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Title:
GAS TURBINE COMBUSTOR
Document Type and Number:
Japanese Patent JP2001254946
Kind Code:
A
Abstract:

To provide a gas turbine combustor which has a good combustion stability and can conduct combustion even with a thin fuel concentration.

In order to have a pilot flame smoothly contacted with a premixed gas, the rear end edge of a pilot cone (17) is extended until it becomes substantially parallel with an axis. Accordingly, the premixed gas discharged from a swirl channel (15) flows along the outer surface of the pilot cone as shown by an arrow (201) while the pilot flame flows along the inner surface of the pilot cone as shown by an arrow (202). Both of them are mixed while being substantially parallel with each other, hardly generating disorder, and thus the flames are stabilized. As the stability of the flames is improved, combustion can be conducted with a thinner fuel concentration, thereby reducing NOx. Also, with the stabilization of combustion, generation rate of heat is prevented from drastically rising, which also contributes to the decreasing of NOx.


Inventors:
Bandai, Shigemi
Itsura, Tetsuo
Tanaka, Katsunori
Nishida, Koichi
Application Number:
JP2000000070893
Publication Date:
September 21, 2001
Filing Date:
March 14, 2000
Export Citation:
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Assignee:
MITSUBISHI HEAVY IND LTD
International Classes:
F23R3/20; F23D17/00; F23D23/00; F23R3/14; F23R3/28; F23R3/32; F23R3/34; (IPC1-7): F23R3/20; F23R3/14; F23R3/32; F23R3/34
Attorney, Agent or Firm:
石田 敬 (外4名)