudres metalliques
US8991188B2 (en) 2011-01-05 2015-03-31 General Electric Company Fuel nozzle passive purge cap flow
US11015808B2 (en) 2011-12-13 2021-05-25 General Electric Company Aerodynamically enhanced premixer with purge slots for reduced emissions
US11421884B2 (en) 2011-12-13 2022-08-23 General Electric Company System for aerodynamically enhanced premixer for reduced emissions
US11421885B2 (en) 2011-12-13 2022-08-23 General Electric Company System for aerodynamically enhanced premixer for reduced emissions
WO2015050987A1 (fr) 2013-10-04 2015-04-09 United Technologies Corporation Âme de gicleur de carburant à fabrication additive pour un moteur à turbine à gaz
EP3052784A4 (fr) * 2013-10-04 2016-08-10 United Technologies Corp Âme de gicleur de carburant à fabrication additive pour un moteur à turbine à gaz
EP3245018A1 (fr) * 2015-01-14 2017-11-22 Digital Metal AB Procédé de fabrication additive, procédé de traitement de données d'objet, support de données, processeur de données d'objet et objet fabriqué

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Publication number Publication date
US20090014101A1 (en) 2009-01-15
JP2009019275A (ja) 2009-01-29
CA2636745A1 (fr) 2009-01-15
MX2008008376A (es) 2009-03-04
CN101342593A (zh) 2009-01-14

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