GB1366704A - Hollow cool'd blade for a gas - Google Patents

Hollow cool'd blade for a gas

Info

Publication number
GB1366704A
GB1366704A GB3106671A GB3106671A GB1366704A GB 1366704 A GB1366704 A GB 1366704A GB 3106671 A GB3106671 A GB 3106671A GB 3106671 A GB3106671 A GB 3106671A GB 1366704 A GB1366704 A GB 1366704A
Authority
GB
United Kingdom
Prior art keywords
corrugations
tube
blade
air
vortices
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
GB3106671A
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.)
Rolls Royce PLC
Original Assignee
Rolls Royce PLC
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 Rolls Royce PLC filed Critical Rolls Royce PLC
Priority to GB3106671A priority Critical patent/GB1366704A/en
Publication of GB1366704A publication Critical patent/GB1366704A/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
    • F01D5/186—Film cooling
    • 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
    • F01D5/188—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall
    • F01D5/189—Convection cooling with an insert in the blade cavity to guide the cooling fluid, e.g. forming a separation wall the insert having a tubular cross-section, e.g. airfoil shape

Landscapes

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

Abstract

1366704 Gas turbine blades ROLLS-ROYCE (1971) Ltd 28 June 1972 [2 July 1971] 31066/71 Heading FIT A hollow blade for a gas turbine engine includes longitudinally extending corrugations in at least a portion of its internal surface and means to direct cooling fluid into the corrugations to form vortices. In one arrangement the forward portion of the blade has corrugations 16 which support at their peaks a sheet metal tube 17 supplied with cooling air through duct 23. The peaks of corrugations 16 are cut away at 22 to form angled slots which enable the air flowing through holes 20, 21 from the interior of tube 17 to flow from one corrugation to the next and thus generate vortices. This air leaves the corrugations through film cooling holes 24. Some air leaves tube 17 through its open leading edge 18 which is braced by struts 19. The rearward blade portion has longitudinal passages 25, 26, 27 with angled inter-connections at alternate ends to define a sinuous cooling air path in which vortices are generated. Passage 27 is connected by passages 29 to a trailing edge slot 30 which is itself corrugated Fig. 4 (not shown). Film cooling holes also extend from the passages. In modifications tube 17 and corrugations 16 extend to the blade trailing edge. Tube 17 may be provided with inclined nozzles to direct cooling air into the corrugations.
GB3106671A 1972-06-28 1972-06-28 Hollow cool'd blade for a gas Expired GB1366704A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB3106671A GB1366704A (en) 1972-06-28 1972-06-28 Hollow cool'd blade for a gas

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB3106671A GB1366704A (en) 1972-06-28 1972-06-28 Hollow cool'd blade for a gas

Publications (1)

Publication Number Publication Date
GB1366704A true GB1366704A (en) 1974-09-11

Family

ID=10317459

Family Applications (1)

Application Number Title Priority Date Filing Date
GB3106671A Expired GB1366704A (en) 1972-06-28 1972-06-28 Hollow cool'd blade for a gas

Country Status (1)

Country Link
GB (1) GB1366704A (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2294323A1 (en) * 1974-12-11 1976-07-09 United Technologies Corp AIR-COOLED TURBINE VANE
US4180373A (en) * 1977-12-28 1979-12-25 United Technologies Corporation Turbine blade
US4221539A (en) * 1977-04-20 1980-09-09 The Garrett Corporation Laminated airfoil and method for turbomachinery
US4257734A (en) * 1978-03-22 1981-03-24 Rolls-Royce Limited Guide vanes for gas turbine engines
US4752186A (en) * 1981-06-26 1988-06-21 United Technologies Corporation Coolable wall configuration
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
GB2260166A (en) * 1985-10-18 1993-04-07 Rolls Royce Cooled aerofoil blade or vane for a gas turbine engine
GB2270718A (en) * 1992-09-22 1994-03-23 Rolls Royce Plc Single crystal turbine blades having pedestals.
US7329102B2 (en) 2004-11-13 2008-02-12 Rolls-Royce Plc Blade
WO2015030926A1 (en) 2013-08-30 2015-03-05 United Technologies Corporation Baffle for gas turbine engine vane
US10641103B2 (en) 2017-01-19 2020-05-05 United Technologies Corporation Trailing edge configuration with cast slots and drilled filmholes

Cited By (17)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2294323A1 (en) * 1974-12-11 1976-07-09 United Technologies Corp AIR-COOLED TURBINE VANE
US4221539A (en) * 1977-04-20 1980-09-09 The Garrett Corporation Laminated airfoil and method for turbomachinery
US4180373A (en) * 1977-12-28 1979-12-25 United Technologies Corporation Turbine blade
DE2906366A1 (en) * 1977-12-28 1980-08-21 United Technologies Corp TURBINE SHOVEL
US4257734A (en) * 1978-03-22 1981-03-24 Rolls-Royce Limited Guide vanes for gas turbine engines
US4752186A (en) * 1981-06-26 1988-06-21 United Technologies Corporation Coolable wall configuration
GB2260166B (en) * 1985-10-18 1993-06-30 Rolls Royce Cooled aerofoil blade or vane for a gas turbine engine
GB2260166A (en) * 1985-10-18 1993-04-07 Rolls Royce Cooled aerofoil blade or vane for a gas turbine engine
US5263820A (en) * 1985-10-18 1993-11-23 Rolls-Royce Cooled aerofoil blade for vane for a gas turbine engine
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
GB2270718A (en) * 1992-09-22 1994-03-23 Rolls Royce Plc Single crystal turbine blades having pedestals.
US7329102B2 (en) 2004-11-13 2008-02-12 Rolls-Royce Plc Blade
WO2015030926A1 (en) 2013-08-30 2015-03-05 United Technologies Corporation Baffle for gas turbine engine vane
EP3039248A1 (en) * 2013-08-30 2016-07-06 United Technologies Corporation Baffle for gas turbine engine vane
EP3039248A4 (en) * 2013-08-30 2016-09-14 United Technologies Corp Baffle for gas turbine engine vane
US10240470B2 (en) 2013-08-30 2019-03-26 United Technologies Corporation Baffle for gas turbine engine vane
US10641103B2 (en) 2017-01-19 2020-05-05 United Technologies Corporation Trailing edge configuration with cast slots and drilled filmholes

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Legal Events

Date Code Title Description
PS Patent sealed
PCNP Patent ceased through non-payment of renewal fee