US3741821A - Processing for integral gas turbine disc/blade component - Google Patents

Processing for integral gas turbine disc/blade component Download PDF

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Publication number
US3741821A
US3741821A US00141529A US3741821DA US3741821A US 3741821 A US3741821 A US 3741821A US 00141529 A US00141529 A US 00141529A US 3741821D A US3741821D A US 3741821DA US 3741821 A US3741821 A US 3741821A
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US
United States
Prior art keywords
component
heat
blade
disc
temperature
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.)
Expired - Lifetime
Application number
US00141529A
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English (en)
Inventor
R Athey
J Moore
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RTX Corp
Original Assignee
United Aircraft Corp
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Filing date
Publication date
Application filed by United Aircraft Corp filed Critical United Aircraft Corp
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Publication of US3741821A publication Critical patent/US3741821A/en
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    • C—CHEMISTRY; METALLURGY
    • C22—METALLURGY; FERROUS OR NON-FERROUS ALLOYS; TREATMENT OF ALLOYS OR NON-FERROUS METALS
    • C22F—CHANGING THE PHYSICAL STRUCTURE OF NON-FERROUS METALS AND NON-FERROUS ALLOYS
    • C22F1/00—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working
    • C22F1/10—Changing the physical structure of non-ferrous metals or alloys by heat treatment or by hot or cold working of nickel or cobalt or alloys based thereon
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T428/00—Stock material or miscellaneous articles
    • Y10T428/12—All metal or with adjacent metals
    • Y10T428/12493—Composite; i.e., plural, adjacent, spatially distinct metal components [e.g., layers, joint, etc.]
    • Y10T428/12736—Al-base component
    • Y10T428/1275—Next to Group VIII or IB metal-base component

Definitions

  • the pesent invention relates in general to the processing of age-hardenable alloy components.
  • the materials being forged are, by specific thermomechanical procedures, provided in a temporary condition of low strength and high ductility, which is maintained during forging. Subsequent to the forging operation, the forging is heat treated to restore the alloy to a high strength condition.
  • a particular component so processed is simply heat treated prior to use to optimize the alloy microstructure for the particular set of mechanical properties desired, for example, for maximum rupture strength or creep resistance.
  • some components as for example integral disc/:blade units, dilferent properties are required in the blade and disc areas. Accordingly, differing heat treatments are required in the respective areas of such components to provide the optimum overall properties.
  • the present invention contemplates processing for wrought integral disc/ blade components formed from the age-hardenable alloys whereby optimum mechanical properties are provided in respective areas thereof.
  • means are provided for heat treating the blade area of such components under one set of temperature conditions and heat treating the disc area under a different set of conditions.
  • FIG. l is a drawing of an integral disc/ blade component.
  • FIG. 2 illustrates apparatus for selectively heating the blade area of an integral disc/blade component utilizing an induction coil peripherally surrounding the component.
  • FIG. 3 is a View of the apparatus of FIG. 2 taken along the line 3 3.
  • FIG. 4 is a view of apparatus for selectively heating the 3,741,821 Patented June 26, 1973 ice blade area of an integral disc/blade component utilizing a plurality of induction coils of generally U-shaped crosssection.
  • FIG. 5 is a view taken along line 5-5 of FIG. 4.
  • the requisite differential heat treatment required for the integral disc/blade component 2 may conveniently be provided utilizing induction heating apparatus of the type shown in the drawing in one stage of solution heat treatment.
  • the integral disc/blade component 2 is mounted for rotation within a circular induction coil 4.
  • the induction coil is of conventional construction comprising a plurality of turns of suitable inductor such as copper closely surrounding the periphery of the component 2.
  • suitable inductor such as copper closely surrounding the periphery of the component 2.
  • the blades 12 of the disc/blade component are rapidly brought to a high solution temperature.
  • suitable induction heating equipment is available on the market. In the case of a component formed from Alloy A, the blades are brought to a temperature of about 2125 F.
  • FIGS. 2 and 3 heating proceeds radially inward.
  • this apparatus is most suitable for blades of short length.
  • the apparatus shown in FIGS. 4 and 5 is preferred.
  • the component is slowly rotated within the induction coil.
  • induction heating units 14 of generally U-shaped cross-section provide the heat source for the solutioning of the blading.
  • the legs 16 and 18 of the U-shaped (in cross-section) induction heating units are of suflicient length to essentially encompass the entire length of the blades.
  • the processing of the integral disc/blade component is conducted to provide a high solution heat treatment and grain growth in the blade portion of the component and a lower solution treatment and finer-grained microstructure in the disc portion 20 of the component. Subsequently heat treatments for stabilization or aging correspond to that normally associated with heat treatment of the disc portion.
  • suitable coatings may be applied to the component or sections thereof prior to or during a portion of the heat treatment cycle.
  • suitable coatings may be applied to the component or sections thereof prior to or during a portion of the heat treatment cycle.
  • 4 3,102,044 may be applied to the solutioned blades with the requisite coating/ substrate diffusion being provided by the heat treatment for the disc portion.
  • alloy B This alloy is hereinafter identified as Alloy B.
  • preferred processing according to this invention is as follows:
  • the agehardenable alloy is a nickel-base superalloy.

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  • Chemical & Material Sciences (AREA)
  • Physics & Mathematics (AREA)
  • Thermal Sciences (AREA)
  • Crystallography & Structural Chemistry (AREA)
  • Engineering & Computer Science (AREA)
  • Materials Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Metallurgy (AREA)
  • Organic Chemistry (AREA)
  • Heat Treatment Of Articles (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Heat Treatment Of Nonferrous Metals Or Alloys (AREA)
US00141529A 1971-05-10 1971-05-10 Processing for integral gas turbine disc/blade component Expired - Lifetime US3741821A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US14152971A 1971-05-10 1971-05-10

Publications (1)

Publication Number Publication Date
US3741821A true US3741821A (en) 1973-06-26

Family

ID=22496082

Family Applications (1)

Application Number Title Priority Date Filing Date
US00141529A Expired - Lifetime US3741821A (en) 1971-05-10 1971-05-10 Processing for integral gas turbine disc/blade component

Country Status (10)

Country Link
US (1) US3741821A (OSRAM)
JP (1) JPS5632390B1 (OSRAM)
CA (1) CA959740A (OSRAM)
CH (1) CH544813A (OSRAM)
DE (1) DE2220064C3 (OSRAM)
FR (1) FR2139217A5 (OSRAM)
GB (1) GB1333354A (OSRAM)
IL (1) IL38707A (OSRAM)
IT (1) IT951408B (OSRAM)
SE (1) SE383534B (OSRAM)

Cited By (19)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3898109A (en) * 1973-09-06 1975-08-05 Int Nickel Co Heat treatment of nickel-chromium-cobalt base alloys
US4168182A (en) * 1975-11-11 1979-09-18 Motoren- Und Turbinen-Union Munchen Gmbh Method of producing shaped metallic parts
DE2949673A1 (de) * 1978-12-15 1980-06-26 Westinghouse Electric Corp Verfahren zur herstellung einer zusammengesetzten kornstruktur in gegenstaenden aus nickellegierung
FR2480786A1 (fr) * 1980-04-21 1981-10-23 Gen Electric Procede de fabrication d'une piece coulee a structure granulaire composite et piece obtenue
US4401480A (en) * 1978-12-15 1983-08-30 Westinghouse Electric Corp. Method of selective grain growth in nickel-base superalloys by controlled boron diffusion
EP0170348A1 (en) * 1984-05-07 1986-02-05 Eaton Corporation Solution heat treated engine poppet valves
US4654091A (en) * 1980-12-10 1987-03-31 United Technologies Corporation Elimination of quench cracking in superalloy disks
US4729802A (en) * 1986-01-16 1988-03-08 J. I. Case Company Opener-disk heat-treating process and product
US4813470A (en) * 1987-11-05 1989-03-21 Allied-Signal Inc. Casting turbine components with integral airfoils
US4838069A (en) * 1988-02-12 1989-06-13 United Technologies Corporation Apparatus for fabricating integrally bladed rotors
US4841614A (en) * 1988-02-12 1989-06-27 United Technologies Corporation Method for fabricating integrally bladed rotors
US5100050A (en) * 1989-10-04 1992-03-31 General Electric Company Method of manufacturing dual alloy turbine disks
US5189279A (en) * 1991-12-30 1993-02-23 General Electric Company Steam turbine rotor welding
US5326409A (en) * 1987-03-24 1994-07-05 Wyman-Gordon Company System for peripheral differential heat treatemnt to form dual-property workpiece
US5527020A (en) * 1992-03-13 1996-06-18 General Electric Company Differentially heat treated article, and apparatus and process for the manufacture thereof
US5551999A (en) * 1984-04-23 1996-09-03 United Technologies Corporation Cyclic recovery heat treatment
RU2119842C1 (ru) * 1996-06-21 1998-10-10 Институт проблем сверхпластичности металлов РАН Способ изготовления осесимметричных деталей и способ получения заготовок для его осуществления (варианты)
WO2017077248A1 (fr) 2015-11-06 2017-05-11 Safran Dispositif de generation d'une microstructure a gradient de structure sur une piece axisymetrique
CN108031779A (zh) * 2017-11-29 2018-05-15 无锡透平叶片有限公司 一种透平叶片及其制备方法

Families Citing this family (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP0365543B1 (en) * 1987-03-24 1993-10-27 Wyman-Gordon Company System for peripheral differential heat treatment to form dual-property workpieces
US4820358A (en) * 1987-04-01 1989-04-11 General Electric Company Method of making high strength superalloy components with graded properties
US7553384B2 (en) * 2006-01-25 2009-06-30 General Electric Company Local heat treatment for improved fatigue resistance in turbine components
WO2011057661A1 (de) * 2009-11-11 2011-05-19 Siemens Aktiengesellschaft Bauteil mit bereichen unterschiedlicher duktilität und verfahren zur herstellung eines bauteils
PL397937A1 (pl) 2012-01-30 2013-08-05 General Electric Company Uklad indukcyjnego wyzarzania odpuszczajacego dla turbiny

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3898109A (en) * 1973-09-06 1975-08-05 Int Nickel Co Heat treatment of nickel-chromium-cobalt base alloys
US4168182A (en) * 1975-11-11 1979-09-18 Motoren- Und Turbinen-Union Munchen Gmbh Method of producing shaped metallic parts
DE2949673A1 (de) * 1978-12-15 1980-06-26 Westinghouse Electric Corp Verfahren zur herstellung einer zusammengesetzten kornstruktur in gegenstaenden aus nickellegierung
US4401480A (en) * 1978-12-15 1983-08-30 Westinghouse Electric Corp. Method of selective grain growth in nickel-base superalloys by controlled boron diffusion
FR2480786A1 (fr) * 1980-04-21 1981-10-23 Gen Electric Procede de fabrication d'une piece coulee a structure granulaire composite et piece obtenue
US4654091A (en) * 1980-12-10 1987-03-31 United Technologies Corporation Elimination of quench cracking in superalloy disks
US5551999A (en) * 1984-04-23 1996-09-03 United Technologies Corporation Cyclic recovery heat treatment
EP0170348A1 (en) * 1984-05-07 1986-02-05 Eaton Corporation Solution heat treated engine poppet valves
US4729802A (en) * 1986-01-16 1988-03-08 J. I. Case Company Opener-disk heat-treating process and product
US5326409A (en) * 1987-03-24 1994-07-05 Wyman-Gordon Company System for peripheral differential heat treatemnt to form dual-property workpiece
US4813470A (en) * 1987-11-05 1989-03-21 Allied-Signal Inc. Casting turbine components with integral airfoils
US4838069A (en) * 1988-02-12 1989-06-13 United Technologies Corporation Apparatus for fabricating integrally bladed rotors
US4841614A (en) * 1988-02-12 1989-06-27 United Technologies Corporation Method for fabricating integrally bladed rotors
US5100050A (en) * 1989-10-04 1992-03-31 General Electric Company Method of manufacturing dual alloy turbine disks
US5189279A (en) * 1991-12-30 1993-02-23 General Electric Company Steam turbine rotor welding
US5527020A (en) * 1992-03-13 1996-06-18 General Electric Company Differentially heat treated article, and apparatus and process for the manufacture thereof
RU2119842C1 (ru) * 1996-06-21 1998-10-10 Институт проблем сверхпластичности металлов РАН Способ изготовления осесимметричных деталей и способ получения заготовок для его осуществления (варианты)
WO2017077248A1 (fr) 2015-11-06 2017-05-11 Safran Dispositif de generation d'une microstructure a gradient de structure sur une piece axisymetrique
US10837069B2 (en) 2015-11-06 2020-11-17 Safran Device for generating a microstructure with a structural gradient in an axisymmetric part
CN108031779A (zh) * 2017-11-29 2018-05-15 无锡透平叶片有限公司 一种透平叶片及其制备方法

Also Published As

Publication number Publication date
DE2220064C3 (de) 1975-06-12
DE2220064A1 (de) 1972-12-07
FR2139217A5 (OSRAM) 1973-01-05
SE383534B (sv) 1976-03-15
DE2220064B2 (de) 1974-10-24
JPS5632390B1 (OSRAM) 1981-07-27
IT951408B (it) 1973-06-30
GB1333354A (en) 1973-10-10
IL38707A (en) 1975-03-13
IL38707A0 (en) 1972-07-26
CH544813A (fr) 1973-11-30
CA959740A (en) 1974-12-24

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