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GB1070475A - Improvements in hollow turbine or compressor stator vane or rotor blade - Google Patents

Improvements in hollow turbine or compressor stator vane or rotor blade

Info

Publication number
GB1070475A
GB1070475A GB32468/64A GB3246864A GB1070475A GB 1070475 A GB1070475 A GB 1070475A GB 32468/64 A GB32468/64 A GB 32468/64A GB 3246864 A GB3246864 A GB 3246864A GB 1070475 A GB1070475 A GB 1070475A
Authority
GB
United Kingdom
Prior art keywords
blade
aperture
cooling air
compressor
aug
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
GB32468/64A
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 GB1070475A publication Critical patent/GB1070475A/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
    • 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
    • F05D2260/2214—Improvement of heat transfer by increasing the heat transfer surface
    • F05D2260/22141—Improvement of heat transfer by increasing the heat transfer surface using fins or ribs
    • 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

1,070,475. Turbine and compressor blades. GENERAL ELECTRIC CO. Aug.10, 1964 [Aug.30, 1963], No. 32468/64. Heading F1T. A hollow gas turbine nozzle blade 50 has staggered internal transverse baffles 55 integral with the blade walls to form a pair of radially extending serpentine cooling air paths. Cooling air is supplied from the engine compressor to an annular manifold 37 and enters each blade 50 through an aperture 60, exhaust being through aperture 61. In a modification, Fig. 5 (not shown), a radial partition (65) divides the interior of each blade (50') into regions (66, 67) adjacent the leading and trailing edges (51', 52') respectively. Cooling air is supplied through an aperture (60') to flow past baffles (69) in leading edge region (66) and through a passageway (68) in the partition (65) to exhaust through apertures (70) in the trailing edge. The invention is applicable also to rotor blades, Fig.10 (not shown), and to the supply of heating air to compressor inlet guide blades.
GB32468/64A 1963-08-30 1964-08-10 Improvements in hollow turbine or compressor stator vane or rotor blade Expired GB1070475A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US305695A US3220697A (en) 1963-08-30 1963-08-30 Hollow turbine or compressor vane

Publications (1)

Publication Number Publication Date
GB1070475A true GB1070475A (en) 1967-06-01

Family

ID=23181920

Family Applications (1)

Application Number Title Priority Date Filing Date
GB32468/64A Expired GB1070475A (en) 1963-08-30 1964-08-10 Improvements in hollow turbine or compressor stator vane or rotor blade

Country Status (3)

Country Link
US (1) US3220697A (en)
DE (1) DE1265495B (en)
GB (1) GB1070475A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2311176A1 (en) * 1975-05-16 1976-12-10 Bbc Brown Boveri & Cie COOLED TURBINE FIN
GB2163219A (en) * 1981-10-31 1986-02-19 Rolls Royce Cooled turbine blade

Families Citing this family (34)

* 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
US3630707A (en) * 1969-06-11 1971-12-28 Corning Glass Works Temperature control system for glass-shaping molds
US3628885A (en) * 1969-10-01 1971-12-21 Gen Electric Fluid-cooled airfoil
US3849025A (en) * 1973-03-28 1974-11-19 Gen Electric Serpentine cooling channel construction for open-circuit liquid cooled turbine buckets
US3844679A (en) * 1973-03-28 1974-10-29 Gen Electric Pressurized serpentine cooling channel construction for open-circuit liquid cooled turbine buckets
US4173120A (en) * 1977-09-09 1979-11-06 International Harvester Company Turbine nozzle and rotor cooling systems
US4752186A (en) * 1981-06-26 1988-06-21 United Technologies Corporation Coolable wall configuration
US4721433A (en) * 1985-12-19 1988-01-26 United Technologies Corporation Coolable stator structure for a gas turbine engine
US4820122A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
US4820123A (en) * 1988-04-25 1989-04-11 United Technologies Corporation Dirt removal means for air cooled blades
US5488825A (en) * 1994-10-31 1996-02-06 Westinghouse Electric Corporation Gas turbine vane with enhanced cooling
JP4096706B2 (en) * 2002-11-13 2008-06-04 株式会社Ｉｈｉ Thin and lightweight cooling turbine blade
FR2857699B1 (en) * 2003-07-17 2007-06-29 Snecma Moteurs DEFROSTING DEVICE FOR TURBOMACHINE INPUT DIRECTION WHEEL DARK, DAWN WITH SUCH A DEFROSTING DEVICE, AND AIRCRAFT ENGINE EQUIPPED WITH SUCH AUBES
US7753650B1 (en) 2006-12-20 2010-07-13 Florida Turbine Technologies, Inc. Thin turbine rotor blade with sinusoidal flow cooling channels
US7682133B1 (en) * 2007-04-03 2010-03-23 Florida Turbine Technologies, Inc. Cooling circuit for a large highly twisted and tapered rotor blade
US8047788B1 (en) * 2007-10-19 2011-11-01 Florida Turbine Technologies, Inc. Turbine airfoil with near-wall serpentine cooling
US8616834B2 (en) * 2010-04-30 2013-12-31 General Electric Company Gas turbine engine airfoil integrated heat exchanger
EP2392775A1 (en) 2010-06-07 2011-12-07 Siemens Aktiengesellschaft Blade for use in a fluid flow of a turbine engine and turbine engine
US9476313B2 (en) * 2012-12-21 2016-10-25 United Technologies Corporation Gas turbine engine including a pre-diffuser heat exchanger
US9995147B2 (en) * 2015-02-11 2018-06-12 United Technologies Corporation Blade tip cooling arrangement
US20170159568A1 (en) * 2015-12-03 2017-06-08 General Electric Company Intercooling system and method for a gas turbine engine
US10598028B2 (en) 2016-10-26 2020-03-24 General Electric Company Edge coupon including cooling circuit for airfoil
US10352176B2 (en) * 2016-10-26 2019-07-16 General Electric Company Cooling circuits for a multi-wall blade
US10465521B2 (en) 2016-10-26 2019-11-05 General Electric Company Turbine airfoil coolant passage created in cover
US10273810B2 (en) 2016-10-26 2019-04-30 General Electric Company Partially wrapped trailing edge cooling circuit with pressure side serpentine cavities
US10450875B2 (en) 2016-10-26 2019-10-22 General Electric Company Varying geometries for cooling circuits of turbine blades
US10301946B2 (en) 2016-10-26 2019-05-28 General Electric Company Partially wrapped trailing edge cooling circuits with pressure side impingements
US10309227B2 (en) 2016-10-26 2019-06-04 General Electric Company Multi-turn cooling circuits for turbine blades
US10450950B2 (en) 2016-10-26 2019-10-22 General Electric Company Turbomachine blade with trailing edge cooling circuit
US10233761B2 (en) 2016-10-26 2019-03-19 General Electric Company Turbine airfoil trailing edge coolant passage created by cover
US11168702B2 (en) * 2017-08-10 2021-11-09 Raytheon Technologies Corporation Rotating airfoil with tip pocket
US11814965B2 (en) 2021-11-10 2023-11-14 General Electric Company Turbomachine blade trailing edge cooling circuit with turn passage having set of obstructions
US11692448B1 (en) * 2022-03-04 2023-07-04 General Electric Company Passive valve assembly for a nozzle of a gas turbine engine
US20240141836A1 (en) * 2022-10-28 2024-05-02 Pratt & Whitney Canada Corp. Gas turbine engine component with integral heat exchanger

Family Cites Families (20)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE904610C (en) * 1944-04-22 1954-02-22 Siemens Ag Air-cooled hollow blade for gas turbines, in which the cooling air enters the blade from the blade root
NL142752B (en) * 1947-10-28 Tone Boring Co EXCAVATOR.
DE876936C (en) * 1948-10-01 1953-04-02 Aachen Dr.-Ing. Karl Leist Working procedure for gas turbines and gas turbine for carrying out the procedure
FR981599A (en) * 1948-12-31 1951-05-28 Vibration damping device
NL73916C (en) * 1949-07-06 1900-01-01
CH292537A (en) * 1950-10-03 1953-08-15 Rohrbach Hans Ing Dr Impeller for gas and steam turbines.
US2699598A (en) * 1952-02-08 1955-01-18 Utica Drop Forge & Tool Corp Method of making turbine blades
US2801073A (en) * 1952-06-30 1957-07-30 United Aircraft Corp Hollow sheet metal blade or vane construction
GB753224A (en) * 1953-04-13 1956-07-18 Rolls Royce Improvements in or relating to blading for turbines or compressors
US2879028A (en) * 1954-03-31 1959-03-24 Edward A Stalker Cooled turbine blades
US2920866A (en) * 1954-12-20 1960-01-12 A V Roe Canada Ltd Hollow air cooled sheet metal turbine blade
BE557503A (en) * 1956-05-15
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
GB855058A (en) * 1957-02-22 1960-11-30 Rolls Royce Improvements in or relating to bladed rotor or stator constructions for axial-flow fluid machines for example for compressors or turbines of gas-turbine engines
US2973937A (en) * 1958-03-31 1961-03-07 Gen Electric Cooling structure
GB856983A (en) * 1958-06-18 1960-12-21 Rolls Royce Improvements in the formation of holes by spark erosion
US3045965A (en) * 1959-04-27 1962-07-24 Rolls Royce Turbine blades, vanes and the like
GB895077A (en) * 1959-12-09 1962-05-02 Rolls Royce Blades for fluid flow machines such as axial flow turbines
GB910400A (en) * 1960-11-23 1962-11-14 Entwicklungsbau Pirna Veb Improvements in or relating to blades for axial flow rotary machines and the like
US3123283A (en) * 1962-12-07 1964-03-03 Anti-icing valve means

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
FR2311176A1 (en) * 1975-05-16 1976-12-10 Bbc Brown Boveri & Cie COOLED TURBINE FIN
GB2163219A (en) * 1981-10-31 1986-02-19 Rolls Royce Cooled turbine blade

Also Published As

Publication number Publication date
DE1265495B (en) 1968-04-04
US3220697A (en) 1965-11-30

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