Combustor for gas turbines with diverging pilot nozzle cone

Details Combustor for gas turbines with diverging pilot nozzle cone Combustor for gas turbines with diverging pilot nozzle cone

1993-10-18

1995-05-02

Bertsch, Richard A.

Power plants

Combustion products used as motive fluid

Combustion products generator

60749, F02C 100

Patent

active

054108845

ABSTRACT:
A gas turbine combustor suppresses the generation of NOx by mixing a fuel and air homogeneously. A pilot nozzle is provided at the center of the gas turbine combustor. A plurality of main nozzles surround the pilot nozzle. A diverging cone projects from the vicinity of the injection port of the pilot nozzle such that the flame from the main nozzles is sustained by the pilot nozzle and NOx is suppressed. The main nozzles can be provided upstream of the injection port of the pilot nozzle in which case an annular premixing nozzle having a throttled exit end is disposed downstream of the main nozzles. The main nozzle may also be in the form of a fuel nozzle having a plurality of tubes, a gaseous fuel being injected through one of the tubes, and liquid fuel being injected into the annular premixing nozzle through the other of the tubes so that the liquid fuel is atomized to mix the fuel and air homogeneously.

REFERENCES:
patent: 2385833 (1945-10-01), Nahigyan
patent: 3349826 (1967-10-01), Poole et al.
patent: 4982570 (1991-01-01), Waslo et al.

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