Gas Turbine Engine Inlet Anti-Ice System
AssigneeHoneywell International Inc.
InventorPaul W. Banta
Life of this patent
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AssigneeHoneywell International Inc.
InventorPaul W. Banta
Estimating the term…
A gas turbine engine inlet anti-ice system includes an air supply duct, a flow control valve, a pneumatic valve actuator, and a mechanical thermostat. The air supply duct has an inlet to receive pressurized air, and an outlet coupled to an anti-ice flow duct formed within an inlet portion of a gas turbine engine. The flow control valve is disposed within the air supply duct between the inlet and the outlet and is moveable to a valve position between a closed position and a plurality of open positions. The pneumatic valve actuator is responsive to a pneumatic control pressure to move the flow control valve between the closed position and the plurality of open positions. The mechanical thermostat is responsive to temperature within the anti-ice flow duct to control the pneumatic control pressure, to thereby control the temperature of the air in the anti-ice flow duct.
A gas turbine engine inlet anti-ice system, comprising:
A gas turbine engine system, comprising:
A gas turbine engine inlet anti-ice system, comprising:
Dependencies are inferred from the claim text.