GB1190771A - Improvements in or relating to Turbine and Compressor Blades - Google Patents

Improvements in or relating to Turbine and Compressor Blades

Info

Publication number
GB1190771A
GB1190771A GB06245/66A GB1624566A GB1190771A GB 1190771 A GB1190771 A GB 1190771A GB 06245/66 A GB06245/66 A GB 06245/66A GB 1624566 A GB1624566 A GB 1624566A GB 1190771 A GB1190771 A GB 1190771A
Authority
GB
United Kingdom
Prior art keywords
turbine
compressor blades
relating
bore
slot
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
GB06245/66A
Inventor
John Alan Courteney Hyde
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.)
English Electric Co Ltd
Original Assignee
English Electric Co 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 English Electric Co Ltd filed Critical English Electric Co Ltd
Priority to GB06245/66A priority Critical patent/GB1190771A/en
Publication of GB1190771A publication Critical patent/GB1190771A/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
    • F01D5/30—Fixing blades to rotors; Blade roots ; Blade spacers
    • F01D5/3007—Fixing blades to rotors; Blade roots ; Blade spacers of axial insertion type
    • 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
    • F01D5/141—Shape, i.e. outer, aerodynamic form
    • 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
    • F01D5/147—Construction, i.e. structural features, e.g. of weight-saving hollow 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
    • F05D2240/00—Components
    • F05D2240/80—Platforms for stationary or moving blades
    • 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)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Architecture (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

1,190,771. Turbine and compressor blades. ENGLISH ELECTRIC CO. Ltd. July 7, 1967 [April 13, 1966], No. 16245/66. Heading F1T. A turbine or compressor blade has a slot 16 or bore (14), Fig. 2 (not shown), in its platform 11 which is substantially symmetrical about the trailing edge portion 13 and allows thermal expansion of the trailing edge portion. The blade may have platforms at each of its ends, one or both of which have a bore or slot therein.
GB06245/66A 1966-04-13 1966-04-13 Improvements in or relating to Turbine and Compressor Blades Expired GB1190771A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
GB06245/66A GB1190771A (en) 1966-04-13 1966-04-13 Improvements in or relating to Turbine and Compressor Blades

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
GB06245/66A GB1190771A (en) 1966-04-13 1966-04-13 Improvements in or relating to Turbine and Compressor Blades

Publications (1)

Publication Number Publication Date
GB1190771A true GB1190771A (en) 1970-05-06

Family

ID=10073820

Family Applications (1)

Application Number Title Priority Date Filing Date
GB06245/66A Expired GB1190771A (en) 1966-04-13 1966-04-13 Improvements in or relating to Turbine and Compressor Blades

Country Status (1)

Country Link
GB (1) GB1190771A (en)

Cited By (9)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1219778A3 (en) * 2000-12-27 2004-01-07 General Electric Company Gas turbine blade with platform undercut
GB2408077A (en) * 2003-10-31 2005-05-18 Gen Electric Methods and apparatus for cooling gas turbine rotor blades
EP1544410A1 (en) * 2003-12-17 2005-06-22 United Technologies Corporation Turbine blade with trailing edge platform undercut
FR2874402A1 (en) * 2004-08-23 2006-02-24 Snecma Moteurs Sa Rotor blade for compressor/gas turbine of turbine engine, has stiffener connecting platform to blade root, and including notch formed at level of trailing edge, where notch permits to provide relative flexibility to platform
US7121803B2 (en) 2002-12-26 2006-10-17 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
US7165944B2 (en) 2002-12-26 2007-01-23 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
CH699998A1 (en) * 2008-11-26 2010-05-31 Alstom Technology Ltd Guide vane for a gas turbine.
JP2010156331A (en) * 2009-01-02 2010-07-15 General Electric Co <Ge> Method and device for reducing stress of nozzle
US8550783B2 (en) 2011-04-01 2013-10-08 Alstom Technology Ltd. Turbine blade platform undercut

Cited By (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
EP1219778A3 (en) * 2000-12-27 2004-01-07 General Electric Company Gas turbine blade with platform undercut
KR100785541B1 (en) * 2000-12-27 2007-12-12 제너럴 일렉트릭 캄파니 Gas turbine blade with platform undercut
US7121803B2 (en) 2002-12-26 2006-10-17 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
US7165944B2 (en) 2002-12-26 2007-01-23 General Electric Company Compressor blade with dovetail slotted to reduce stress on the airfoil leading edge
US6984112B2 (en) 2003-10-31 2006-01-10 General Electric Company Methods and apparatus for cooling gas turbine rotor blades
GB2408077B (en) * 2003-10-31 2007-08-08 Gen Electric Methods and apparatus for cooling gas turbine rotor blades
GB2408077A (en) * 2003-10-31 2005-05-18 Gen Electric Methods and apparatus for cooling gas turbine rotor blades
US6951447B2 (en) 2003-12-17 2005-10-04 United Technologies Corporation Turbine blade with trailing edge platform undercut
EP1544410A1 (en) * 2003-12-17 2005-06-22 United Technologies Corporation Turbine blade with trailing edge platform undercut
FR2874402A1 (en) * 2004-08-23 2006-02-24 Snecma Moteurs Sa Rotor blade for compressor/gas turbine of turbine engine, has stiffener connecting platform to blade root, and including notch formed at level of trailing edge, where notch permits to provide relative flexibility to platform
CH699998A1 (en) * 2008-11-26 2010-05-31 Alstom Technology Ltd Guide vane for a gas turbine.
WO2010060823A1 (en) * 2008-11-26 2010-06-03 Alstom Technology Ltd. Guide blade for a gas turbine and associated gas turbine
JP2010156331A (en) * 2009-01-02 2010-07-15 General Electric Co <Ge> Method and device for reducing stress of nozzle
US8550783B2 (en) 2011-04-01 2013-10-08 Alstom Technology Ltd. Turbine blade platform undercut

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Legal Events

Date Code Title Description
PS Patent sealed
PLNP Patent lapsed through nonpayment of renewal fees