GB1467483A - Cooled vane for a gas turbine engine - Google Patents

Cooled vane for a gas turbine engine

Info

Publication number
GB1467483A
GB1467483A GB742474A GB742474A GB1467483A GB 1467483 A GB1467483 A GB 1467483A GB 742474 A GB742474 A GB 742474A GB 742474 A GB742474 A GB 742474A GB 1467483 A GB1467483 A GB 1467483A
Authority
GB
United Kingdom
Prior art keywords
vane
cooling
tubes
tube
section
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
GB742474A
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 GB742474A priority Critical patent/GB1467483A/en
Priority to IT20384/75A priority patent/IT1031830B/en
Priority to FR7504997A priority patent/FR2333947A1/en
Publication of GB1467483A publication Critical patent/GB1467483A/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
    • 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

1467483 Gas turbine engines; cooled inlet guide vanes ROLLS-ROYCE (1971) Ltd 31 Jan 1975 [19 Feb 1974] 07424/74 Heading FIT A cooled vane for a gas turbine engine comprises a longitudinally extending hollow within the vane and a pair of nested cooling air entry tubes 20, 21 within the hollow, a first cooling space within the innermost tube 20 and a second cooling space between the two tubes 20, 21 being provided with cooling air entries at opposite ends of the vane, and at least one of the tubes 20, 21 tapering so that the cooling space it defines reduces progressively in sectional area from its end adjacent into cooling air entry to its other end, each tube comprising one open side which is closed by part of the wall of the longitudinally extending hollow within the vane. In the embodiment illustrated, the outermost tube 21 is of constant sectional area whilst the innermost tube 20 tapers, the tubes 20, 21 being mounted within a leading edge compartment of an aerofoil section 19 and each having one side completed by the leading edge wall of the vane. The innermost tube 20 is unapertured while the outermost tube 21 is provided with holes 26 for the impingement cooling of the adjacent aerofoil section wall. The leading edge portion of the vane is provided with film cooling holes 32. The forward section of the vane is divided from the rearward section by an apertured web 27, and the latter section is provided with internal divisions 28, 29 forming a labyrinthine passage leading to a trailing edge air exit slot 30 braced by struts 31.
GB742474A 1974-02-19 1974-02-19 Cooled vane for a gas turbine engine Expired GB1467483A (en)

Priority Applications (3)

Application Number Priority Date Filing Date Title
GB742474A GB1467483A (en) 1974-02-19 1974-02-19 Cooled vane for a gas turbine engine
IT20384/75A IT1031830B (en) 1974-02-19 1975-02-18 COOLED VANE FOR GAS TURBINE ENGINES
FR7504997A FR2333947A1 (en) 1974-02-19 1975-02-18 REFRIGERATED BLADE FOR GAS TURBINE ENGINE

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB742474A GB1467483A (en) 1974-02-19 1974-02-19 Cooled vane for a gas turbine engine

Publications (1)

Publication Number Publication Date
GB1467483A true GB1467483A (en) 1977-03-16

Family

ID=9832863

Family Applications (1)

Application Number Title Priority Date Filing Date
GB742474A Expired GB1467483A (en) 1974-02-19 1974-02-19 Cooled vane for a gas turbine engine

Country Status (3)

Country Link
FR (1) FR2333947A1 (en)
GB (1) GB1467483A (en)
IT (1) IT1031830B (en)

Cited By (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4303374A (en) * 1978-12-15 1981-12-01 General Electric Company Film cooled airfoil body
US4461612A (en) * 1982-04-27 1984-07-24 Rolls-Royce Limited Aerofoil for a gas turbine engine
EP1052373A2 (en) 1999-05-10 2000-11-15 General Electric Company Pressure compensated turbine nozzle
EP1207269A1 (en) * 2000-11-16 2002-05-22 Siemens Aktiengesellschaft Gas turbine vane
US6468031B1 (en) * 2000-05-16 2002-10-22 General Electric Company Nozzle cavity impingement/area reduction insert
EP1283326A1 (en) * 2001-08-09 2003-02-12 Siemens Aktiengesellschaft Cooling of a turbine vane
GB2405451A (en) * 2003-08-23 2005-03-02 Rolls Royce Plc A vane assembly for a gas turbine engine
US7431559B2 (en) 2004-12-21 2008-10-07 United Technologies Corporation Dirt separation for impingement cooled turbine components
EP3023586A1 (en) * 2014-11-21 2016-05-25 Siemens Aktiengesellschaft Hollow blade body, inserted fin and hollow blade
EP3032034A1 (en) * 2014-12-12 2016-06-15 United Technologies Corporation Baffle insert, vane with a baffle insert, and corresponding method of manufacturing a vane
US20170234145A1 (en) * 2016-02-15 2017-08-17 General Electric Company Accelerator insert for a gas turbine engine airfoil
CN109210573A (en) * 2018-08-10 2019-01-15 江苏大学 A kind of Novel variable-section aeroengine combustor buring room
EP3569819A1 (en) * 2018-05-17 2019-11-20 United Technologies Corporation Multiple source impingement baffles for gas turbine engine components

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4025226A (en) * 1975-10-03 1977-05-24 United Technologies Corporation Air cooled turbine vane
US4257734A (en) * 1978-03-22 1981-03-24 Rolls-Royce Limited Guide vanes for gas turbine engines
GB2106996A (en) * 1981-09-30 1983-04-20 Rolls Royce Cooled rotor aerofoil blade for a gas turbine engine

Cited By (28)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4303374A (en) * 1978-12-15 1981-12-01 General Electric Company Film cooled airfoil body
US4461612A (en) * 1982-04-27 1984-07-24 Rolls-Royce Limited Aerofoil for a gas turbine engine
EP1052373A2 (en) 1999-05-10 2000-11-15 General Electric Company Pressure compensated turbine nozzle
JP2000345808A (en) * 1999-05-10 2000-12-12 General Electric Co <Ge> Pressure compensation turbine nozzle
JP4627840B2 (en) * 1999-05-10 2011-02-09 ゼネラル・エレクトリック・カンパニイ Pressure compensated turbine nozzle
EP1052373A3 (en) * 1999-05-10 2004-01-28 General Electric Company Pressure compensated turbine nozzle
US6468031B1 (en) * 2000-05-16 2002-10-22 General Electric Company Nozzle cavity impingement/area reduction insert
US6572329B2 (en) 2000-11-16 2003-06-03 Siemens Aktiengesellschaft Gas turbine
EP1207269A1 (en) * 2000-11-16 2002-05-22 Siemens Aktiengesellschaft Gas turbine vane
EP1283326A1 (en) * 2001-08-09 2003-02-12 Siemens Aktiengesellschaft Cooling of a turbine vane
US6905301B2 (en) 2001-08-09 2005-06-14 Siemens Aktiengesellschaft Turbine blade/vane
GB2405451A (en) * 2003-08-23 2005-03-02 Rolls Royce Plc A vane assembly for a gas turbine engine
US7179047B2 (en) 2003-08-23 2007-02-20 Rolls-Royce Plc Vane apparatus for a gas turbine engine
GB2405451B (en) * 2003-08-23 2008-03-19 Rolls Royce Plc Vane apparatus for a gas turbine engine
US7431559B2 (en) 2004-12-21 2008-10-07 United Technologies Corporation Dirt separation for impingement cooled turbine components
CN107002496A (en) * 2014-11-21 2017-08-01 西门子股份公司 Hollow blade body, insertion rib and hollow blade
WO2016078851A1 (en) * 2014-11-21 2016-05-26 Siemens Aktiengesellschaft Hollow blade body, insertion rib, and hollow blade
EP3023586A1 (en) * 2014-11-21 2016-05-25 Siemens Aktiengesellschaft Hollow blade body, inserted fin and hollow blade
EP3032034A1 (en) * 2014-12-12 2016-06-15 United Technologies Corporation Baffle insert, vane with a baffle insert, and corresponding method of manufacturing a vane
US10053996B2 (en) 2014-12-12 2018-08-21 United Technologies Corporation Sliding baffle inserts
US20180371926A1 (en) * 2014-12-12 2018-12-27 United Technologies Corporation Sliding baffle inserts
US10753216B2 (en) 2014-12-12 2020-08-25 Raytheon Technologies Corporation Sliding baffle inserts
US20170234145A1 (en) * 2016-02-15 2017-08-17 General Electric Company Accelerator insert for a gas turbine engine airfoil
US10443407B2 (en) * 2016-02-15 2019-10-15 General Electric Company Accelerator insert for a gas turbine engine airfoil
EP3569819A1 (en) * 2018-05-17 2019-11-20 United Technologies Corporation Multiple source impingement baffles for gas turbine engine components
US10697310B2 (en) 2018-05-17 2020-06-30 Raytheon Technologies Corporation Multiple source impingement baffles for gas turbine engine components
CN109210573A (en) * 2018-08-10 2019-01-15 江苏大学 A kind of Novel variable-section aeroengine combustor buring room
CN109210573B (en) * 2018-08-10 2023-08-18 江苏大学 Novel variable cross-section aeroengine combustion chamber

Also Published As

Publication number Publication date
IT1031830B (en) 1979-05-10
FR2333947A1 (en) 1977-07-01

Similar Documents

Publication Publication Date Title
GB1467483A (en) Cooled vane for a gas turbine engine
US3051439A (en) Blades for gas turbine engines
US4474532A (en) Coolable airfoil for a rotary machine
US4252501A (en) Hollow cooled vane for a gas turbine engine
US4168938A (en) Blade or vane for a gas turbine engine
GB1359983A (en) Cooled guide blades for gas turbines
US5215431A (en) Cooled turbine guide vane
GB1519590A (en) Gas turbine engine
GB1400285A (en) Hollow cooled vane or blade for a gas turbine engine
GB1355558A (en) Cooled vane or blade for a gas turbine engine
US3045965A (en) Turbine blades, vanes and the like
US4312624A (en) Air cooled hollow vane construction
US5342172A (en) Cooled turbo-machine vane
GB1357713A (en) Cooled rotor blades for gas turbines
GB1331206A (en) Vane structure for gas turbine
GB1304678A (en)
GB1514613A (en) Blade or vane for a gas turbine engine
GB1222565A (en) Gas turbine guide blade
GB784196A (en) Hollow air cooled sheet metal turbine blade
GB1034260A (en) Aerofoil-shaped blade for use in a fluid flow machine
GB1316029A (en) Turbofan engine thrust reversers
GB1508571A (en) Hollow cooled blade or vane for a gas turbine engine
GB1285369A (en) Improvements in or relating to blades for fluid flow machines
GB1338892A (en) Silencer or muffler for the composite nozzle of an aircraft jet engine
US2884759A (en) Combustion chamber construction

Legal Events

Date Code Title Description
CSNS Application of which complete specification have been accepted and published, but patent is not sealed