GB1097300A - Improvements in gas turbine blades - Google Patents

Improvements in gas turbine blades

Info

Publication number
GB1097300A
GB1097300A GB55518/66A GB5551866A GB1097300A GB 1097300 A GB1097300 A GB 1097300A GB 55518/66 A GB55518/66 A GB 55518/66A GB 5551866 A GB5551866 A GB 5551866A GB 1097300 A GB1097300 A GB 1097300A
Authority
GB
United Kingdom
Prior art keywords
blade
air
supplied
gas turbine
fins
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
GB55518/66A
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.)
Daimler Benz AG
Original Assignee
Daimler Benz AG
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 Daimler Benz AG filed Critical Daimler Benz AG
Publication of GB1097300A publication Critical patent/GB1097300A/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
    • 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
    • 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

1,097,300. Gas turbine blades. DAIMLERBENZ A.G. Dec.12, 1966 [Dec. 11, 1965], No. 55518/66. Heading F1T. An air cooled gas turbine blade 10 has fins 11 on its internal surface extending parallel to the direction of flow of working gas past the blade and a hollow internal member 12 to which the cooling air is supplied. The air is directed by radial or transverse slits 17, (16) in the leading edge of the member 12 to impinge on the interior surface 18 of the blade leading edge before flowing rearwardly past the fins 11 to exhaust into the working gas stream through radial slits 21, (20, 22) in the blade trailing edge 19. In the case of a guide blade, shown, the cooling air is supplied to the radially outer end of member 13, a plate 15 sealing the inner end, whereas a rotor blade is supplied with air at its radially inner end. Member 12 may be a sheet metal insert or cast in position. Alternatively, a small tube may be used.
GB55518/66A 1965-12-11 1966-12-12 Improvements in gas turbine blades Expired GB1097300A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
DED0048895 1965-12-11

Publications (1)

Publication Number Publication Date
GB1097300A true GB1097300A (en) 1968-01-03

Family

ID=7051492

Family Applications (1)

Application Number Title Priority Date Filing Date
GB55518/66A Expired GB1097300A (en) 1965-12-11 1966-12-12 Improvements in gas turbine blades

Country Status (3)

Country Link
US (1) US3373970A (en)
FR (1) FR1503348A (en)
GB (1) GB1097300A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4623087A (en) * 1983-05-26 1986-11-18 Rolls-Royce Limited Application of coatings to articles
JPH0749001A (en) * 1994-02-07 1995-02-21 Toshiba Corp Gas turbine blade
JPH0756201B2 (en) 1984-03-13 1995-06-14 株式会社東芝 Gas turbine blades

Families Citing this family (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3574481A (en) * 1968-05-09 1971-04-13 James A Pyne Jr Variable area cooled airfoil construction for gas turbines
BE755567A (en) * 1969-12-01 1971-02-15 Gen Electric FIXED VANE STRUCTURE, FOR GAS TURBINE ENGINE AND ASSOCIATED TEMPERATURE ADJUSTMENT ARRANGEMENT
GB1304678A (en) * 1971-06-30 1973-01-24
CH582305A5 (en) * 1974-09-05 1976-11-30 Bbc Sulzer Turbomaschinen
FR2476207A1 (en) * 1980-02-19 1981-08-21 Snecma IMPROVEMENT TO AUBES OF COOLED TURBINES
US5203873A (en) * 1991-08-29 1993-04-20 General Electric Company Turbine blade impingement baffle
ITTO20010704A1 (en) * 2001-07-18 2003-01-18 Fiatavio Spa DOUBLE WALL VANE FOR A TURBINE, PARTICULARLY FOR AERONAUTICAL APPLICATIONS.
GB2386926A (en) * 2002-03-27 2003-10-01 Alstom Two part impingement tube for a turbine blade or vane
GB2395232B (en) * 2002-11-12 2006-01-25 Rolls Royce Plc Turbine components
US7258528B2 (en) * 2004-12-02 2007-08-21 Pratt & Whitney Canada Corp. Internally cooled airfoil for a gas turbine engine and method
US8961133B2 (en) 2010-12-28 2015-02-24 Rolls-Royce North American Technologies, Inc. Gas turbine engine and cooled airfoil
FR3021698B1 (en) * 2014-05-28 2021-07-02 Snecma TURBINE BLADE, INCLUDING A CENTRAL COOLING DUCT THERMALLY INSULATED FROM THE BLADE WALLS BY TWO JOINT SIDE CAVITIES DOWNSTREAM FROM THE CENTRAL DUCT
FR3021697B1 (en) * 2014-05-28 2021-09-17 Snecma OPTIMIZED COOLING TURBINE BLADE

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
DE767546C (en) * 1938-09-12 1952-11-04 Bmw Flugmotorenbau G M B H Internally cooled turbine blade
US2514105A (en) * 1945-12-07 1950-07-04 Thomas Wilfred Airfoil conditioning means
US2858100A (en) * 1952-02-01 1958-10-28 Stalker Dev Company Blade structure for turbines and the like
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
FR1177035A (en) * 1957-05-28 1959-04-20 Snecma Method and device for cooling machine parts

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US4623087A (en) * 1983-05-26 1986-11-18 Rolls-Royce Limited Application of coatings to articles
JPH0756201B2 (en) 1984-03-13 1995-06-14 株式会社東芝 Gas turbine blades
JPH0749001A (en) * 1994-02-07 1995-02-21 Toshiba Corp Gas turbine blade
JP2609805B2 (en) 1994-02-07 1997-05-14 株式会社東芝 Gas turbine blades

Also Published As

Publication number Publication date
US3373970A (en) 1968-03-19
FR1503348A (en) 1967-11-24

Similar Documents

Publication Publication Date Title
GB1097300A (en) Improvements in gas turbine blades
GB1357713A (en) Cooled rotor blades for gas turbines
GB1101543A (en) Improvements in turbine diaphragm structure
GB1331206A (en) Vane structure for gas turbine
US3782852A (en) Gas turbine engine blades
GB1282796A (en) Fluid cooled turbine blade
GB1225926A (en)
GB989217A (en) Turbine blades
GB1177410A (en) Improvements in Gas Turbine Engine Turbine Rotor Shrouds
GB1144036A (en) A vane for an aerial flow turbomachine
GB1359983A (en) Cooled guide blades for gas turbines
FR2181407A5 (en)
GB1489098A (en) Gas turbines
GB1271819A (en) Improvements in film cooling of structural members in gas turbine engines
GB1261765A (en) Improvements in axial flow turbomachinery vanes
GB1514613A (en) Blade or vane for a gas turbine engine
GB1351029A (en) Turbo machinery blade cooling
GB1125920A (en) Turbomachine rotors
GB1218371A (en) Improvements in or relating to aerofoil vanes or blades for high temperature use
GB1068280A (en) Aerofoil-shaped blade for use in a fluid flow machine such as a turbine
GB1304678A (en)
GB650437A (en) Improvements in and relating to the manufacture and attachment of turbine blading
GB1222565A (en) Gas turbine guide blade
GB1285369A (en) Improvements in or relating to blades for fluid flow machines
GB1126020A (en) Fluid directing structures, applicable for example, to gas turbine engines