JPS6463605A - Gas turbine moving blade - Google Patents

Gas turbine moving blade

Info

Publication number
JPS6463605A
JPS6463605A JP22019987A JP22019987A JPS6463605A JP S6463605 A JPS6463605 A JP S6463605A JP 22019987 A JP22019987 A JP 22019987A JP 22019987 A JP22019987 A JP 22019987A JP S6463605 A JPS6463605 A JP S6463605A
Authority
JP
Japan
Prior art keywords
blade
shank
dovetail
platform
passage
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.)
Pending
Application number
JP22019987A
Other languages
Japanese (ja)
Inventor
Tetsuo Sasada
Haruo Urushiya
Hajime Toritani
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.)
Hitachi Ltd
Original Assignee
Hitachi 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 Hitachi Ltd filed Critical Hitachi Ltd
Priority to JP22019987A priority Critical patent/JPS6463605A/en
Publication of JPS6463605A publication Critical patent/JPS6463605A/en
Pending legal-status Critical Current

Links

Abstract

PURPOSE:To prevent the localized heating condition of a platform member of a blade member end part by providing a cooling passage for introducing cooling air flowing into through a space between adjacent shank members located between the blade member and a dovetail member to a space between the blade members. CONSTITUTION:A high temperature gas turbine moving blade is constituted of a blade member 1, a platform member 2 forming a bottom member of a stream passage between the blades, a dovetail member 4 attaching the blade member 1 to a rotor disc 11, a shank member 3 connecting the blade member 1 to the dovetail member 4. In this occasion, a cutout groove 5 is formed approximately on a center member of the span direction in the inner surface of an end part 2a of a platform 2, located on a belly side of the blade member 1 while forming an introduction hole 6 of cooling air at the boundary member between the shank member 3 and the dovetail member 4. A shank pin 7 for damping is inserted between adjacent blade members 1, 1 so as to form an air passage between the shank pin 7 and the cutout groove 5. Thereby, it is possible to introduce the cooling air 9 to the stream passage between the blades through the cutout groove 5.
JP22019987A 1987-09-04 1987-09-04 Gas turbine moving blade Pending JPS6463605A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP22019987A JPS6463605A (en) 1987-09-04 1987-09-04 Gas turbine moving blade

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP22019987A JPS6463605A (en) 1987-09-04 1987-09-04 Gas turbine moving blade

Publications (1)

Publication Number Publication Date
JPS6463605A true JPS6463605A (en) 1989-03-09

Family

ID=16747441

Family Applications (1)

Application Number Title Priority Date Filing Date
JP22019987A Pending JPS6463605A (en) 1987-09-04 1987-09-04 Gas turbine moving blade

Country Status (1)

Country Link
JP (1) JPS6463605A (en)

Cited By (10)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1996006266A1 (en) * 1994-08-24 1996-02-29 Westinghouse Electric Corporation Gas turbine blade with cooled platform
US6190130B1 (en) * 1998-03-03 2001-02-20 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade platform
GB2408077A (en) * 2003-10-31 2005-05-18 Gen Electric Methods and apparatus for cooling gas turbine rotor blades
JP2005133726A (en) * 2003-10-31 2005-05-26 General Electric Co <Ge> Method and apparatus for cooling gas turbine engine rotor assembly
JP2006070899A (en) * 2004-09-02 2006-03-16 General Electric Co <Ge> Method and device for cooling gas turbine engine rotor assembly
JP2007224919A (en) * 2006-02-24 2007-09-06 General Electric Co <Ge> Method of cooling turbine moving blade and platform for turbine moving blade
US7481614B2 (en) 2004-02-23 2009-01-27 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same
US7758309B2 (en) * 2004-07-09 2010-07-20 Siemens Aktiengesellschaft Vane wheel of turbine comprising a vane and at least one cooling channel
US7811058B2 (en) 2005-11-12 2010-10-12 Rolls-Royce Plc Cooling arrangement
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

Cited By (16)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
WO1996006266A1 (en) * 1994-08-24 1996-02-29 Westinghouse Electric Corporation Gas turbine blade with cooled platform
US5639216A (en) * 1994-08-24 1997-06-17 Westinghouse Electric Corporation Gas turbine blade with cooled platform
US6190130B1 (en) * 1998-03-03 2001-02-20 Mitsubishi Heavy Industries, Ltd. Gas turbine moving blade platform
GB2408077B (en) * 2003-10-31 2007-08-08 Gen Electric Methods and apparatus for cooling gas turbine rotor blades
JP2005133726A (en) * 2003-10-31 2005-05-26 General Electric Co <Ge> Method and apparatus for cooling gas turbine engine rotor assembly
JP2005133723A (en) * 2003-10-31 2005-05-26 General Electric Co <Ge> Method and device for cooling gas turbine rotor blade
US6984112B2 (en) 2003-10-31 2006-01-10 General Electric Company 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
US7600972B2 (en) 2003-10-31 2009-10-13 General Electric Company Methods and apparatus for cooling gas turbine engine rotor assemblies
EP1528224A3 (en) * 2003-10-31 2012-06-13 General Electric Company Method and apparatus for cooling gas turbine engine rotor blade
US7481614B2 (en) 2004-02-23 2009-01-27 Mitsubishi Heavy Industries, Ltd. Moving blade and gas turbine using the same
US7758309B2 (en) * 2004-07-09 2010-07-20 Siemens Aktiengesellschaft Vane wheel of turbine comprising a vane and at least one cooling channel
JP2006070899A (en) * 2004-09-02 2006-03-16 General Electric Co <Ge> Method and device for cooling gas turbine engine rotor assembly
US7811058B2 (en) 2005-11-12 2010-10-12 Rolls-Royce Plc Cooling arrangement
JP2007224919A (en) * 2006-02-24 2007-09-06 General Electric Co <Ge> Method of cooling turbine moving blade and platform for turbine moving blade
US10851661B2 (en) 2017-08-01 2020-12-01 General Electric Company Sealing system for a rotary machine and method of assembling same

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