GB1289435A - - Google Patents
Info
- Publication number
- GB1289435A GB1289435A GB1289435DA GB1289435A GB 1289435 A GB1289435 A GB 1289435A GB 1289435D A GB1289435D A GB 1289435DA GB 1289435 A GB1289435 A GB 1289435A
- Authority
- GB
- United Kingdom
- Prior art keywords
- facing
- pores
- layers
- cooling air
- surface relief
- 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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/182—Transpiration cooling
- F01D5/184—Blade walls being made of perforated sheet laminae
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D5/00—Blades; Blade-carrying members; Heating, heat-insulating, cooling or antivibration means on the blades or the members
- F01D5/12—Blades
- F01D5/14—Form or construction
- F01D5/18—Hollow blades, i.e. blades with cooling or heating channels or cavities; Heating, heat-insulating or cooling means on blades
- F01D5/186—Film cooling
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F05—INDEXING SCHEMES RELATING TO ENGINES OR PUMPS IN VARIOUS SUBCLASSES OF CLASSES F01-F04
- F05D—INDEXING SCHEME FOR ASPECTS RELATING TO NON-POSITIVE-DISPLACEMENT MACHINES OR ENGINES, GAS-TURBINES OR JET-PROPULSION PLANTS
- F05D2240/00—Components
- F05D2240/80—Platforms for stationary or moving blades
- F05D2240/81—Cooled platforms
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Turbine Rotor Nozzle Sealing (AREA)
Abstract
1289435 Making turbines; casting composite articles GENERAL MOTORS CORP 19 April 1971 [8 June 1970] 22613/71 Headings B3A and B3F [Also in Division F1] A cast metal gas turbine engine nozzle shroud segment 7 or rotor blade platform 43 has a porous laminated facing 18 or 51 composed of mutually bonded metal layers 19, 20, 22, 23. The facing and a porous laminated nozzle or rotor blade 4 or 40 are located in a mould into which metal is poured and solidified. The mould includes cores to form the cooling air passages in the shroud segment or blade platform and the open end of the blade is plugged. The cast metal fills holes 24 or 52 in the facing and holes 28 in flanges 27 on the facing base layer 23 to secure the facing. The facings and blades have numerous pores, with the pores in each layer out of register with those of the adjacent layer or layers, and some form of surface relief to provide for cooling air flow parallel to the face from one set of pores to the next. The surface relief and pores may be produced by photo-etching. The facing layers may be of a thoria-dispersed nickel chromium alloy.
Applications Claiming Priority (1)
Application Number | Priority Date | Filing Date | Title |
---|---|---|---|
US4403270A | 1970-06-08 | 1970-06-08 |
Publications (1)
Publication Number | Publication Date |
---|---|
GB1289435A true GB1289435A (en) | 1972-09-20 |
Family
ID=21930163
Family Applications (1)
Application Number | Title | Priority Date | Filing Date |
---|---|---|---|
GB1289435D Expired GB1289435A (en) | 1970-06-08 | 1971-04-19 |
Country Status (3)
Country | Link |
---|---|
US (1) | US3610769A (en) |
CA (1) | CA929859A (en) |
GB (1) | GB1289435A (en) |
Cited By (4)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2132703A (en) * | 1982-12-15 | 1984-07-11 | Onera (Off Nat Aerospatiale) | Cooling ceramic blades of turbomachines |
GB2253443A (en) * | 1991-03-05 | 1992-09-09 | Rolls Royce Plc | Gas turbine nozzle guide vane arrangement |
WO1999054597A1 (en) | 1998-04-21 | 1999-10-28 | Siemens Aktiengesellschaft | Turbine blade |
US6887040B2 (en) | 2001-09-12 | 2005-05-03 | Siemens Aktiengesellschaft | Turbine blade/vane |
Families Citing this family (20)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
BE791162A (en) * | 1971-11-10 | 1973-03-01 | Penny Robert N | TURBINE ROTOR |
US3834831A (en) * | 1973-01-23 | 1974-09-10 | Westinghouse Electric Corp | Blade shank cooling arrangement |
US3967353A (en) * | 1974-07-18 | 1976-07-06 | General Electric Company | Gas turbine bucket-root sidewall piece seals |
US4040767A (en) * | 1975-06-02 | 1977-08-09 | United Technologies Corporation | Coolable nozzle guide vane |
US4012167A (en) * | 1975-10-14 | 1977-03-15 | United Technologies Corporation | Turbomachinery vane or blade with cooled platforms |
US4017213A (en) * | 1975-10-14 | 1977-04-12 | United Technologies Corporation | Turbomachinery vane or blade with cooled platforms |
US4118146A (en) * | 1976-08-11 | 1978-10-03 | United Technologies Corporation | Coolable wall |
US4218178A (en) * | 1978-03-31 | 1980-08-19 | General Motors Corporation | Turbine vane structure |
US4650394A (en) * | 1984-11-13 | 1987-03-17 | United Technologies Corporation | Coolable seal assembly for a gas turbine engine |
US5810552A (en) * | 1992-02-18 | 1998-09-22 | Allison Engine Company, Inc. | Single-cast, high-temperature, thin wall structures having a high thermal conductivity member connecting the walls and methods of making the same |
US5295530A (en) * | 1992-02-18 | 1994-03-22 | General Motors Corporation | Single-cast, high-temperature, thin wall structures and methods of making the same |
US5413458A (en) * | 1994-03-29 | 1995-05-09 | United Technologies Corporation | Turbine vane with a platform cavity having a double feed for cooling fluid |
US5711650A (en) * | 1996-10-04 | 1998-01-27 | Pratt & Whitney Canada, Inc. | Gas turbine airfoil cooling |
US6887033B1 (en) * | 2003-11-10 | 2005-05-03 | General Electric Company | Cooling system for nozzle segment platform edges |
US7004720B2 (en) * | 2003-12-17 | 2006-02-28 | Pratt & Whitney Canada Corp. | Cooled turbine vane platform |
GB2439330B (en) * | 2006-06-22 | 2008-09-17 | Rolls Royce Plc | Aerofoil |
US7766606B2 (en) * | 2006-08-17 | 2010-08-03 | Siemens Energy, Inc. | Turbine airfoil cooling system with platform cooling channels with diffusion slots |
EP1923536A1 (en) * | 2006-11-17 | 2008-05-21 | Siemens Aktiengesellschaft | Liner in a cooling channel of a turbine blade |
US9726028B2 (en) | 2011-06-29 | 2017-08-08 | Siemens Energy, Inc. | Ductile alloys for sealing modular component interfaces |
WO2013188869A1 (en) | 2012-06-15 | 2013-12-19 | General Electric Company | Turbine airfoil with cast platform cooling circuit |
Family Cites Families (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB738656A (en) * | 1952-07-26 | 1955-10-19 | Power Jets Res & Dev Ltd | Blades for compressors, turbines and like bladed fluid flow machines |
US3433015A (en) * | 1965-06-23 | 1969-03-18 | Nasa | Gas turbine combustion apparatus |
US3527543A (en) * | 1965-08-26 | 1970-09-08 | Gen Electric | Cooling of structural members particularly for gas turbine engines |
US3529902A (en) * | 1968-05-22 | 1970-09-22 | Gen Motors Corp | Turbine vane |
US3554663A (en) * | 1968-09-25 | 1971-01-12 | Gen Motors Corp | Cooled blade |
-
1970
- 1970-06-08 US US44032A patent/US3610769A/en not_active Expired - Lifetime
-
1971
- 1971-02-05 CA CA104573A patent/CA929859A/en not_active Expired
- 1971-04-19 GB GB1289435D patent/GB1289435A/en not_active Expired
Cited By (5)
Publication number | Priority date | Publication date | Assignee | Title |
---|---|---|---|---|
GB2132703A (en) * | 1982-12-15 | 1984-07-11 | Onera (Off Nat Aerospatiale) | Cooling ceramic blades of turbomachines |
GB2253443A (en) * | 1991-03-05 | 1992-09-09 | Rolls Royce Plc | Gas turbine nozzle guide vane arrangement |
WO1999054597A1 (en) | 1998-04-21 | 1999-10-28 | Siemens Aktiengesellschaft | Turbine blade |
US6533544B1 (en) | 1998-04-21 | 2003-03-18 | Siemens Aktiengesellschaft | Turbine blade |
US6887040B2 (en) | 2001-09-12 | 2005-05-03 | Siemens Aktiengesellschaft | Turbine blade/vane |
Also Published As
Publication number | Publication date |
---|---|
CA929859A (en) | 1973-07-10 |
US3610769A (en) | 1971-10-05 |
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Legal Events
Date | Code | Title | Description |
---|---|---|---|
PS | Patent sealed [section 19, patents act 1949] | ||
PE20 | Patent expired after termination of 20 years |