AIRCRAFT POWER OUTTAKE MANAGEMENT
First Claim
1. A system for controlling a gas turbine engine supplying power to an aircraft, the system comprising:
- a receiving unit adapted to receive a measurement signal comprising a measurement of a portion of a supplied power currently consumed by at least one load coupled to the engine; and
a processing unit adapted to extract the measurement from the measurement signal, generate a control signal in response to the portion of the supplied power currently consumed by the at least one load, and send the control signal to the engine for controlling an operation of the engine.
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Accused Products
Abstract
A system and method for controlling the operation of a gas turbine engine supplying power to an aircraft. The engine is controlled according to a reading of an amount of power drawn from the supplied power. The reading is fed directly to a control system, which issues commands for controlling engine parameters comprising an acceleration reference signal, load shedding, variable geometry positioning, and fuel flow. The control system may further issue commands for controlling the amount of power drawn. The control system may further use the reading to monitor the engine'"'"'s condition.
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Citations
19 Claims
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1. A system for controlling a gas turbine engine supplying power to an aircraft, the system comprising:
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a receiving unit adapted to receive a measurement signal comprising a measurement of a portion of a supplied power currently consumed by at least one load coupled to the engine; and a processing unit adapted to extract the measurement from the measurement signal, generate a control signal in response to the portion of the supplied power currently consumed by the at least one load, and send the control signal to the engine for controlling an operation of the engine. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A method for controlling a gas turbine engine supplying power to an aircraft, the method comprising:
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receiving a measurement signal comprising a measurement of a portion of a supplied power currently consumed by at least one load coupled to the engine; extracting the measurement from the measurement signal; generating a control signal in response to the portion of the supplied power currently consumed by the at least one load; and sending the control signal to the engine for controlling an operation of the engine. - View Dependent Claims (11, 12, 13, 14, 15, 16, 17, 18)
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19. A system for controlling a gas turbine engine supplying power to an aircraft, the system comprising:
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means for receiving a measurement signal comprising a measurement of a portion of a supplied power currently consumed by at least one load coupled to the engine; means for extracting the measurement from the measurement signal; means for generating a control signal in response to the portion of the supplied power currently consumed by the at least one load; and means for sending the control signal to the engine for controlling an operation of the engine.
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Specification