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
Application number
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 filed Critical
Publication of GB1289435A publication Critical patent/GB1289435A/en
Expired legal-status Critical Current

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.
GB1289435D 1970-06-08 1971-04-19 Expired GB1289435A (en)

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)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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)

* Cited by examiner, † Cited by third party
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

Cited By (5)

* Cited by examiner, † Cited by third party
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