Title:
GAS TURBINE COMBUSTOR
Document Type and Number:
Japanese Patent JP2008082590
Kind Code:
A
Abstract:
To improve both of low NOx combustion and stability in combustion in a gas turbine combustor.
In this gas turbine combustor comprising a combustion chamber to which fuel is supplied from a plurality of fuel nozzles, and the air is supplied from a plurality of air holes, and constituted to supply the coaxial jet formed by surrounding the circumference of the fuel flow by the air flow, to the combustion chamber, swirl vanes are disposed at the downstream of the air holes. As a result, the strong swirl flow is formed at the downstream of a burner, and the stability of flame can be improved. Further as a mixing distance can be extended without weakening the swirl flow, both of the stability of flame and the low NOx combustion can be improved.
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Inventors:
MIURA KEISUKE
INOUE HIROSHI
KOYAMA KAZUHITO
SAITO TAKEO
INOUE HIROSHI
KOYAMA KAZUHITO
SAITO TAKEO
Application Number:
JP2006261652A
Publication Date:
April 10, 2008
Filing Date:
September 27, 2006
Export Citation:
Assignee:
HITACHI LTD
International Classes:
F23R3/14; F02C7/22; F23R3/28
Attorney, Agent or Firm:
Manabu Inoue