Premixed combustion burner for gas turbine

Power plants – Combustion products used as motive fluid – Combustion products generator

Reexamination Certificate

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Details

C060S748000

Reexamination Certificate

active

08065880

ABSTRACT:
A premixed combustion burner for a gas turbine can efficiently premix fuel and air to produce fuel gas having a uniform concentration, while reliably achieving prevention of flash back by making the flow rate of fuel gas substantially uniform. The premixed combustion burner for a gas turbine has a fuel nozzle, a burner cylinder arranged so as to surround the fuel nozzle and form an air passageway between itself and the fuel nozzle, and swirler vanes that are arranged along an axial direction of the fuel nozzle in a plurality of positions around the circumferential direction of an outer circumference surface of the fuel nozzle. The swirler vanes gradually curve from an upstream side to a downstream side to spin the air traveling within the air passageway from the upstream side to the downstream side. A cutaway section is provided in a rear edge section on an inner circumference side of the swirler vanes.

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German Office Action (with English translation) issued Jul. 21, 2009 in counterpart German Application No. 102007004394.7.
Japanese Office Action dated Aug. 27, 2010 in corresponding Japanese Patent Application No. 2006-112217 with English translation.
German Office Action issued Mar. 4, 2011 in corresponding German Patent Application No. 102007004394.7 w/English translation.

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