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GB723394A - Improvements in turbine blades - Google Patents

Improvements in turbine blades

Info

Publication number
GB723394A
GB723394A GB25423/52A GB2542352A GB723394A GB 723394 A GB723394 A GB 723394A GB 25423/52 A GB25423/52 A GB 25423/52A GB 2542352 A GB2542352 A GB 2542352A GB 723394 A GB723394 A GB 723394A
Authority
GB
United Kingdom
Prior art keywords
blade
walls
brazed
oct
tip
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
GB25423/52A
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 GB723394A publication Critical patent/GB723394A/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
    • 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
    • Y10—TECHNICAL SUBJECTS COVERED BY FORMER USPC
    • Y10T—TECHNICAL SUBJECTS COVERED BY FORMER US CLASSIFICATION
    • Y10T29/00—Metal working
    • Y10T29/49—Method of mechanical manufacture
    • Y10T29/49316—Impeller making

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

723,394. Gas-turbine rotors. GENERAL MOTORS CORPORATION. Oct. 10, 1952 [Oct. 10, 1951], No. 25423/52. Class 110 (3). [Also in Group XXII] A hollow gas-turbine rotor blade of aerofoil cross-section comprises at least one strip welded or brazed along longitudinal surfaces to the opposite internal walls of the blade so as to form longitudinally extending channels therein. The blade comprises a sheet-metal portion 11 brazed at the trailing edge, the walls of the blade preferably tapering towards the tip The blade root is composed of two serrated castings 21, 22 which are brazed to the portion 11. The walls 12, 13 of the blade are bridged by metal strips 17 which preferably extend slightly within the rim of the rotor disc to the tip of the blade. Air is fed to the blade through a passage in the rotor disc. In a modification, the strips 17 are provided with flanges and in a further modification they are replaced by a corrugated strip. The portion 11 may be formed from a tube with tapered walls or constitute a casting.
GB25423/52A 1951-10-10 1952-10-10 Improvements in turbine blades Expired GB723394A (en)

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
US250654A US2817490A (en) 1951-10-10 1951-10-10 Turbine bucket with internal fins

Publications (1)

Publication Number Publication Date
GB723394A true GB723394A (en) 1955-02-09

Family

ID=22948625

Family Applications (1)

Application Number Title Priority Date Filing Date
GB25423/52A Expired GB723394A (en) 1951-10-10 1952-10-10 Improvements in turbine blades

Country Status (2)

Country Link
US (1) US2817490A (en)
GB (1) GB723394A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2828106A (en) * 1955-05-31 1958-03-25 Wilson B Schramm Laminated internal finned air-cooled strut-supported turbine blade
US4056332A (en) * 1975-05-16 1977-11-01 Bbc Brown Boveri & Company Limited Cooled turbine blade
GB2441771A (en) * 2006-09-13 2008-03-19 Rolls Royce Plc Gas turbine engine component cooling

Families Citing this family (11)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3045967A (en) * 1952-04-12 1962-07-24 Stalker Corp Hollow blades and manufacture thereof
US3073568A (en) * 1958-06-27 1963-01-15 Edward A Stalker Composite blades for turbines, compressors and the like
US3029485A (en) * 1959-01-14 1962-04-17 Gen Motors Corp Method of making hollow castings
US3346235A (en) * 1963-12-23 1967-10-10 Papst Hermann Boundary layer control
US3369792A (en) * 1966-04-07 1968-02-20 Gen Electric Airfoil vane
US3950114A (en) * 1968-02-23 1976-04-13 General Motors Corporation Turbine blade
US3653110A (en) * 1970-01-05 1972-04-04 North American Rockwell Method of fabricating hollow blades
DE19963716A1 (en) * 1999-12-29 2001-07-05 Alstom Power Schweiz Ag Baden Cooled flow deflection device for a turbomachine operating at high temperatures
US7713029B1 (en) 2007-03-28 2010-05-11 Florida Turbine Technologies, Inc. Turbine blade with spar and shell construction
US7972113B1 (en) * 2007-05-02 2011-07-05 Florida Turbine Technologies, Inc. Integral turbine blade and platform
FR3071008B1 (en) * 2017-09-11 2019-09-13 Safran Aircraft Engines DRAFT OUTPUT DIRECTOR FOR TURBOMACHINE, COMPRISING A LUBRICANT COOLING PASSAGE EQUIPPED WITH COMPRESSED THERMAL CONDUCTION MATRIX BETWEEN THE INTRADOS AND EXTRADOS WALLS

Family Cites Families (13)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US385384A (en) * 1888-07-03 Method of joining pipes by electricity
US822801A (en) * 1905-09-02 1906-06-05 Wilkinson Turbine Company Turbine bucket-wheel.
US994166A (en) * 1911-02-17 1911-06-06 Arnold Kienast Turbine-blade.
US1706703A (en) * 1923-04-20 1929-03-26 Thomas E Murray Method of production of turbine blandes
US2063706A (en) * 1935-06-14 1936-12-08 Westinghouse Electric & Mfg Co Method of manufacturing blades
US2563269A (en) * 1943-05-22 1951-08-07 Lockheed Aircraft Corp Gas turbine
GB602530A (en) * 1945-10-16 1948-05-28 Bristol Aeroplane Co Ltd Improvements in or relating to gas turbines
CH267499A (en) * 1945-11-30 1950-03-31 Atkinson Joseph Rotor with blades for axial flow machine.
GB625693A (en) * 1946-10-25 1949-07-01 Brush Electrical Eng Improvements in and relating to turbine blades
US2613910A (en) * 1947-01-24 1952-10-14 Edward A Stalker Slotted turbine blade
GB653267A (en) * 1947-12-12 1951-05-09 Mini Of Supply Improvements in and relating to combustion turbines
US2641040A (en) * 1948-01-02 1953-06-09 Esther C Goddard Means for cooling turbine blades by air
US2568726A (en) * 1949-08-03 1951-09-25 Franz Anselm Air-cooled turbine blade

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2828106A (en) * 1955-05-31 1958-03-25 Wilson B Schramm Laminated internal finned air-cooled strut-supported turbine blade
US4056332A (en) * 1975-05-16 1977-11-01 Bbc Brown Boveri & Company Limited Cooled turbine blade
GB2441771A (en) * 2006-09-13 2008-03-19 Rolls Royce Plc Gas turbine engine component cooling
GB2441771B (en) * 2006-09-13 2009-07-08 Rolls Royce Plc Cooling arrangement for a component of a gas turbine engine
US7938624B2 (en) 2006-09-13 2011-05-10 Rolls-Royce Plc Cooling arrangement for a component of a gas turbine engine

Also Published As

Publication number Publication date
US2817490A (en) 1957-12-24

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