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JPS5581232A - Method of cooling combustor for gas turbine - Google Patents

Method of cooling combustor for gas turbine

Info

Publication number
JPS5581232A
JPS5581232A JP15719978A JP15719978A JPS5581232A JP S5581232 A JPS5581232 A JP S5581232A JP 15719978 A JP15719978 A JP 15719978A JP 15719978 A JP15719978 A JP 15719978A JP S5581232 A JPS5581232 A JP S5581232A
Authority
JP
Japan
Prior art keywords
transition piece
gas turbine
air
double
passed
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.)
Granted
Application number
JP15719978A
Other languages
Japanese (ja)
Other versions
JPS6142166B2 (en
Inventor
Isao Sato
Yoshihiro Uchiyama
Yoji Ishibashi
Fumio Kato
Tadashi Mizuno
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 JP15719978A priority Critical patent/JPS5581232A/en
Publication of JPS5581232A publication Critical patent/JPS5581232A/en
Publication of JPS6142166B2 publication Critical patent/JPS6142166B2/ja
Granted legal-status Critical Current

Links

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE: To cool hot inner wall surface of transition piece efficiently, by constituting the transition piece in a double metal-wall structure and passing air at a high speed through the space formed between the double walls.
CONSTITUTION: Transition piece 6 is formed in a double structure having cover 16 on its outside. Therefore, a portion of air 14 supplied from compressor 1 is passed through the space formed between the double walls and cools the transition piece 6. Air 15 passed through transition piece 6 is then used to cool first-stage stator blades 17 and first-stage rotor blades 13.
COPYRIGHT: (C)1980,JPO&Japio
JP15719978A 1978-12-15 1978-12-15 Method of cooling combustor for gas turbine Granted JPS5581232A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP15719978A JPS5581232A (en) 1978-12-15 1978-12-15 Method of cooling combustor for gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP15719978A JPS5581232A (en) 1978-12-15 1978-12-15 Method of cooling combustor for gas turbine

Publications (2)

Publication Number Publication Date
JPS5581232A true JPS5581232A (en) 1980-06-19
JPS6142166B2 JPS6142166B2 (en) 1986-09-19

Family

ID=15644359

Family Applications (1)

Application Number Title Priority Date Filing Date
JP15719978A Granted JPS5581232A (en) 1978-12-15 1978-12-15 Method of cooling combustor for gas turbine

Country Status (1)

Country Link
JP (1) JPS5581232A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS62102029A (en) * 1985-10-30 1987-05-12 Toshiba Corp Gas turbine combustion unit

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JPS62102029A (en) * 1985-10-30 1987-05-12 Toshiba Corp Gas turbine combustion unit
JPH0726734B2 (en) * 1985-10-30 1995-03-29 株式会社東芝 Gas turbine combustor

Also Published As

Publication number Publication date
JPS6142166B2 (en) 1986-09-19

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