GB1388260A - Cooled turbine blades - Google Patents

Cooled turbine blades

Info

Publication number
GB1388260A
GB1388260A GB1839373A GB1839373A GB1388260A GB 1388260 A GB1388260 A GB 1388260A GB 1839373 A GB1839373 A GB 1839373A GB 1839373 A GB1839373 A GB 1839373A GB 1388260 A GB1388260 A GB 1388260A
Authority
GB
United Kingdom
Prior art keywords
air
blade
cavity
trailing edge
exhausted
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
GB1839373A
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.)
General Electric Co
Original Assignee
General Electric Co
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 General Electric Co filed Critical General Electric Co
Publication of GB1388260A publication Critical patent/GB1388260A/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
    • F01D5/187—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
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/60—Efficient propulsion technologies, e.g. for aircraft

Landscapes

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

Abstract

1388260 Air-cooled turbine blades GENERAL ELECTRIC CO 17 April 1973 [24 April 1972] 18393/73 Heading FIT An air-cooled turbine blade includes three cavities 30, 32, 34 disposed serially adjacent to one another between the trailing edge 28 and the leading edge 26 of the blade shell 16. Inserts 36, 38 are disposed within cavities 32, 34 and are provided with arrays of orifices 37, 39 for the distribution of cooling air in an impinging flow against the inner surfaces 33, 35 of each respective cavity. The inner surfaces 31 of cavity 30 are provided with protrusions 31a to enhance the turbulence of the coolant flow. Air enters the blade through inlets 40, 42 leading into cavities 30, 34 and a passage 44 adjacent the blade tip enables the air in cavity 30 to pass into cavity 32. A minor portion of the cooling air introduced through trailing edge inlet 40 is exhausted through a plurality of exit apertures 46 provided at the trailing edge 28 of the blade shell 16. The air entering leading edge cavity 34 through inlet 42 is exhausted through three groups of apertures 48, 50, 52 which direct the air in a cooling film across various portions of the outer surface of the blade shell 16. Air is exhausted from cavity 32 through apertures 54, also in a cooling film, over the blade outer surface adjacent the blade trailing edge.
GB1839373A 1972-04-24 1973-04-17 Cooled turbine blades Expired GB1388260A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US246778A US3891348A (en) 1972-04-24 1972-04-24 Turbine blade with increased film cooling

Publications (1)

Publication Number Publication Date
GB1388260A true GB1388260A (en) 1975-03-26

Family

ID=22932164

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1839373A Expired GB1388260A (en) 1972-04-24 1973-04-17 Cooled turbine blades

Country Status (4)

Country Link
US (1) US3891348A (en)
DE (1) DE2320581C2 (en)
FR (1) FR2331251A5 (en)
GB (1) GB1388260A (en)

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4056332A (en) * 1975-05-16 1977-11-01 Bbc Brown Boveri & Company Limited Cooled turbine blade
EP0130038A1 (en) * 1983-06-20 1985-01-02 General Electric Company Turbulence promotion
EP0182588A1 (en) * 1984-11-15 1986-05-28 Westinghouse Electric Corporation Multi-chamber airfoil cooling insert for turbine vane
WO2012145121A1 (en) * 2011-04-20 2012-10-26 Siemens Energy, Inc. Cooled airfoil in a turbine engine

Families Citing this family (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB1565361A (en) * 1976-01-29 1980-04-16 Rolls Royce Blade or vane for a gas turbine engien
US4221539A (en) * 1977-04-20 1980-09-09 The Garrett Corporation Laminated airfoil and method for turbomachinery
US4257737A (en) * 1978-07-10 1981-03-24 United Technologies Corporation Cooled rotor blade
FR2516165B1 (en) * 1981-11-10 1986-07-04 Snecma GAS TURBINE BLADE WITH FLUID CIRCULATION COOLING CHAMBER AND METHOD FOR PRODUCING THE SAME
US4645415A (en) * 1983-12-23 1987-02-24 United Technologies Corporation Air cooler for providing buffer air to a bearing compartment
US4529358A (en) * 1984-02-15 1985-07-16 The United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration Vortex generating flow passage design for increased film cooling effectiveness
US4705455A (en) * 1985-12-23 1987-11-10 United Technologies Corporation Convergent-divergent film coolant passage
DE3629910A1 (en) * 1986-09-03 1988-03-17 Mtu Muenchen Gmbh METAL HOLLOW COMPONENT WITH A METAL INSERT, IN PARTICULAR TURBINE BLADE WITH COOLING INSERT
JP3142850B2 (en) * 1989-03-13 2001-03-07 株式会社東芝 Turbine cooling blades and combined power plants
US5156526A (en) * 1990-12-18 1992-10-20 General Electric Company Rotation enhanced rotor blade cooling using a single row of coolant passageways
US5165852A (en) * 1990-12-18 1992-11-24 General Electric Company Rotation enhanced rotor blade cooling using a double row of coolant passageways
US5660524A (en) * 1992-07-13 1997-08-26 General Electric Company Airfoil blade having a serpentine cooling circuit and impingement cooling
US5591002A (en) * 1994-08-23 1997-01-07 General Electric Co. Closed or open air cooling circuits for nozzle segments with wheelspace purge
US5503529A (en) * 1994-12-08 1996-04-02 General Electric Company Turbine blade having angled ejection slot
US6193465B1 (en) * 1998-09-28 2001-02-27 General Electric Company Trapped insert turbine airfoil
US6183192B1 (en) * 1999-03-22 2001-02-06 General Electric Company Durable turbine nozzle
US6283708B1 (en) 1999-12-03 2001-09-04 United Technologies Corporation Coolable vane or blade for a turbomachine
DE10004128B4 (en) 2000-01-31 2007-06-28 Alstom Technology Ltd. Air-cooled turbine blade
JP2009162119A (en) * 2008-01-08 2009-07-23 Ihi Corp Turbine blade cooling structure
JP5948436B2 (en) 2011-12-29 2016-07-06 ゼネラル・エレクトリック・カンパニイ Blade cooling circuit
EP2626519A1 (en) * 2012-02-09 2013-08-14 Siemens Aktiengesellschaft Turbine assembly, corresponding impingement cooling tube and gas turbine engine
US10662778B2 (en) * 2015-08-28 2020-05-26 Siemens Aktiengesellschaft Turbine airfoil with internal impingement cooling feature
US10895158B2 (en) * 2016-07-28 2021-01-19 Siemens Aktiengesellschaft Turbine airfoil with independent cooling circuit for mid-body temperature control
US20180051566A1 (en) * 2016-08-16 2018-02-22 General Electric Company Airfoil for a turbine engine with a porous tip
US10260363B2 (en) * 2016-12-08 2019-04-16 General Electric Company Additive manufactured seal for insert compartmentalization
US10697310B2 (en) * 2018-05-17 2020-06-30 Raytheon Technologies Corporation Multiple source impingement baffles for gas turbine engine components
US11293347B2 (en) * 2018-11-09 2022-04-05 Raytheon Technologies Corporation Airfoil with baffle showerhead and cooling passage network having aft inlet
US11480059B2 (en) * 2019-08-20 2022-10-25 Raytheon Technologies Corporation Airfoil with rib having connector arms

Family Cites Families (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2699598A (en) * 1952-02-08 1955-01-18 Utica Drop Forge & Tool Corp Method of making turbine blades
NL88170C (en) * 1952-10-31 1900-01-01
US2866618A (en) * 1953-02-13 1958-12-30 Thomas W Jackson Reverse flow air cooled turbine blade
US3301526A (en) * 1964-12-22 1967-01-31 United Aircraft Corp Stacked-wafer turbine vane or blade
US3528751A (en) * 1966-02-26 1970-09-15 Gen Electric Cooled vane structure for high temperature turbine
US3560107A (en) * 1968-09-25 1971-02-02 Gen Motors Corp Cooled airfoil
US3628885A (en) * 1969-10-01 1971-12-21 Gen Electric Fluid-cooled airfoil
BE755567A (en) * 1969-12-01 1971-02-15 Gen Electric FIXED VANE STRUCTURE, FOR GAS TURBINE ENGINE AND ASSOCIATED TEMPERATURE ADJUSTMENT ARRANGEMENT

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4056332A (en) * 1975-05-16 1977-11-01 Bbc Brown Boveri & Company Limited Cooled turbine blade
EP0130038A1 (en) * 1983-06-20 1985-01-02 General Electric Company Turbulence promotion
EP0182588A1 (en) * 1984-11-15 1986-05-28 Westinghouse Electric Corporation Multi-chamber airfoil cooling insert for turbine vane
WO2012145121A1 (en) * 2011-04-20 2012-10-26 Siemens Energy, Inc. Cooled airfoil in a turbine engine
US9011077B2 (en) 2011-04-20 2015-04-21 Siemens Energy, Inc. Cooled airfoil in a turbine engine

Also Published As

Publication number Publication date
US3891348A (en) 1975-06-24
DE2320581A1 (en) 1975-05-28
FR2331251A5 (en) 1977-06-03
DE2320581C2 (en) 1984-06-07

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Legal Events

Date Code Title Description
PS Patent sealed
PE20 Patent expired after termination of 20 years

Effective date: 19930416