[go: up one dir, main page]

US20060083653A1 - Low porosity powder metallurgy produced components - Google Patents

Low porosity powder metallurgy produced components Download PDF

Info

Publication number
US20060083653A1
US20060083653A1 US10/969,160 US96916004A US2006083653A1 US 20060083653 A1 US20060083653 A1 US 20060083653A1 US 96916004 A US96916004 A US 96916004A US 2006083653 A1 US2006083653 A1 US 2006083653A1
Authority
US
United States
Prior art keywords
component
powder
hot isostatic
heat treated
microstructure
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.)
Abandoned
Application number
US10/969,160
Other languages
English (en)
Inventor
Gopal Das
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.)
RTX Corp
Original Assignee
Individual
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 Individual filed Critical Individual
Priority to US10/969,160 priority Critical patent/US20060083653A1/en
Assigned to UNITED TECHNOLOGIES CORPORATION reassignment UNITED TECHNOLOGIES CORPORATION ASSIGNMENT OF ASSIGNORS INTEREST (SEE DOCUMENT FOR DETAILS). Assignors: DAS, GOPAL
Priority to RU2005125788/02A priority patent/RU2005125788A/ru
Priority to JP2005237029A priority patent/JP2006118038A/ja
Priority to EP05255133A priority patent/EP1649954A3/en
Priority to KR1020050075977A priority patent/KR20060053133A/ko
Publication of US20060083653A1 publication Critical patent/US20060083653A1/en
Abandoned legal-status Critical Current

Links

Images

Classifications

    • 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
    • B22F3/11—Making porous workpieces or articles
    • 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
    • B22F3/02—Compacting only
    • B22F3/04—Compacting only by applying fluid pressure, e.g. by cold isostatic pressing [CIP]
    • B22F3/045—Semi-isostatic pressure
    • 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
    • B22F3/12—Both compacting and sintering
    • B22F3/14—Both compacting and sintering simultaneously
    • B22F3/15—Hot isostatic pressing

Definitions

  • the present invention relates generally to components prepared by powder metallurgy techniques. More specifically, the present invention relates to hot isostatic pressing such components after heat treating to eliminate, or at least minimize or shrink, any porosity therein.
  • Two-phase gamma-TiAl based intermetallic alloys have received considerable attention as potential materials for high-temperature aerospace and automotive applications, particularly as possible replacements for conventional nickel and titanium alloys in gas turbine engines.
  • Such alloys exhibit improved high temperature mechanical properties and improved oxidation resistance as compared to conventional high temperature titanium alloys.
  • Such alloys have good creep resistance and strength at elevated temperatures, and have a lower density than conventional nickel and titanium alloys.
  • Such alloys could be used to make lightweight gas turbine engine components, such as blades, vanes, disks, etc., where higher operating temperatures would allow increased efficiency to be achieved.
  • Powder metallurgy techniques can produce components having greater homogeneity than cast components, and higher strengthener content than conventionally wrought components. Therefore, it may be desirable to use powder metallurgy techniques to form such components.
  • the powder metallurgy techniques currently used to produce such components often create components having porosity therein that is too large or too numerous for many applications. Therefore, it would be desirable to have improved powder metallurgy techniques for producing such components. It would also be desirable to have methods for minimizing the porosity in such components, or at least reducing the porosity therein to an acceptable level. It would be further desirable to have powder metallurgy processing techniques that are useful for a variety of materials.
  • Embodiments of this invention comprise components and methods for forming such components, comprising: providing a powder; creating a preform from the powder; creating a component from the preform; heat treating the component to create a predetermined microstructure therein; and hot isostatic pressing the heat treated component to reduce any porosity therein.
  • Embodiments may further comprise machining the heat treated and hot isostatic pressed component to its final dimensions. Any porosity remaining in the heat treated and hot isostatic pressed component is generally less than about 0.005 inches in size.
  • This invention may be utilized to create gas turbine engine components such as, but not limited to, compressor disks, compressor blades, low pressure turbine blades, and tangential on board injectors.
  • Creating the preform from the powder may comprise hot isostatic pressing the powder at a temperature sufficient to densify the preform and consolidate the powder through bonding thereof.
  • this hot isostatic pressing may occur at about 925-1320° C. and about 15-45 ksi for about 2-10 hours in an argon atmosphere. More specifically, in embodiments, this hot isostatic pressing may occur at about 1260° C. and about 25 ksi for about 4 hours in an argon atmosphere.
  • the component may be created from the preform in numerous ways, such as via extrusion and/or isothermal forging, etc.
  • the component may be created from the preform at a temperature below the alpha transus temperature of the powder so that a near gamma microstructure exists in the preform.
  • Heat treating the component occurs at a time and temperature sufficient to create the desired microstructure in the component.
  • this heat treating may occur at a temperature above the alpha transus temperature of the powder, for example, at about 925-1370° C. for about 2-10 hours, to create a lamellar microstructure in the component. More specifically, in embodiments, this heat treating may occur at about 1354° C. for about 4 hours.
  • the component is hot isostatic pressed at a temperature low enough to prevent significant grain growth from occurring in the component.
  • this temperature may preserve a lamellar microstructure in the component, and be carried out at about 925-1320° C. and about 15-45 ksi for about 2-10 hours. More specifically, in embodiments, this hot isostatic pressing may be carried out at about 1232° C. and about 25 ksi for about 10 hours. After this hot isostatic pressing step, the component will have less or smaller porosity than existed in the component prior to this step.
  • the powder utilized in this invention may comprise any suitable material, including, but not limited to, gamma-TiAl, nickel aluminides, iron aluminides, titanium alloys, and superalloys.
  • the powder may comprise about 44-48 atomic percent aluminum, about 1-2 atomic percent niobium, about 1-2 atomic percent chromium, about 1-2 atomic percent molybdenum, about 0.1-0.2 atomic percent boron, and about 0.1-0.2 atomic percent carbon, the balance substantially titanium.
  • the powder may have an average particle size of about 70 ⁇ m.
  • FIG. 1 is a flowchart showing an exemplary powder metallurgy processing technique that may be utilized in embodiments of this invention to create a component having minimal or no porosity;
  • FIG. 2 is a SEM photomicrograph showing the near gamma microstructure of a disk utilized in embodiments of this invention
  • FIG. 3 is a SEM photomicrograph showing the lamellar microstructure of the disk of FIG. 2 after it was heat treated;
  • FIG. 4 is an ultrasonic C-scan showing a portion of the heat treated disk of FIG. 3 , showing two visible flaws;
  • FIGS. 5 ( a ) and ( b ) are ultrasonic A-scans confirming the presence of the flaws depicted in FIG. 4 ;
  • FIG. 6 is an ultrasonic C-scan showing the same portion of the disk of FIG. 3 after the heat treated disk was hot isostatic pressed, showing no visible indication of the flaws identified in FIGS. 4 and 5 ;
  • FIGS. 7 ( a ) and ( b ) are ultrasonic A-scans confirming the elimination of the flaws identified in FIGS. 4 and 5 ;
  • FIG. 8 is a SEM photomicrograph showing that the lamellar microstructure of the disk of FIG. 3 was maintained after the heat treated disk was hot isostatic pressed.
  • FIGS. 1-8 For the purposes of promoting an understanding of the invention, reference will now be made to some embodiments of this invention as illustrated in FIGS. 1-8 and specific language used to describe the same.
  • the terminology used herein is for the purpose of description, not limitation. Specific structural and functional details disclosed herein are not to be interpreted as limiting, but merely as a basis for teaching one skilled in the art to variously employ the present invention. Any modifications or variations in the depicted structures and methods, and such further applications of the principles of the invention as illustrated herein, as would normally occur to one skilled in the art, are considered to be within the spirit and scope of this invention as described and claimed.
  • This invention relates to improved powder metallurgy processed components that have little or no porosity therein.
  • Powder metallurgy techniques are used to make the components of this invention because such techniques provide microstructural and chemical homogeneities in the consolidated powder, and therefore, also in the final extruded and/or forged components produced therefrom.
  • This invention may be utilized with any material formed from a rapidly solidified powder produced by powder metallurgy in insoluble gas (i.e., argon or helium), and having thermally induced porosity therein in its consolidated and heat treated form.
  • insoluble gas i.e., argon or helium
  • Materials created from powders produced via powder metallurgy in argon or helium gas generally contain thermally induced porosity after heat treatment because argon and helium are both insoluble in metals, and when heat treated at elevated temperatures, these gases become mobile and precipitate as pores (i.e., as thermally induced porosity) in the material.
  • Embodiments of this invention comprise the general powder metallurgy technique 10 shown in FIG. 1 .
  • a powder may be provided 11 .
  • a preform may be created 13 from the powder.
  • a component may be created 15 from the preform.
  • the component may be heat treated 17 to create a desired microstructure therein.
  • the component may be hot isostatic pressed 19 to minimize any porosity therein that is created during heat treatment.
  • the component can then be machined or otherwise formed into its final desired shape, form or dimensions.
  • the powders 11 utilized in this invention may comprise any rapidly solidified, insoluble gas produced powder, such as, but not limited to, gamma-TiAl powders, nickel aluminide powders, iron aluminide powders, titanium alloy powders, any other superalloy powders utilized to make gas turbine engine components, etc.
  • argon gas atomized gamma-TiAl powder may be desirable because it comprises a fine grain microstructure with virtually no chemical segregation.
  • gamma-TiAl components may be used instead of the superalloy components currently used in many gas turbine engine components.
  • gamma titanium aluminides and derivations thereof (i.e., gamma-TiAl, ⁇ -TiAl, etc.) are those compositions that are capable of forming the two-phase ( ⁇ + ⁇ 2 ) microstructure found generally centered around about 44-48 atomic percent aluminum in the binary titanium-aluminum phase diagram. Alloying additions of X, where X may include, but is not limited to, chromium, niobium, molybdenum, boron, and/or carbon, etc., may be provided in embodiments of this invention to modify and/or improve the properties of the alloy for a given application.
  • the preform may be formed 13 from the powder in any suitable manner, such as, for example, by hot isostatic pressing, hot die compaction, etc.
  • the powder may be canned and hot isostatic pressed at a temperature sufficient to densify the preform and consolidate the powder through bonding thereof. Hot isostatic pressing the powder in this manner allows the powder grains to connect metallically and/or to sinter together.
  • the preform should have a near gamma microstructure if the hot isostatic pressing is performed below the alpha transus temperature (T ⁇ ) of the powder.
  • the component can be created 15 therefrom in any suitable manner, such as, for example, by forging, extrusion, and/or by a combination of extrusion and then forging, etc.
  • the preform may be isothermally forged to create a desired component, such as a disk.
  • the extrusion and/or isothermal forging are typically carried out at a temperature in the ( ⁇ + ⁇ ) phase field of the Ti—Al phase diagram, which is well below T ⁇ for this material. Therefore, gamma-TiAl components should have a near gamma microstructure after they are formed.
  • the extrusion and/or isothermal forging may be carried out at temperatures as high as about 1023° C. or higher.
  • the component can be heat treated 17 to create the desired microstructure therein. Since fully lamellar microstructures are strong and crack resistant, they are desirable in many applications.
  • a crack resistant lamellar microstructure can be achieved in gamma-TiAl components by heat treating the component at a temperature above the T ⁇ of the component alloy. In other embodiments (i.e., nickel aluminides, iron aluminides, other titanium alloys and other superalloys), heat treating at temperatures of about 1000-1200° C. for about 2-4 hours may be used to create a desirable microstructure in the components.
  • Such elevated temperature heat treatment often leaves behind cavities in the component, which can be confirmed in various manners, such as, for example, by ultrasonic scanning, x-ray radiography, serial sectioning, etc.
  • porosity may be thermally induced porosity that is created by the argon or other insoluble gas that is entrapped in the powder, which agglomerates in the form of cavities/pores during heat treatment. This is an undesirable condition known as thermally induced porosity. Regardless of the mechanism of formation, this porosity may be much larger than acceptable for many components.
  • the porosity may be associated with grain boundaries, which may reduce the low cycle fatigue properties of the final component by serving as preferential sites for crack initiation. Therefore, this porosity must be eliminated, or at least be reduced to an acceptable level, in order for powder metallurgy techniques to be acceptably utilized for forming many components.
  • hot isostatic pressing 19 the component after heat treating 17 may eliminate the porosity therein, or at least reduce the porosity therein to an acceptable level.
  • Hot isostatic pressing can eliminate internal voids and microporosity in a component through a combination of plastic deformation, creep and diffusion, thereby producing a denser component.
  • This hot isostatic pressing step should have minimal effect on the microstructure, other than decreasing the amount or size of porosity therein.
  • a simple calculation may be done to show whether or not the compressive creep strain that is developed during this hot isostatic pressing step is enough to heal the porosity therein sufficiently to make the component acceptable for use for a given application.
  • ultrasonic inspection may be utilized to verify that any porosity remaining in the component is acceptable.
  • the component Once the component is heat treated and hot isostatic pressed, it may be machined or otherwise formed to its desired final dimensions, if necessary.
  • the fully lamellar microstructure of the gamma-TiAl components should be maintained if this additional processing step is carried out at a temperature below the T ⁇ of the component alloy.
  • the powder metallurgy processing techniques of this invention may be utilized to make a variety of components, such as, for example, gas turbine engine components (i.e., compressor disks, compressor blades, low pressure turbine blades, tangential on board injectors, etc.) or any other components that may be exposed to high mechanical loads at high temperatures.
  • gas turbine engine components i.e., compressor disks, compressor blades, low pressure turbine blades, tangential on board injectors, etc.
  • any other components that may be exposed to high mechanical loads at high temperatures.
  • An exemplary non-limiting sample gamma-TiAl disk was made and evaluated to verify this invention.
  • This sample was prepared utilizing argon gas atomized gamma-TiAl powder 11 having a nominal composition, in atomic percent, of Ti-46Al-3.7(Nb,Cr,Mo)-0.4(B,C) and having an average particle size of about 70 ⁇ m.
  • a preform was created 13 by canning and hot isostatic pressing this powder at about 1260° C. and about 25 ksi for about 4 hours in an argon atmosphere. Once the preform was consolidated, the preform was isothermally forged 15 into a disk in a two-step operation in the ( ⁇ + ⁇ ) phase field at about 1177° C.
  • the disk had a near gamma microstructure, as shown in FIG. 2 .
  • the disk was then heat treated 17 at about 1354° C. for about 4 hours under vacuum to create a fully lamellar microstructure comprising alternating platelets of ⁇ -TiAl phase and ⁇ 2 -Ti 3 Al with an average lamellar grain size of about 250 ⁇ m, as shown in FIG. 3 .
  • gamma-TiAl having a duplex microstructure provides better elongation and strength properties
  • gamma-TiAl having a lamellar microstructure provides better creep resistance, toughness, and crack resistance.
  • Ultrasonic scans and serial sectioning indicated that a small amount of cavities/pores 50 , 55 existed in this heat treated disk, as shown in FIG. 4 .
  • ultrasonic scans confirmed the presence of this porosity 50 , 55 .
  • This porosity 50 , 55 which had diameters of about 0.013′′ and 0.019′′ respectively, was much larger than acceptable for many components, such as for rotating compressor disks used in gas turbine engines. Therefore, further processing was undertaken in an attempt to eliminate this porosity 50 , 55 .
  • the heat treated disk was hot isostatic pressed 19 at about 1232° C.
  • this invention provides improved powder metallurgy processing techniques for producing components having little or no porosity therein.
  • these techniques can be used with a variety of materials to produce components that have good mechanical properties at elevated temperatures. These techniques may be utilized to make gas turbine engine components and other components that are subjected to high mechanical loads at high temperatures. Many other embodiments and advantages will be apparent to those skilled in the relevant art.

Landscapes

  • Engineering & Computer Science (AREA)
  • Manufacturing & Machinery (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Powder Metallurgy (AREA)
US10/969,160 2004-10-20 2004-10-20 Low porosity powder metallurgy produced components Abandoned US20060083653A1 (en)

Priority Applications (5)

Application Number Priority Date Filing Date Title
US10/969,160 US20060083653A1 (en) 2004-10-20 2004-10-20 Low porosity powder metallurgy produced components
RU2005125788/02A RU2005125788A (ru) 2004-10-20 2005-08-15 Способ изготовления компонента (варианты) и компонент низкой пористости, изготовленный данным способом
JP2005237029A JP2006118038A (ja) 2004-10-20 2005-08-18 粉末冶金による部材形成方法
EP05255133A EP1649954A3 (en) 2004-10-20 2005-08-19 Low porosity powder metallurgy produced components
KR1020050075977A KR20060053133A (ko) 2004-10-20 2005-08-19 저다공 분말 야금 생산 부품

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US10/969,160 US20060083653A1 (en) 2004-10-20 2004-10-20 Low porosity powder metallurgy produced components

Publications (1)

Publication Number Publication Date
US20060083653A1 true US20060083653A1 (en) 2006-04-20

Family

ID=35445832

Family Applications (1)

Application Number Title Priority Date Filing Date
US10/969,160 Abandoned US20060083653A1 (en) 2004-10-20 2004-10-20 Low porosity powder metallurgy produced components

Country Status (5)

Country Link
US (1) US20060083653A1 (ja)
EP (1) EP1649954A3 (ja)
JP (1) JP2006118038A (ja)
KR (1) KR20060053133A (ja)
RU (1) RU2005125788A (ja)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102776413A (zh) * 2012-07-27 2012-11-14 中国航空工业集团公司北京航空材料研究院 一种新型钛基高温合金的制备方法
US20130224049A1 (en) * 2012-02-29 2013-08-29 Frederick M. Schwarz Lightweight fan driving turbine
US8740561B2 (en) 2010-05-18 2014-06-03 Nuovo Pignone S.P.A. Jacket impeller with functional graded material and method
WO2014149292A1 (en) * 2013-03-15 2014-09-25 United Technologies Corporation Titanium aluminide turbine exhaust structure
US20140369846A1 (en) * 2011-09-15 2014-12-18 Sandvik Intellectual Property Ab Erosion resistant impeller vane made of metallic laminate
US20160059312A1 (en) * 2014-09-01 2016-03-03 MTU Aero Engines AG PRODUCTION PROCESS FOR TiAl COMPONENTS
CN106244853A (zh) * 2016-08-30 2016-12-21 南京赛达机械制造有限公司 一种防水蚀钛合金汽轮机叶片
CN113664199A (zh) * 2021-08-20 2021-11-19 西安欧中材料科技有限公司 航空发动机涡轮叶片热等静压近净成型方法

Families Citing this family (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
KR100757258B1 (ko) * 2006-10-31 2007-09-10 한국전력공사 고온등압압축-열처리 일괄공정에 의한 가스터빈용 니켈계초합금 부품의 제조방법 및 그 부품
KR101312317B1 (ko) * 2011-11-16 2013-09-27 국방과학연구소 이종 특성을 가진 부재들을 포함하는 일체형 부품 및 그 제조 방법
US9120151B2 (en) * 2012-08-01 2015-09-01 Honeywell International Inc. Methods for manufacturing titanium aluminide components from articles formed by consolidation processes
DE102015103422B3 (de) 2015-03-09 2016-07-14 LEISTRITZ Turbinentechnik GmbH Verfahren zur Herstellung eines hochbelastbaren Bauteils aus einer Alpha+Gamma-Titanaluminid-Legierung für Kolbenmaschinen und Gasturbinen, insbesondere Flugtriebwerke
JP6792837B2 (ja) * 2016-02-17 2020-12-02 国立大学法人大阪大学 チタン‐アルミニウム合金
CN108380893B (zh) * 2018-03-28 2020-11-03 西北工业大学 TiAl系金属间化合物圆环热等静压扩散连接方法

Citations (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4081295A (en) * 1977-06-02 1978-03-28 United Technologies Corporation Fabricating process for high strength, low ductility nickel base alloys
US4769087A (en) * 1986-06-02 1988-09-06 United Technologies Corporation Nickel base superalloy articles and method for making
US4981528A (en) * 1987-09-16 1991-01-01 Rockwell International Corporation Hot isostatic pressing of single crystal superalloy articles
US5000910A (en) * 1989-01-24 1991-03-19 Masaharu Tokizane Method of manufacturing intermetallic compound
US5032353A (en) * 1989-10-27 1991-07-16 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Sintering method for producing structural components of an intermetallic compound
US5098469A (en) * 1991-09-12 1992-03-24 General Motors Corporation Powder metal process for producing multiphase NI-AL-TI intermetallic alloys
US5284620A (en) * 1990-12-11 1994-02-08 Howmet Corporation Investment casting a titanium aluminide article having net or near-net shape
US5395699A (en) * 1992-06-13 1995-03-07 Asea Brown Boveri Ltd. Component, in particular turbine blade which can be exposed to high temperatures, and method of producing said component
US5424027A (en) * 1993-12-06 1995-06-13 The United States Of America As Represented By The Secretary Of The Air Force Method to produce hot-worked gamma titanium aluminide articles
US5580665A (en) * 1992-11-09 1996-12-03 Nhk Spring Co., Ltd. Article made of TI-AL intermetallic compound, and method for fabricating the same
US5768679A (en) * 1992-11-09 1998-06-16 Nhk Spring R & D Center Inc. Article made of a Ti-Al intermetallic compound
US5820700A (en) * 1993-06-10 1998-10-13 United Technologies Corporation Nickel base superalloy columnar grain and equiaxed materials with improved performance in hydrogen and air
US5823243A (en) * 1996-12-31 1998-10-20 General Electric Company Low-porosity gamma titanium aluminide cast articles and their preparation
US6551372B1 (en) * 1999-09-17 2003-04-22 Rolls-Royce Corporation High performance wrought powder metal articles and method of manufacture

Family Cites Families (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPH05141213A (ja) * 1991-11-18 1993-06-08 Sumitomo Light Metal Ind Ltd 内燃機関用吸・排気バルブ

Patent Citations (15)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4081295A (en) * 1977-06-02 1978-03-28 United Technologies Corporation Fabricating process for high strength, low ductility nickel base alloys
US4769087A (en) * 1986-06-02 1988-09-06 United Technologies Corporation Nickel base superalloy articles and method for making
US4981528A (en) * 1987-09-16 1991-01-01 Rockwell International Corporation Hot isostatic pressing of single crystal superalloy articles
US5000910A (en) * 1989-01-24 1991-03-19 Masaharu Tokizane Method of manufacturing intermetallic compound
US5032353A (en) * 1989-10-27 1991-07-16 Mtu Motoren-Und Turbinen-Union Muenchen Gmbh Sintering method for producing structural components of an intermetallic compound
US5284620A (en) * 1990-12-11 1994-02-08 Howmet Corporation Investment casting a titanium aluminide article having net or near-net shape
US5098469A (en) * 1991-09-12 1992-03-24 General Motors Corporation Powder metal process for producing multiphase NI-AL-TI intermetallic alloys
US5395699A (en) * 1992-06-13 1995-03-07 Asea Brown Boveri Ltd. Component, in particular turbine blade which can be exposed to high temperatures, and method of producing said component
US5580665A (en) * 1992-11-09 1996-12-03 Nhk Spring Co., Ltd. Article made of TI-AL intermetallic compound, and method for fabricating the same
US5701575A (en) * 1992-11-09 1997-12-23 Nhk Spring Co., Ltd. Article made of a Ti-Al intermetallic compound, and method for fabrication of same
US5768679A (en) * 1992-11-09 1998-06-16 Nhk Spring R & D Center Inc. Article made of a Ti-Al intermetallic compound
US5820700A (en) * 1993-06-10 1998-10-13 United Technologies Corporation Nickel base superalloy columnar grain and equiaxed materials with improved performance in hydrogen and air
US5424027A (en) * 1993-12-06 1995-06-13 The United States Of America As Represented By The Secretary Of The Air Force Method to produce hot-worked gamma titanium aluminide articles
US5823243A (en) * 1996-12-31 1998-10-20 General Electric Company Low-porosity gamma titanium aluminide cast articles and their preparation
US6551372B1 (en) * 1999-09-17 2003-04-22 Rolls-Royce Corporation High performance wrought powder metal articles and method of manufacture

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8740561B2 (en) 2010-05-18 2014-06-03 Nuovo Pignone S.P.A. Jacket impeller with functional graded material and method
US20140369846A1 (en) * 2011-09-15 2014-12-18 Sandvik Intellectual Property Ab Erosion resistant impeller vane made of metallic laminate
US20130224049A1 (en) * 2012-02-29 2013-08-29 Frederick M. Schwarz Lightweight fan driving turbine
US10309232B2 (en) * 2012-02-29 2019-06-04 United Technologies Corporation Gas turbine engine with stage dependent material selection for blades and disk
CN102776413A (zh) * 2012-07-27 2012-11-14 中国航空工业集团公司北京航空材料研究院 一种新型钛基高温合金的制备方法
WO2014149292A1 (en) * 2013-03-15 2014-09-25 United Technologies Corporation Titanium aluminide turbine exhaust structure
US20160059312A1 (en) * 2014-09-01 2016-03-03 MTU Aero Engines AG PRODUCTION PROCESS FOR TiAl COMPONENTS
US10029309B2 (en) * 2014-09-01 2018-07-24 MTU Aero Engines AG Production process for TiAl components
CN106244853A (zh) * 2016-08-30 2016-12-21 南京赛达机械制造有限公司 一种防水蚀钛合金汽轮机叶片
CN113664199A (zh) * 2021-08-20 2021-11-19 西安欧中材料科技有限公司 航空发动机涡轮叶片热等静压近净成型方法

Also Published As

Publication number Publication date
JP2006118038A (ja) 2006-05-11
KR20060053133A (ko) 2006-05-19
EP1649954A3 (en) 2006-10-11
EP1649954A2 (en) 2006-04-26
RU2005125788A (ru) 2007-02-20

Similar Documents

Publication Publication Date Title
Sachdev et al. Titanium for automotive applications: challenges and opportunities in materials and processing
Clemens et al. Processing and applications of intermetallic γ‐TiAl‐based alloys
Chen et al. Development of Ti2AlNb alloys: opportunities and challenges
EP1666618B1 (en) Ni based superalloy and its use as gas turbine disks, shafts and impellers
Liu et al. Design of powder metallurgy titanium alloys and composites
Clemens Intermetallic γ-TiAl Based Alloy Sheet Materials-—Processing and Mechanical Properties
US20060083653A1 (en) Low porosity powder metallurgy produced components
US10309229B2 (en) Nickel based alloy composition
CA2496093C (en) Process for producing components or semi-finished products which contain intermetallic titanium aluminide alloys, and components producible by the process
KR20160033096A (ko) 티타늄-알루미늄 합금 부품 제조 방법
JP4409409B2 (ja) Ｎｉ−Ｆｅ基超合金とその製造法及びガスタービン
Clemens et al. Advanced intermetallic titanium aluminides
KR20220048789A (ko) 고온 경도가 우수한 하이엔트로피 합금
Bambach et al. Isothermal forging of titanium aluminides without beta-phase—Using non-equilibrium phases produced by spark plasma sintering for improved hot working behavior
JP2017145501A (ja) チタン‐アルミニウム合金
JP2007031836A (ja) タービンエンジン用の粉末金属回転構成部品及びその処理方法
JP5645054B2 (ja) アニーリングツインを含有するニッケル基耐熱超合金と耐熱超合金部材
Clemens et al. Development status, applications and perspectives of advanced intermetallic titanium aluminides
US20160138423A1 (en) Titanium-aluminide components
WO2017123186A1 (en) Tial-based alloys having improved creep strength by strengthening of gamma phase
EP2283952A2 (en) Powder metal mold
Schwartz Emerging Engineering Materials: esign, Processes and Applications
Chesnutt Titanium aluminides for aerospace applications
Clemens et al. Advanced β-solidifying titanium aluminides–development status and perspectives
TWI732729B (zh) 鎳基超合金及其材料

Legal Events

Date Code Title Description
AS Assignment

Owner name: UNITED TECHNOLOGIES CORPORATION, CONNECTICUT

Free format text: ASSIGNMENT OF ASSIGNORS INTEREST;ASSIGNOR:DAS, GOPAL;REEL/FRAME:015941/0156

Effective date: 20041018

STCB Information on status: application discontinuation

Free format text: ABANDONED -- FAILURE TO RESPOND TO AN OFFICE ACTION