Compressor power unit fuel flow control
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United States of America Patent
Stats
-
Jul 28, 1987
Grant Date -
N/A
app pub date -
Oct 4, 1985
filing date -
Oct 4, 1985
priority date (Note) -
Expired
status (Latency Note)
Importance
Abstract
In a gas turbine engine compressor power unit fuel is supplied at an essentially constant pressure to a fuel nozzle for injection into the combustion liner of the power unit's combustor. Nozzle fuel flow is modulated solely by bleeding off combustor supply air to vary the internal liner pressure, thereby altering the fuel pressure drop across the nozzle.
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