Small gas turbine engine having enhanced fuel economy

Details Small gas turbine engine having enhanced fuel economy Small gas turbine engine having enhanced fuel economy

1993-08-02

1995-10-03

Casaregola, Louis J.

Power plants

Combustion products used as motive fluid

Combustion products generator

415115, 417406, F02C 712

Patent

active

054542227

ABSTRACT:
A gas turbine engine ducted to have the air pass sequentially through a single stage axial-flow compressor, a single-stage hybrid axial-radial centrifugal compressor, a burner, an inward flow radial turbine, an axial-flow, high-pressure turbine, and then exit nozzles. The axial compressor and axial turbine are on a common core shaft. The centrifugal compressor and the radial turbine are on a common porous hub and form an integral, modular unit in which forces on the radial turbine blades drive the centrifugal compressor. The porous common hub permits air to transpire from the compressor to the turbine, serving to cool the turbine. Fuel is burned in annular, "folded-comma" shaped burners with multiple fuel-injection and ignition zones (two-stage combustion).

REFERENCES:
patent: 2514874 (1950-07-01), Kollsman
patent: 2709893 (1955-06-01), Birmann
patent: 3927952 (1975-12-01), Kirby
patent: 5253472 (1993-10-01), Dev

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