Gas turbine combustor with a plurality of circumferentially spac

Details Gas turbine combustor with a plurality of circumferentially spac Gas turbine combustor with a plurality of circumferentially spac

1994-09-14

1997-01-28

Thorpe, Timothy S.

Power plants

Combustion products used as motive fluid

Combustion products generator

60746, F02C 708

Patent

active

055968732

ABSTRACT:
An annular combustor with an air fuel mixer is disclosed including a plurality of mixing tubes having a forward end and an exit end, wherein a longitudinal axis through the exit end for each mixing tube is at both an axial angle and a radial angle to the centerline axis of the mixer. A fuel injector for providing fuel to the forward end of each mixing tube, a fuel manifold in flow communication with each of the fuel injectors, and a fuel supply and control means are provided. High pressure air from a compressor is injected into the mixing tubes and fuel is injected into the mixing tubes from the fuel injectors, wherein the high pressure air and the fuel is uniformly mixed therein so as to produce minimal formation of pollutants when the fuel/air mixture is exhausted out the downstream end of the mixing tubes into the combustor and combusted. The mixing tubes preferably impart a swirl to the fuel/air mixture as it exits into the combustor.

REFERENCES:
patent: 3452933 (1969-07-01), Hakluytt
patent: 4215535 (1980-08-01), Lewis
patent: 4222232 (1980-09-01), Robinson
patent: 4827724 (1989-05-01), Maghon et al.
patent: 5070700 (1991-12-01), Mowill
patent: 5156002 (1992-10-01), Mowill
patent: 5165241 (1992-11-01), Joshi et al.
patent: 5218824 (1993-06-01), Cederwall et al.
patent: 5251447 (1993-10-01), Joshi et al.

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