GB728834A - Cooling of turbine blades - Google Patents

Cooling of turbine blades

Info

Publication number
GB728834A
GB728834A GB14028/52A GB1402852A GB728834A GB 728834 A GB728834 A GB 728834A GB 14028/52 A GB14028/52 A GB 14028/52A GB 1402852 A GB1402852 A GB 1402852A GB 728834 A GB728834 A GB 728834A
Authority
GB
United Kingdom
Prior art keywords
passage
fin
fins
insert
pitch
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
GB14028/52A
Inventor
Austin Geoffrey Smith
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.)
Power Jets Research and Development Ltd
Original Assignee
Power Jets Research and Development Ltd
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 Power Jets Research and Development Ltd filed Critical Power Jets Research and Development Ltd
Publication of GB728834A publication Critical patent/GB728834A/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
    • 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
    • F05D2250/00—Geometry
    • F05D2250/20—Three-dimensional
    • F05D2250/25—Three-dimensional helical
    • 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
    • F05D2260/00—Function
    • F05D2260/20—Heat transfer, e.g. cooling
    • F05D2260/221—Improvement of heat transfer
    • F05D2260/2212—Improvement of heat transfer by creating turbulence

Abstract

728,834. Turbine blades. POWER JETS (RESEARCH & DEVELOPMENT), Ltd. June 1, 1953 [June 3, 1952], No. 14028/52. Addition to 680,118. Class 110 (3). A turbine blade has a longitudinally-extending internal passage 1a therethrough for the flow of cooling fluid and a formed insert 2 which is formed separately from the blade is placed in the passage with the fin or fins in good heat-conducting relationship with the wall of the passage, the pitch of the fin or fins varying along at least a part of the length of the passage. The insert shown in Fig. 2 has a core 2b and a continuous helical fin 2a of varying pitch. In a second embodiment, the insert has a plurality of radially projecting fins spaced at varying pitch. The pitch of the fin or fins may be least towards the blade tip end of the passage so that the heat conductance increases progressively towards the tip end. The fin or fins of the insert may be bonded to the wall of the passage to ensure good heatconducting relationship. Specification. 651,830 is referred to.
GB14028/52A 1949-07-06 1952-06-03 Cooling of turbine blades Expired GB728834A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB286626X 1949-07-06

Publications (1)

Publication Number Publication Date
GB728834A true GB728834A (en) 1955-04-27

Family

ID=10279147

Family Applications (2)

Application Number Title Priority Date Filing Date
GB17900/49A Expired GB680118A (en) 1949-07-06 1949-07-06 Improvements in or relating to turbine and like blades
GB14028/52A Expired GB728834A (en) 1949-07-06 1952-06-03 Cooling of turbine blades

Family Applications Before (1)

Application Number Title Priority Date Filing Date
GB17900/49A Expired GB680118A (en) 1949-07-06 1949-07-06 Improvements in or relating to turbine and like blades

Country Status (6)

Country Link
US (1) US2843354A (en)
BE (1) BE496812A (en)
CH (1) CH286626A (en)
FR (2) FR1022398A (en)
GB (2) GB680118A (en)
NL (1) NL73916C (en)

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3370829A (en) * 1965-12-20 1968-02-27 Avco Corp Gas turbine blade construction
US4080095A (en) * 1976-09-02 1978-03-21 Westinghouse Electric Corporation Cooled turbine vane
US4119390A (en) * 1976-11-19 1978-10-10 General Electric Company Liquid-cooled, turbine bucket with enhanced heat transfer performance
US4383854A (en) * 1980-12-29 1983-05-17 General Electric Company Method of creating a controlled interior surface configuration of passages within a substrate
US4684322A (en) * 1981-10-31 1987-08-04 Rolls-Royce Plc Cooled turbine blade
GB2238582A (en) * 1989-10-02 1991-06-05 Gen Electric Internally cooled airfoil blade.
US5253976A (en) * 1991-11-19 1993-10-19 General Electric Company Integrated steam and air cooling for combined cycle gas turbines
US5320483A (en) * 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
EP0641917A1 (en) * 1993-09-08 1995-03-08 United Technologies Corporation Leading edge cooling of airfoils
US5993156A (en) * 1997-06-26 1999-11-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Snecma Turbine vane cooling system
US8864438B1 (en) * 2013-12-05 2014-10-21 Siemens Energy, Inc. Flow control insert in cooling passage for turbine vane

Families Citing this family (27)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2921769A (en) * 1953-06-08 1960-01-19 Peerless Turbine Corp Turbine rotor
GB778672A (en) * 1954-10-18 1957-07-10 Parsons & Marine Eng Turbine Improvements in and relating to the cooling of bodies subject to a hot gas stream, for example turbine blades
US2999669A (en) * 1958-11-21 1961-09-12 Westinghouse Electric Corp Damping apparatus
GB895077A (en) * 1959-12-09 1962-05-02 Rolls Royce Blades for fluid flow machines such as axial flow turbines
US3220697A (en) * 1963-08-30 1965-11-30 Gen Electric Hollow turbine or compressor vane
FR2098558A5 (en) * 1970-07-20 1972-03-10 Onera (Off Nat Aerospatiale)
NL7712519A (en) * 1976-11-19 1978-05-23 Gen Electric LIQUID COOLED TURBINE BLADE WITH IMPROVED HEAT TRANSFER BEHAVIOR.
US4142831A (en) * 1977-06-15 1979-03-06 General Electric Company Liquid-cooled turbine bucket with enhanced heat transfer performance
DE3416087A1 (en) * 1984-04-30 1985-10-31 Klöckner-Humboldt-Deutz AG, 5000 Köln COOLED TURBINE BLADE
US5704763A (en) * 1990-08-01 1998-01-06 General Electric Company Shear jet cooling passages for internally cooled machine elements
EP1621730B1 (en) * 2004-07-26 2008-10-08 Siemens Aktiengesellschaft Cooled turbomachinery element and casting method thereof
US7163373B2 (en) * 2005-02-02 2007-01-16 Siemens Power Generation, Inc. Vortex dissipation device for a cooling system within a turbine blade of a turbine engine
US8297927B1 (en) * 2008-03-04 2012-10-30 Florida Turbine Technologies, Inc. Near wall multiple impingement serpentine flow cooled airfoil
EP2372087A1 (en) * 2010-03-26 2011-10-05 Siemens Aktiengesellschaft Components with an external wall which can be exposed to a hot gas of a gas turbine and method for producing such a component
DE102012017491A1 (en) * 2012-09-04 2014-03-06 Rolls-Royce Deutschland Ltd & Co Kg Turbine blade of a gas turbine with swirl-generating element
GB2518379A (en) * 2013-09-19 2015-03-25 Rolls Royce Deutschland Aerofoil cooling system and method
US9932835B2 (en) * 2014-05-23 2018-04-03 United Technologies Corporation Airfoil cooling device and method of manufacture
JP6347893B2 (en) * 2014-07-24 2018-06-27 シーメンス アクチエンゲゼルシヤフトＳｉｅｍｅｎｓ Ａｋｔｉｅｎｇｅｓｅｌｌｓｃｈａｆｔ Turbine blade cooling system with a flow blocker extending in the blade length direction
EP3350414A1 (en) * 2015-11-10 2018-07-25 Siemens Aktiengesellschaft Laminated airfoil for a gas turbine
PL232314B1 (en) * 2016-05-06 2019-06-28 Gen Electric Fluid-flow machine equipped with the clearance adjustment system
US10309246B2 (en) 2016-06-07 2019-06-04 General Electric Company Passive clearance control system for gas turbomachine
US10605093B2 (en) 2016-07-12 2020-03-31 General Electric Company Heat transfer device and related turbine airfoil
US10392944B2 (en) 2016-07-12 2019-08-27 General Electric Company Turbomachine component having impingement heat transfer feature, related turbomachine and storage medium
US10738622B2 (en) 2016-08-09 2020-08-11 General Electric Company Components having outer wall recesses for impingement cooling
US11149550B2 (en) * 2019-02-07 2021-10-19 Raytheon Technologies Corporation Blade neck transition
US10871074B2 (en) 2019-02-28 2020-12-22 Raytheon Technologies Corporation Blade/vane cooling passages
CN112483191B (en) * 2020-11-30 2022-07-19 日照黎阳工业装备有限公司 Turbine blade suitable for gas turbine possesses heat convection function

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US970349A (en) * 1910-02-25 1910-09-13 Theodore B Stubbs Crude-oil burner.
US1864742A (en) * 1923-06-15 1932-06-28 Charles N Koch Combustion turbine and method of burning fuel
US1928504A (en) * 1932-01-09 1933-09-26 Holzwarth Gas Turbine Co Cooled nozzle segment for combustion gas turbines
US2043644A (en) * 1933-09-21 1936-06-09 Cyril C Young Heat transfer apparatus
GB426885A (en) * 1933-11-03 1935-04-11 Dewandre Co Ltd C Improvements in or relating to heat transmitting tubes
CH213483A (en) * 1938-11-23 1941-02-15 Porsche Kg Impeller for internal combustion or steam turbines and process for producing the same.
US2297446A (en) * 1938-12-03 1942-09-29 Zellbeck Gustav Hollow blade for exhaust gas turbine rotors
US2407531A (en) * 1942-05-02 1946-09-10 Fed Reserve Bank Elastic fluid mechanism
US2520373A (en) * 1945-01-24 1950-08-29 Lockheed Aircraft Corp Turbine blade and method of making the same
GB625693A (en) * 1946-10-25 1949-07-01 Brush Electrical Eng Improvements in and relating to turbine blades
US2581252A (en) * 1947-12-31 1952-01-01 Sintercast Corp America Powder metallurgy articles
US2665881A (en) * 1948-06-15 1954-01-12 Chrysler Corp Cooled turbine blade
US2568726A (en) * 1949-08-03 1951-09-25 Franz Anselm Air-cooled turbine blade

Cited By (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3370829A (en) * 1965-12-20 1968-02-27 Avco Corp Gas turbine blade construction
US4080095A (en) * 1976-09-02 1978-03-21 Westinghouse Electric Corporation Cooled turbine vane
US4119390A (en) * 1976-11-19 1978-10-10 General Electric Company Liquid-cooled, turbine bucket with enhanced heat transfer performance
US4383854A (en) * 1980-12-29 1983-05-17 General Electric Company Method of creating a controlled interior surface configuration of passages within a substrate
US4684322A (en) * 1981-10-31 1987-08-04 Rolls-Royce Plc Cooled turbine blade
GB2238582A (en) * 1989-10-02 1991-06-05 Gen Electric Internally cooled airfoil blade.
US5253976A (en) * 1991-11-19 1993-10-19 General Electric Company Integrated steam and air cooling for combined cycle gas turbines
US5320483A (en) * 1992-12-30 1994-06-14 General Electric Company Steam and air cooling for stator stage of a turbine
EP0641917A1 (en) * 1993-09-08 1995-03-08 United Technologies Corporation Leading edge cooling of airfoils
US5993156A (en) * 1997-06-26 1999-11-30 Societe Nationale D'etude Et De Construction De Moteurs D'aviation Snecma Turbine vane cooling system
US8864438B1 (en) * 2013-12-05 2014-10-21 Siemens Energy, Inc. Flow control insert in cooling passage for turbine vane

Also Published As

Publication number Publication date
US2843354A (en) 1958-07-15
FR66874E (en) 1957-10-31
NL73916C (en) 1900-01-01
CH286626A (en) 1952-10-31
BE496812A (en) 1900-01-01
GB680118A (en) 1952-10-01
FR1022398A (en) 1953-03-04

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