GB1333354A - Processing for integral gas turbine disc blade components formed from age-hardenable alloys - Google Patents
Processing for integral gas turbine disc blade components formed from age-hardenable alloysInfo
- Publication number
- GB1333354A GB1333354A GB564772A GB564772A GB1333354A GB 1333354 A GB1333354 A GB 1333354A GB 564772 A GB564772 A GB 564772A GB 564772 A GB564772 A GB 564772A GB 1333354 A GB1333354 A GB 1333354A
- Authority
- GB
- United Kingdom
- Prior art keywords
- hours
- component
- air cooling
- followed
- cooling
- 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
Links
Classifications
-
- 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
Abstract
1333354 Heat-treating turbine components UNITED AIRCRAFT CORP 7 Feb 1972 [10 May 1971] 5647/72 Headings C7A and C7N A wrought integral gas turbine blade-disc component is differentially solution treated in two stages in one of which the blade region only is heated to a relatively high temperature to produce a coarse-grained creep-resistant structure while in the other the whole component is heated to a lower temperature to produce in the disc a finegrained fatigue-resistant structure; preferably the local treatment may precede the general but the order may be reversed. The component is then given conventional stabilization and precipitation heat-treatments. As exemplified an alloy containing in percentage by weight C 0À03-0À09 Cr 14-16 Co 16-18 Mo 4À5-5À5 Ti 3À35-3À65 Al 3À85-4À15 B 0À02-0À03 Ni balance is treated by heating the blade region to the 1163- 1204C. followed by air cooling or faster, after which the whole component is held at 1107C. for 4 hours and preferably quenched into a salt bath at 316C. followed by air cooling. It is then given a stabilization treatment at 871C for 8 hours, cooled at not less than air cooling rate, heated to 982C. for 4 hours and again cooled at least as rapidly as air cooling. Finally it is precipitation hardened at 649C. for 24 hours and at 760C. for 8 hours, the two stages being separated and followed by air cooling. After local solution treatment the component may be aluminized, diffusion being brought about during subsequent treatments. In a second example an alloy containing C 0À03-0À1 Cr 18-21 Co 12-15 Mo 3À5-5 Ti 2À75-3À25 Al 1À2-1À6 Zr 0À05-0À12 B 0À003-0À07 Ni balance was heated in the blade region only to 1097À5C., and cooled in air or faster, followed by heating the whole component to 1024C. for 4 hours and cooling There follows stabilization at 843C. for 4 hours, cooling and precipitation hardening at 760C. for 16 hours and cooling. Localised heat-treatment may be effected by the ring inductor 4 of Fig.2, or the U-form type <SP>14</SP> of Fig.4.
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| US14152971A | 1971-05-10 | 1971-05-10 |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| GB1333354A true GB1333354A (en) | 1973-10-10 |
Family
ID=22496082
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| GB564772A Expired GB1333354A (en) | 1971-05-10 | 1972-02-07 | Processing for integral gas turbine disc blade components formed from age-hardenable alloys |
Country Status (10)
| Country | Link |
|---|---|
| US (1) | US3741821A (en) |
| JP (1) | JPS5632390B1 (en) |
| CA (1) | CA959740A (en) |
| CH (1) | CH544813A (en) |
| DE (1) | DE2220064C3 (en) |
| FR (1) | FR2139217A5 (en) |
| GB (1) | GB1333354A (en) |
| IL (1) | IL38707A (en) |
| IT (1) | IT951408B (en) |
| SE (1) | SE383534B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1813690A1 (en) * | 2006-01-25 | 2007-08-01 | General Electric Company | Local heat treatment for improved fatigue resistance in turbine components |
| US9938596B2 (en) | 2012-01-30 | 2018-04-10 | General Electric Company | Turbine induction temper system |
Families Citing this family (21)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB1417474A (en) * | 1973-09-06 | 1975-12-10 | Int Nickel Ltd | Heat-treatment of nickel-chromium-cobalt base alloys |
| DE2550858C3 (en) * | 1975-11-12 | 1978-09-28 | 8000 Muenchen | Process for the production and / or heat treatment of metallic moldings |
| US4401480A (en) * | 1978-12-15 | 1983-08-30 | Westinghouse Electric Corp. | Method of selective grain growth in nickel-base superalloys by controlled boron diffusion |
| CA1133366A (en) * | 1978-12-15 | 1982-10-12 | Edwin A. Crombie, Iii | Method of selective grain growth in nickel-base superalloys by controlled boron diffusion |
| US4345950A (en) * | 1980-04-21 | 1982-08-24 | General Electric Company | Method for making a composite grained cast article |
| 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 |
| US4547229A (en) * | 1984-05-07 | 1985-10-15 | Eaton Corporation | Solution heat treating of engine poppet valves |
| US4729802A (en) * | 1986-01-16 | 1988-03-08 | J. I. Case Company | Opener-disk heat-treating process and product |
| DE3885283T2 (en) * | 1987-03-24 | 1994-05-19 | Wyman Gordon Co | METHOD FOR DIFFERENT BORDER HEAT TREATMENT FOR THE PRODUCTION OF WORKPIECES WITH DUAL PROPERTIES. |
| US5326409A (en) * | 1987-03-24 | 1994-07-05 | Wyman-Gordon Company | System for peripheral differential heat treatemnt to form dual-property workpiece |
| US4820358A (en) * | 1987-04-01 | 1989-04-11 | General Electric Company | Method of making high strength superalloy components with graded properties |
| US4813470A (en) * | 1987-11-05 | 1989-03-21 | Allied-Signal Inc. | Casting turbine components with integral airfoils |
| US4841614A (en) * | 1988-02-12 | 1989-06-27 | United Technologies Corporation | Method for fabricating integrally bladed rotors |
| US4838069A (en) * | 1988-02-12 | 1989-06-13 | United Technologies Corporation | Apparatus 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 |
| US5527402A (en) * | 1992-03-13 | 1996-06-18 | General Electric Company | Differentially heat treated process for the manufacture thereof |
| WO2011057661A1 (en) * | 2009-11-11 | 2011-05-19 | Siemens Aktiengesellschaft | Component having areas of different ductility and method for producing a component |
| FR3043410B1 (en) | 2015-11-06 | 2017-12-08 | Safran | DEVICE FOR GENERATING A GRADIENT MICROSTRUCTURE OF STRUCTURE ON AN AXISYMETRIC PIECE |
| CN108031779A (en) * | 2017-11-29 | 2018-05-15 | 无锡透平叶片有限公司 | A kind of turbine blade and preparation method thereof |
-
1971
- 1971-05-10 US US00141529A patent/US3741821A/en not_active Expired - Lifetime
-
1972
- 1972-01-14 CA CA132,507A patent/CA959740A/en not_active Expired
- 1972-02-04 CH CH167672A patent/CH544813A/en not_active IP Right Cessation
- 1972-02-07 GB GB564772A patent/GB1333354A/en not_active Expired
- 1972-02-07 IL IL38707A patent/IL38707A/en unknown
- 1972-02-17 SE SE7201907A patent/SE383534B/en unknown
- 1972-02-24 FR FR7207315A patent/FR2139217A5/fr not_active Expired
- 1972-04-15 IT IT23136/72A patent/IT951408B/en active
- 1972-04-24 DE DE2220064A patent/DE2220064C3/en not_active Expired
- 1972-05-10 JP JP4627672A patent/JPS5632390B1/ja active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| EP1813690A1 (en) * | 2006-01-25 | 2007-08-01 | General Electric Company | Local heat treatment for improved fatigue resistance in turbine components |
| JP2007197830A (en) * | 2006-01-25 | 2007-08-09 | General Electric Co <Ge> | Local heat treatment for improved fatigue resistance in turbine component |
| US9938596B2 (en) | 2012-01-30 | 2018-04-10 | General Electric Company | Turbine induction temper system |
Also Published As
| Publication number | Publication date |
|---|---|
| IL38707A0 (en) | 1972-07-26 |
| CA959740A (en) | 1974-12-24 |
| DE2220064C3 (en) | 1975-06-12 |
| SE383534B (en) | 1976-03-15 |
| JPS5632390B1 (en) | 1981-07-27 |
| IL38707A (en) | 1975-03-13 |
| IT951408B (en) | 1973-06-30 |
| DE2220064B2 (en) | 1974-10-24 |
| DE2220064A1 (en) | 1972-12-07 |
| US3741821A (en) | 1973-06-26 |
| FR2139217A5 (en) | 1973-01-05 |
| CH544813A (en) | 1973-11-30 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| PS | Patent sealed [section 19, patents act 1949] | ||
| PCNP | Patent ceased through non-payment of renewal fee |