Maneuver based aircraft gas turbine engine speed control
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United States of America Patent
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May 25, 2010
Grant Date -
Apr 16, 2009
app pub date -
Feb 15, 2007
filing date -
Feb 15, 2007
priority date (Note) -
Expired
status (Latency Note)
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Abstract
A system and method for controlling the rotational speed of a gas turbine engine in an aircraft includes appropriate devices and processes for determining a pressure of lubricant supplied to the turbine engine, and for determining a maneuver state of the aircraft. The rotational speed of the gas turbine engine is controlled based at least partially on the determined pressure and the determined maneuver state. Thus, if the aircraft is in a maneuver state that may cause a reduction or loss of lubricant to the gas turbine engine, the rotational speed of the gas turbine engine can be reduced to a magnitude sufficient to increase turbomachine tolerance to the reduced or no lubricant flow.
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