GB787666A - Improvements in blades for gas turbine engines - Google Patents

Improvements in blades for gas turbine engines

Info

Publication number
GB787666A
GB787666A GB1002955A GB1002955A GB787666A GB 787666 A GB787666 A GB 787666A GB 1002955 A GB1002955 A GB 1002955A GB 1002955 A GB1002955 A GB 1002955A GB 787666 A GB787666 A GB 787666A
Authority
GB
United Kingdom
Prior art keywords
blade
cooling air
platform
flanges
blades
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
GB1002955A
Inventor
Horace Sinclair Rainbow
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.)
Armstrong Siddeley Motors Ltd
Original Assignee
Armstrong Siddeley Motors Ltd
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
Priority to BE546821D priority Critical patent/BE546821A/xx
Application filed by Armstrong Siddeley Motors Ltd filed Critical Armstrong Siddeley Motors Ltd
Priority to GB1002955A priority patent/GB787666A/en
Priority to FR1144955D priority patent/FR1144955A/en
Publication of GB787666A publication Critical patent/GB787666A/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
    • F01D9/00—Stators
    • F01D9/02—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles
    • F01D9/04—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector
    • F01D9/042—Nozzles; Nozzle boxes; Stator blades; Guide conduits, e.g. individual nozzles forming ring or sector fixing blades to stators
    • 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
    • F01D5/187—Convection cooling

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

787,666. Turbine stator blades. ARMSTRONG SIDDELEY MOTORS, Ltd. March 19, 1956 [April 6, 1955], No. 10029/55. Class 110(3). A turbine stator blade for a gas turbine engine having means for internal flow of cooling air from one end of the blade to the other is provided with an individual chamber at the cooling air outlet end of the blade, the chamber having an aperture at or adjacent the trailing edge whereby all the cooling air flowing through the blade is caused to discharge into a region of uniform low pressure. The stator blade shown has a central lightening passage 29 which is closed at the radially outer end 30 and a series of cooling air ducts 31 extend through the blade adjacent its periphery. The outer and inner ends of the blade are secured by brazing in lozenge-shaped platforms 12, 13 respectively, the outer platform having a pair of integral lugs 14 which are clamped by a bolt 16 to flanges 18, 19 on outer casing rings 20, 21, tubular distance pieces 22 being disposed between the flanges 14. The inner platform 13 is formed with an individual chamber 32 and has an outlet in the form of an elongated aperture 33 at its downstream end, the platform being located between flanges 23, 24 of structural ring members 25, 26, a pin member 28 integral with the platform 13 being received in a radial hole in the ring 26 to locate the platform axially and circumferentially while permitting radial movement. Cooling air flows from a space around the ring members 20, 21 through the ducts 31 in the stator blades to the chambers 32 and finally discharges through the outlets 33 into the gas stream.
GB1002955A 1955-04-06 1955-04-06 Improvements in blades for gas turbine engines Expired GB787666A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
BE546821D BE546821A (en) 1955-04-06
GB1002955A GB787666A (en) 1955-04-06 1955-04-06 Improvements in blades for gas turbine engines
FR1144955D FR1144955A (en) 1955-04-06 1956-03-30 Turbine stator fin

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB1002955A GB787666A (en) 1955-04-06 1955-04-06 Improvements in blades for gas turbine engines

Publications (1)

Publication Number Publication Date
GB787666A true GB787666A (en) 1957-12-11

Family

ID=9960136

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1002955A Expired GB787666A (en) 1955-04-06 1955-04-06 Improvements in blades for gas turbine engines

Country Status (3)

Country Link
BE (1) BE546821A (en)
FR (1) FR1144955A (en)
GB (1) GB787666A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3275294A (en) * 1963-11-14 1966-09-27 Westinghouse Electric Corp Elastic fluid apparatus
US3295823A (en) * 1965-10-13 1967-01-03 Raymond G H Waugh Gas turbine cooling distribution system using the blade ring principle
US3628880A (en) * 1969-12-01 1971-12-21 Gen Electric Vane assembly and temperature control arrangement
US3945758A (en) * 1974-02-28 1976-03-23 Westinghouse Electric Corporation Cooling system for a gas turbine
US4962640A (en) * 1989-02-06 1990-10-16 Westinghouse Electric Corp. Apparatus and method for cooling a gas turbine vane
US5759012A (en) * 1996-12-13 1998-06-02 Caterpillar Inc. Turbine disc ingress prevention method and apparatus

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4126405A (en) * 1976-12-16 1978-11-21 General Electric Company Turbine nozzle
FR2468727A1 (en) * 1979-10-26 1981-05-08 Snecma IMPROVEMENT TO COOLED TURBINE AUBES
US5690469A (en) * 1996-06-06 1997-11-25 United Technologies Corporation Method and apparatus for replacing a vane assembly in a turbine engine

Cited By (7)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3275294A (en) * 1963-11-14 1966-09-27 Westinghouse Electric Corp Elastic fluid apparatus
US3295823A (en) * 1965-10-13 1967-01-03 Raymond G H Waugh Gas turbine cooling distribution system using the blade ring principle
US3628880A (en) * 1969-12-01 1971-12-21 Gen Electric Vane assembly and temperature control arrangement
US3945758A (en) * 1974-02-28 1976-03-23 Westinghouse Electric Corporation Cooling system for a gas turbine
US4962640A (en) * 1989-02-06 1990-10-16 Westinghouse Electric Corp. Apparatus and method for cooling a gas turbine vane
US5759012A (en) * 1996-12-13 1998-06-02 Caterpillar Inc. Turbine disc ingress prevention method and apparatus
GB2320295A (en) * 1996-12-13 1998-06-17 Solar Turbines Inc Injecting cooling air into stator vane wake

Also Published As

Publication number Publication date
FR1144955A (en) 1957-10-21
BE546821A (en)

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