Gas turbine engine with radial turbine having modulated fuel cooled cooling air
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United States of America Patent
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Apr 4, 2023
Grant Date -
N/A
app pub date -
Mar 7, 2022
filing date -
Mar 7, 2022
priority date (Note) -
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status (Latency Note)
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Abstract
A gas turbine engine includes a centrifugal compressor, a combustor, a radial turbine, and a cooling air metering system. The centrifugal compressor is configured to rotate about an axis to produce compressed air. The combustor is fluidly connected downstream of the centrifugal compressor to receive the compressed air from the centrifugal compressor. The radial turbine is fluidly connected with the combustor and is axially spaced apart from the centrifugal compressor. The cooling air metering system is configured to selectively block or allow a portion of the compressed air flowing radially between the centrifugal compressor and the radial turbine, bypassing the combustor, and through a heat exchanger for cooling the radial turbine and other components.
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