JPS5510004A - Gas turbine - Google Patents

Gas turbine

Info

Publication number
JPS5510004A
JPS5510004A JP8099078A JP8099078A JPS5510004A JP S5510004 A JPS5510004 A JP S5510004A JP 8099078 A JP8099078 A JP 8099078A JP 8099078 A JP8099078 A JP 8099078A JP S5510004 A JPS5510004 A JP S5510004A
Authority
JP
Japan
Prior art keywords
transition piece
air flow
air
high speed
gas turbine
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
JP8099078A
Other languages
Japanese (ja)
Inventor
Isao Sato
Yoshihiro Uchiyama
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 JP8099078A priority Critical patent/JPS5510004A/en
Publication of JPS5510004A publication Critical patent/JPS5510004A/en
Pending legal-status Critical Current

Links

Abstract

PURPOSE: To enhance a cooling effect of the transition piece with the gas turbine compressed air used, by making an air from the compressor to pass flowing at high speed through a clearance provided between the transition piece and the outside wall.
CONSTITUTION: A compressed air 1, being used as an air flow 20, is conducted into a cobustion liner 6, and mixed with an injected fuel from a fuel nozzle 10, to become burning with an ignition made by a spark plug 12. The combustion gas, after passing through a transition piece 8, is led to a first stage stator blade 14 to perform a work in the turbine. The air flow 20, with an outer wall 18 provided in the outside of the transition piece 8, is divided into an air flow 22 and air flow 21 that passes through a clearance 19, and the high speed air flow 21 works to operates a cooling of the transition piece 8.
COPYRIGHT: (C)1980,JPO&Japio
JP8099078A 1978-07-05 1978-07-05 Gas turbine Pending JPS5510004A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP8099078A JPS5510004A (en) 1978-07-05 1978-07-05 Gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP8099078A JPS5510004A (en) 1978-07-05 1978-07-05 Gas turbine

Publications (1)

Publication Number Publication Date
JPS5510004A true JPS5510004A (en) 1980-01-24

Family

ID=13733929

Family Applications (1)

Application Number Title Priority Date Filing Date
JP8099078A Pending JPS5510004A (en) 1978-07-05 1978-07-05 Gas turbine

Country Status (1)

Country Link
JP (1) JPS5510004A (en)

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5523400A (en) * 1978-08-03 1980-02-19 Bbc Brown Boveri & Cie Cooled highhtemperature gas casing for gas turbine
JPH01200025A (en) * 1988-02-05 1989-08-11 Hitachi Ltd Gas turbine burner and its cooling method
JPH05126335A (en) * 1991-11-07 1993-05-21 Hitachi Ltd Gas turbine combustion controller and gas turbine combustion control method
JP2010159744A (en) * 2009-01-06 2010-07-22 General Electric Co <Ge> Method and apparatus for cooling transition piece
CN104595926A (en) * 2015-01-23 2015-05-06 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Integral combustion chamber for heat-channel components

Cited By (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS5523400A (en) * 1978-08-03 1980-02-19 Bbc Brown Boveri & Cie Cooled highhtemperature gas casing for gas turbine
JPH01200025A (en) * 1988-02-05 1989-08-11 Hitachi Ltd Gas turbine burner and its cooling method
JPH05126335A (en) * 1991-11-07 1993-05-21 Hitachi Ltd Gas turbine combustion controller and gas turbine combustion control method
JP2010159744A (en) * 2009-01-06 2010-07-22 General Electric Co <Ge> Method and apparatus for cooling transition piece
CN104595926A (en) * 2015-01-23 2015-05-06 北京华清燃气轮机与煤气化联合循环工程技术有限公司 Integral combustion chamber for heat-channel components

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