GB2005775A - Cooled rotor blade for a gas turbine engine - Google Patents

Cooled rotor blade for a gas turbine engine

Info

Publication number
GB2005775A
GB2005775A GB7837265A GB7837265A GB2005775A GB 2005775 A GB2005775 A GB 2005775A GB 7837265 A GB7837265 A GB 7837265A GB 7837265 A GB7837265 A GB 7837265A GB 2005775 A GB2005775 A GB 2005775A
Authority
GB
United Kingdom
Prior art keywords
gas turbine
turbine engine
rotor blade
cooled rotor
tube
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.)
Granted
Application number
GB7837265A
Other versions
GB2005775B (en
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 GB7837265A priority Critical patent/GB2005775B/en
Publication of GB2005775A publication Critical patent/GB2005775A/en
Application granted granted Critical
Publication of GB2005775B publication Critical patent/GB2005775B/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
    • 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
    • F01D5/22—Blade-to-blade connections, e.g. for damping vibrations
    • F01D5/225—Blade-to-blade connections, e.g. for damping vibrations by shrouding
    • 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

The blade comprises an aerofoil 19 in which there are longitudinally extending cooling fluid passages 22, 23, 24, 25. At the tip of the aerofoil is located a separate, chordwise extending tube 29. The tube has apertures 34, 35, 36 in its wall which correspond with at least some of the passages 23, 24, and 25, whereby the spent cooling fluid from these passages may pass through the tube 29 to join the gas flow of the engine. <IMAGE>
GB7837265A 1977-10-08 1978-09-19 Cooled rotor blade for a gas turbine engine Expired GB2005775B (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB7837265A GB2005775B (en) 1977-10-08 1978-09-19 Cooled rotor blade for a gas turbine engine

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
GB4196077 1977-10-08
GB7837265A GB2005775B (en) 1977-10-08 1978-09-19 Cooled rotor blade for a gas turbine engine

Publications (2)

Publication Number Publication Date
GB2005775A true GB2005775A (en) 1979-04-25
GB2005775B GB2005775B (en) 1982-05-06

Family

ID=26264786

Family Applications (1)

Application Number Title Priority Date Filing Date
GB7837265A Expired GB2005775B (en) 1977-10-08 1978-09-19 Cooled rotor blade for a gas turbine engine

Country Status (1)

Country Link
GB (1) GB2005775B (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994012768A2 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Coolable airfoil structure
US6142739A (en) * 1996-04-12 2000-11-07 Rolls-Royce Plc Turbine rotor blades
EP1426554A1 (en) * 2002-12-06 2004-06-09 Rolls-Royce Plc Blade cooling
CN102639817A (en) * 2010-01-20 2012-08-15 三菱重工业株式会社 Turbine rotor blade and turbo machine
US8573925B2 (en) 2009-06-15 2013-11-05 Rolls-Royce Plc Cooled component for a gas turbine engine
US20150017003A1 (en) * 2013-03-07 2015-01-15 Rolls-Royce Corporation Gas turbine engine shrouded blade
EP3163023A1 (en) * 2015-10-27 2017-05-03 General Electric Company Turbine bucket with cooling passage in the shroud
US10156145B2 (en) 2015-10-27 2018-12-18 General Electric Company Turbine bucket having cooling passageway
US10508554B2 (en) 2015-10-27 2019-12-17 General Electric Company Turbine bucket having outlet path in shroud

Cited By (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1994012768A3 (en) * 1992-11-24 1994-07-21 United Technologies Corp Coolable airfoil structure
US5462405A (en) * 1992-11-24 1995-10-31 United Technologies Corporation Coolable airfoil structure
WO1994012768A2 (en) * 1992-11-24 1994-06-09 United Technologies Corporation Coolable airfoil structure
US6142739A (en) * 1996-04-12 2000-11-07 Rolls-Royce Plc Turbine rotor blades
EP1426554A1 (en) * 2002-12-06 2004-06-09 Rolls-Royce Plc Blade cooling
US8573925B2 (en) 2009-06-15 2013-11-05 Rolls-Royce Plc Cooled component for a gas turbine engine
US9194239B2 (en) 2010-01-20 2015-11-24 Mitsubishi Heavy Industries, Ltd. Turbine rotor blade and turbo machine
CN102639817A (en) * 2010-01-20 2012-08-15 三菱重工业株式会社 Turbine rotor blade and turbo machine
EP2527596A1 (en) * 2010-01-20 2012-11-28 Mitsubishi Heavy Industries, Ltd. Turbine rotor blade and turbo machine
EP2527596A4 (en) * 2010-01-20 2013-07-31 Mitsubishi Heavy Ind Ltd Turbine rotor blade and turbo machine
KR101305575B1 (en) 2010-01-20 2013-09-09 미츠비시 쥬고교 가부시키가이샤 Turbine rotor blade and turbo machine
CN102639817B (en) * 2010-01-20 2015-03-11 三菱重工业株式会社 Turbine rotor blade and turbo machine
US20150017003A1 (en) * 2013-03-07 2015-01-15 Rolls-Royce Corporation Gas turbine engine shrouded blade
US9683446B2 (en) * 2013-03-07 2017-06-20 Rolls-Royce Energy Systems, Inc. Gas turbine engine shrouded blade
EP3163023A1 (en) * 2015-10-27 2017-05-03 General Electric Company Turbine bucket with cooling passage in the shroud
JP2017082786A (en) * 2015-10-27 2017-05-18 ゼネラル・エレクトリック・カンパニイ Turbine bucket having outlet path in shroud
US9885243B2 (en) 2015-10-27 2018-02-06 General Electric Company Turbine bucket having outlet path in shroud
US10156145B2 (en) 2015-10-27 2018-12-18 General Electric Company Turbine bucket having cooling passageway
US10508554B2 (en) 2015-10-27 2019-12-17 General Electric Company Turbine bucket having outlet path in shroud
US11078797B2 (en) 2015-10-27 2021-08-03 General Electric Company Turbine bucket having outlet path in shroud

Also Published As

Publication number Publication date
GB2005775B (en) 1982-05-06

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Legal Events

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