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GB754217A - Improvements relating to turbine blades - Google Patents

Improvements relating to turbine blades

Info

Publication number
GB754217A
GB754217A GB1375/54A GB137554A GB754217A GB 754217 A GB754217 A GB 754217A GB 1375/54 A GB1375/54 A GB 1375/54A GB 137554 A GB137554 A GB 137554A GB 754217 A GB754217 A GB 754217A
Authority
GB
United Kingdom
Prior art keywords
grooves
blade
halves
passages
root
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
GB1375/54A
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.)
Motors Liquidation Co
Original Assignee
General Motors Corp
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 Motors Corp filed Critical General Motors Corp
Publication of GB754217A publication Critical patent/GB754217A/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
    • F01D5/14—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
    • 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

754,217. Turbine blades. GENERAL MOTORS CORPORATION. Jan. 18 1954 [Jan. 30, 1953], No. 1375/54. Class 110(3) [Also in Group XXII] A turbine blade or nozzle guide vane comprises two halves formed by casting the two halves each having an outer surface forming one side of the aerofoil and root profile and an inner surface having grooves, the two halves being joined together along a spanwise junction surface by a metal fusion process, the grooves forming spanwise cooling passages in the aerofoil portion and duct means in the root by which cooling fluid is supplied to the passages. In Figs. 1 and 5 the turbine rotor blade comprises two halves 17, 18, the abutting surfaces 19 of which are formed with longitudinal grooves. 22, 23 adjacent the leading and trailing edges, and grooves 24 therebetween, which grooves upon assembly form closed passages. The root portion of the blade is formed with passages 31, 33, 34 which communicate with the longitudinal passages 22, 23, 24 so that cooling fluid such as air supplied through the passage 32 in the rotor can flow through the blade and discharge at the tip. The ribs 26 between the grooves provide a large heat exchange surface. The abutting surfaces are connected by brazing. In a second embodiment. Figs. 6 and 10 the two blade halves do not abut face to face but a metal sheet 38 is interposed therebetween and is bonded to each of the blade halves. Also. the larger grooves 22, 23 are omitted. The grooves 24<SP>1</SP> extend from the blade root to the tip. but the grooves 37 extend only to an intermediate point along the blade. The sheet 38 is cut away towards the tip of the trailing edge so that a narrow space is formed into which the grooves 37 discharge. Cooling air is supplied as in the first embodiment.
GB1375/54A 1953-01-30 1954-01-18 Improvements relating to turbine blades Expired GB754217A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US323718XA 1953-01-30 1953-01-30

Publications (1)

Publication Number Publication Date
GB754217A true GB754217A (en) 1956-08-08

Family

ID=21864607

Family Applications (1)

Application Number Title Priority Date Filing Date
GB1375/54A Expired GB754217A (en) 1953-01-30 1954-01-18 Improvements relating to turbine blades

Country Status (3)

Country Link
CH (1) CH323718A (en)
FR (1) FR1092136A (en)
GB (1) GB754217A (en)

Cited By (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2923525A (en) * 1958-04-04 1960-02-02 Orenda Engines Ltd Hollow gas turbine blade
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US3044745A (en) * 1956-11-20 1962-07-17 Rolls Royce Turbine and compressor blades
US5259730A (en) * 1991-11-04 1993-11-09 General Electric Company Impingement cooled airfoil with bonding foil insert
EP1122405A2 (en) 2000-02-02 2001-08-08 General Electric Company Gas turbine bucket cooling circuit
FR2859235A1 (en) * 2003-09-03 2005-03-04 Gen Electric LOCATION, MODEL AND CONFIGURATION OF THE COOLING HOLES OF THE SUSTAINING PLAN OF A TURBINE FIN
CN103216273A (en) * 2013-04-17 2013-07-24 北京航空航天大学 Efficient cooling turbine blade taking inner cooling channel surface as flow direction micro groove surface
EP2141326A3 (en) * 2008-07-03 2013-12-25 United Technologies Corporation Airfoil with tapered radial cooling passage

Families Citing this family (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB893706A (en) * 1960-01-05 1962-04-11 Rolls Royce Blades for fluid flow machines
DE1173732B (en) * 1960-06-08 1964-07-09 Gen Motors Corp Cast turbine blade
GB2051964B (en) * 1979-06-30 1983-01-12 Rolls Royce Turbine blade

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3044745A (en) * 1956-11-20 1962-07-17 Rolls Royce Turbine and compressor blades
US3017159A (en) * 1956-11-23 1962-01-16 Curtiss Wright Corp Hollow blade construction
US2923525A (en) * 1958-04-04 1960-02-02 Orenda Engines Ltd Hollow gas turbine blade
US5259730A (en) * 1991-11-04 1993-11-09 General Electric Company Impingement cooled airfoil with bonding foil insert
EP1122405A2 (en) 2000-02-02 2001-08-08 General Electric Company Gas turbine bucket cooling circuit
EP1122405A3 (en) * 2000-02-02 2004-01-07 General Electric Company Gas turbine bucket cooling circuit
FR2859235A1 (en) * 2003-09-03 2005-03-04 Gen Electric LOCATION, MODEL AND CONFIGURATION OF THE COOLING HOLES OF THE SUSTAINING PLAN OF A TURBINE FIN
EP2141326A3 (en) * 2008-07-03 2013-12-25 United Technologies Corporation Airfoil with tapered radial cooling passage
CN103216273A (en) * 2013-04-17 2013-07-24 北京航空航天大学 Efficient cooling turbine blade taking inner cooling channel surface as flow direction micro groove surface

Also Published As

Publication number Publication date
FR1092136A (en) 1955-04-19
CH323718A (en) 1957-08-15

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