Fuel control system for a gas turbine engine
AssigneeLucas Industries Limited
InventorsGeoffrey A. Lewis, Brian E. Sparks
Life of this patent
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Abstract
A gas turbine engine fuel control system has a metering device which is controlled by the delivery pressure of the engine compressor, and an arrangement for modifying flow through the metering device in accordance with the difference between a calculated value of the pressure rise across the compressor, and a measured value of this pressure rise. The calculated value is obtained from a compound cam which is positioned in accordance with desired engine thrust and with one of the compressor pressures and is profiled in accordance with desired values of the other pressure. Movement of a cam follower is compared with a sensed value of the other pressure and used to modify fuel flow.
Claims11
A system for controlling fuel flow to a gas turbine engine in accordance with a difference between an inlet pressure and a delivery pressure of the engine, comprising a metering device having a control element, means for positioning said control element in accordance with a sensed value of said delivery pressure, means for modifying fuel flow through said metering device, a three-dimensional cam movable in response to a desired engine thrust and in response to one of said pressures, said cam being profiled in accordance with calculated values of the other of said pressures, said calculated values corresponding to combinations of said desired thrust and said one pressure, a cam follower co-operating with said cam, and control means responsive to the position of said cam follower and to a sensed value of said other pressure for operating said fuel flow modifying means.
Dependencies are inferred from the claim text.