Title:
SINGLE STAGE PREMIXED CONSTANT FUEL/AIR RATIO COMBUSTOR SYSTEM
Document Type and Number:
Japanese Patent JP3527779
Kind Code:
B2
Abstract:
PURPOSE: To provide a combustion system being used for radial turbine type gas turbine module drastically reduced with NOx and CO level.
CONSTITUTION: An annular combustor system 10 has an annular housing 40 defining a single stage combustor, an external fuel/air premixer system 60 having a mixing chamber 52 and a compressed air valve 90 and a fuel valve 92 both under the control of a control means 94, and provides a preselected lean fuel/air ratio mixture for introduction to the combustion zone 54 of the annular housing. Compressed air conduits 80 are used to channel a portion of the total compressed air flow to the premixer and the remainder to the dilution zone 56 of the combustor. A fuel conduit 66 is used to deliver all of the fuel to the premixer. Convection cooling of the annular housing is accomplished using compressed air without diluting the fuel air ratio in the combustion zone. The axis of the venturi 68, of which inlet is sprayed with fuel by nozzles 64, is aligned substantially tangentially to the annular housing axis 42 to provide a swirling admission of the premixed fuel/air mixture to the combustion zone.
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Inventors:
Mowill, Jan R.
Application Number:
JP17342094A
Publication Date:
May 17, 2004
Filing Date:
June 30, 1994
Export Citation:
Assignee:
Mowill, Jan R.
International Classes:
F02C7/22; F02C7/232; F02C9/50; F23R3/12; F23R3/26; F23R3/28; F23R3/30; F23R3/42; F23R3/50; F02C7/18; F23R3/54; (IPC1-7): F23R3/50; F02C7/18; F02C7/22; F02C7/232; F23R3/12; F23R3/26; F23R3/28; F23R3/30
Attorney, Agent or Firm:
高石 橘馬
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