Gas turbine engine fuel injectors

Details Gas turbine engine fuel injectors Gas turbine engine fuel injectors

1980-07-16

1982-12-07

Garrett, Robert E.

Power plants

Combustion products used as motive fluid

Combustion products generator

60748, 60749, F23R 328, B05B 710

Patent

active

043620213

ABSTRACT:
A gaseous fuel injector for a gas turbine engine, designed to burn gaseous fuels having a wide range of calorific values, includes a fuel nozzle attached to the engine casing and downstream fuel and air inlet means separate from the nozzle, attached to the head of the flame tube. The fuel and air inlet means comprise an outer annular passage containing a row of swirl vanes, through which compressed air from the engine compressor is arranged to flow, and an inner annular passage through which gaseous fuel and compressed air are arranged to flow, the inner annular passage decreasing in cross-sectional area in the direction of flow to prevent the flow of combustion products back into the injector. The nozzle and fuel and air inlet means, which is relatively large, are separate from each other so that the fuel nozzle can be removed and replaced through a relatively small opening in the engine casing.

REFERENCES:
patent: 2920449 (1960-01-01), Johnson et al.
patent: 3690093 (1972-09-01), Carlisle
patent: 3905192 (1975-09-01), Pierce et al.
patent: 4198815 (1980-04-01), Bobo et al.

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