JPS5634027A - Burner for gas turbine - Google Patents

Burner for gas turbine

Info

Publication number
JPS5634027A
JPS5634027A JP10811579A JP10811579A JPS5634027A JP S5634027 A JPS5634027 A JP S5634027A JP 10811579 A JP10811579 A JP 10811579A JP 10811579 A JP10811579 A JP 10811579A JP S5634027 A JPS5634027 A JP S5634027A
Authority
JP
Japan
Prior art keywords
airing
liner cap
burning
multistage cylinder
burner
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
JP10811579A
Other languages
Japanese (ja)
Inventor
Yoshimitsu Minagawa
Yoji Ishibashi
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 JP10811579A priority Critical patent/JPS5634027A/en
Publication of JPS5634027A publication Critical patent/JPS5634027A/en
Pending legal-status Critical Current

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Landscapes

  • Spray-Type Burners (AREA)

Abstract

PURPOSE: To raise the stability of burning by a method wherein a cooling structure is introduced into the multistage cylinder of a liner cap, the air stream advancing straight in the axial direction is supplied among burning flames and thereby cooling and prevention of interference of burning flames with each other are performed in a multinozzle burner for a gas turbine.
CONSTITUTION: The liner cap 7 is formed by the multistage cylinder 10, while each of staged parts is provided with an airing orifice 11. The cooling air 104 from the airing orifice 11 flows along the outer-pheripheral wall of the multistage cylinder 10, thus holding down the rise of temperature of the liner cap 7 itself. Meanwhile, the air advancing straight in the axial direction flows in from airing orifices 13A and 13B provided in a ring 12 and a disc 14, and a part thereof mixes in the recirculation flow of the gas, thereby holding down the rise of temperature of the liner cap 7. The interference of burning flames with each other can be prevented by making the airing orifices 13A and 13B of large diameter.
COPYRIGHT: (C)1981,JPO&Japio
JP10811579A 1979-08-27 1979-08-27 Burner for gas turbine Pending JPS5634027A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
JP10811579A JPS5634027A (en) 1979-08-27 1979-08-27 Burner for gas turbine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
JP10811579A JPS5634027A (en) 1979-08-27 1979-08-27 Burner for gas turbine

Publications (1)

Publication Number Publication Date
JPS5634027A true JPS5634027A (en) 1981-04-06

Family

ID=14476280

Family Applications (1)

Application Number Title Priority Date Filing Date
JP10811579A Pending JPS5634027A (en) 1979-08-27 1979-08-27 Burner for gas turbine

Country Status (1)

Country Link
JP (1) JPS5634027A (en)

Cited By (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2006029773A (en) * 2004-06-30 2006-02-02 General Electric Co <Ge> Multi-venturi tube fuel injector for gas turbine combustor
CN103075746A (en) * 2011-10-26 2013-05-01 通用电气公司 System and method for reducing combustion dynamics and nox in a combustor

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
JP2006029773A (en) * 2004-06-30 2006-02-02 General Electric Co <Ge> Multi-venturi tube fuel injector for gas turbine combustor
CN103075746A (en) * 2011-10-26 2013-05-01 通用电气公司 System and method for reducing combustion dynamics and nox in a combustor
EP2587157A3 (en) * 2011-10-26 2015-11-04 General Electric Company System and method for reducing combustion dynamics and NOx in a combustor

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