GB1299904A - Transpiration cooled turbine blade with thin trailing edge - Google Patents

Transpiration cooled turbine blade with thin trailing edge

Info

Publication number
GB1299904A
GB1299904A GB6320069A GB6320069A GB1299904A GB 1299904 A GB1299904 A GB 1299904A GB 6320069 A GB6320069 A GB 6320069A GB 6320069 A GB6320069 A GB 6320069A GB 1299904 A GB1299904 A GB 1299904A
Authority
GB
United Kingdom
Prior art keywords
blade
turbine blade
air
trailing edge
ribs
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
GB6320069A
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.)
Curtiss Wright Corp
Original Assignee
Curtiss Wright Corp
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 by Curtiss Wright Corp filed Critical Curtiss Wright Corp
Priority to GB6320069A priority Critical patent/GB1299904A/en
Publication of GB1299904A publication Critical patent/GB1299904A/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
    • F01D5/183—Blade walls being porous

Landscapes

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

Abstract

1299904 Turbine blades CURTISS WRIGHT CORP 30 Dec 1969 63200/69 Heading FIT A gas turbine blade comprises a strut member 26 of generally aerofoil cross-section having a smooth trailing portion 21 and a forward portion with ribs 30 to which is secured a sheath 23 of porous material which terminates flush with the trailing portion 21. As shown the blade is a stator blade and the strut 26 has a chamber 27 to which cooling air is supplied through hollow trunnions 28, the air thence flowing through holes 31 to the recesses 29 between ribs 30. Adjacent recesses 29 may be inter-connected. The air then flows through the porous sheath 23, which is formed of metal mesh or sintered powdered metal, and over the blade exterior. The blade may be a rotor blade.
GB6320069A 1969-12-30 1969-12-30 Transpiration cooled turbine blade with thin trailing edge Expired GB1299904A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB6320069A GB1299904A (en) 1969-12-30 1969-12-30 Transpiration cooled turbine blade with thin trailing edge

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB6320069A GB1299904A (en) 1969-12-30 1969-12-30 Transpiration cooled turbine blade with thin trailing edge

Publications (1)

Publication Number Publication Date
GB1299904A true GB1299904A (en) 1972-12-13

Family

ID=10488858

Family Applications (1)

Application Number Title Priority Date Filing Date
GB6320069A Expired GB1299904A (en) 1969-12-30 1969-12-30 Transpiration cooled turbine blade with thin trailing edge

Country Status (1)

Country Link
GB (1) GB1299904A (en)

Cited By (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5102299A (en) * 1986-11-10 1992-04-07 The United States Of America As Represented By The Secretary Of The Air Force Airfoil trailing edge cooling configuration
US5405242A (en) * 1990-07-09 1995-04-11 United Technologies Corporation Cooled vane
US5720431A (en) * 1988-08-24 1998-02-24 United Technologies Corporation Cooled blades for a gas turbine engine
US5976337A (en) * 1997-10-27 1999-11-02 Allison Engine Company Method for electrophoretic deposition of brazing material
EP2472062A1 (en) * 2010-12-28 2012-07-04 Rolls-Royce North American Technologies, Inc. Gas turbine engine and airfoil
US20200109635A1 (en) * 2018-10-05 2020-04-09 United Technologies Corporation Composite cast porous metal turbine component

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US5102299A (en) * 1986-11-10 1992-04-07 The United States Of America As Represented By The Secretary Of The Air Force Airfoil trailing edge cooling configuration
US5720431A (en) * 1988-08-24 1998-02-24 United Technologies Corporation Cooled blades for a gas turbine engine
US5405242A (en) * 1990-07-09 1995-04-11 United Technologies Corporation Cooled vane
US5419039A (en) * 1990-07-09 1995-05-30 United Technologies Corporation Method of making an air cooled vane with film cooling pocket construction
US5976337A (en) * 1997-10-27 1999-11-02 Allison Engine Company Method for electrophoretic deposition of brazing material
EP2472062A1 (en) * 2010-12-28 2012-07-04 Rolls-Royce North American Technologies, Inc. Gas turbine engine and airfoil
US8961133B2 (en) 2010-12-28 2015-02-24 Rolls-Royce North American Technologies, Inc. Gas turbine engine and cooled airfoil
US20200109635A1 (en) * 2018-10-05 2020-04-09 United Technologies Corporation Composite cast porous metal turbine component

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees