Small gas turbine having enhanced fuel economy
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United States of America Patent
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Oct 19, 1993
Grant Date -
N/A
app pub date -
Feb 28, 1990
filing date -
Feb 28, 1990
priority date (Note) -
Expired
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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).
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