JPS5582233A - Combustion device for gas turbine - Google Patents

Combustion device for gas turbine

Info

Publication number
JPS5582233A
JPS5582233A JP15722678A JP15722678A JPS5582233A JP S5582233 A JPS5582233 A JP S5582233A JP 15722678 A JP15722678 A JP 15722678A JP 15722678 A JP15722678 A JP 15722678A JP S5582233 A JPS5582233 A JP S5582233A
Authority
JP
Japan
Prior art keywords
liner
air
combustion
combustion device
head portion
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
JP15722678A
Other languages
Japanese (ja)
Inventor
Yoji Ishibashi
Yoshimitsu Minagawa
Isao Sato
Tadashi Mizuno
Hidekazu Fujimura
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 JP15722678A priority Critical patent/JPS5582233A/en
Publication of JPS5582233A publication Critical patent/JPS5582233A/en
Pending legal-status Critical Current

Links

Landscapes

  • Turbine Rotor Nozzle Sealing (AREA)

Abstract

PURPOSE: To improve the efficiency of cooling a liner of a combustion device for gas turbines, which liner is doubly formed with respect to a part or the whole of its length, by providing the liner with an inwardly bent head portion of a predetermined curvature.
CONSTITUTION: In a combustion decice 1 for a gas turbine, compressed air 100 from an air compressor 5 is emitted between a high-temperature duct, i.e. a transition piece 4, which communicates a liner 2 with a turbine nozzle 6, and a turbine casing 11 so as to flow backwardly to a head portion of the combustion device 1. This air is supplied into the combustion device for combustion and cooling purposes. The head portion of the liner 2 has two walls 12, 13 the end sections 14 of which are bent inwardly in the liner 2 at a predetermined curvature. Those parts of the end sections 14 which are on the upstream side thereof define slits 15 for passing cooling air therethrough. Namely, a part of air 106 for combustion flows into the liner as cooling air 107 through the slits 15.
COPYRIGHT: (C)1980,JPO&Japio
JP15722678A 1978-12-15 1978-12-15 Combustion device for gas turbine Pending JPS5582233A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP15722678A JPS5582233A (en) 1978-12-15 1978-12-15 Combustion device for gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP15722678A JPS5582233A (en) 1978-12-15 1978-12-15 Combustion device for gas turbine

Publications (1)

Publication Number Publication Date
JPS5582233A true JPS5582233A (en) 1980-06-20

Family

ID=15644972

Family Applications (1)

Application Number Title Priority Date Filing Date
JP15722678A Pending JPS5582233A (en) 1978-12-15 1978-12-15 Combustion device for gas turbine

Country Status (1)

Country Link
JP (1) JPS5582233A (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010209912A (en) * 2009-03-10 2010-09-24 General Electric Co <Ge> Combustor liner cooling system

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2010209912A (en) * 2009-03-10 2010-09-24 General Electric Co <Ge> Combustor liner cooling system

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