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US 9,194,301 B2Granted
Protecting the operating margin of a gas turbine engine having variable vanes from aerodynamic distortion
AssigneeUnited Technologies Corporation
InventorWayne P. Parente
Life of this patent
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Abstract
A method of protecting operating margin of the gas turbine engine includes calculating an aerodynamic distortion of air entering an inlet of a gas turbine engine that has a compressor section with variable vanes that are movable subject to a control parameter. The control parameter is selectively modified in response to the aerodynamic distortion.
Claims18
A method of protecting operating margin of a gas turbine engine, the method comprising:
- calculating an aerodynamic distortion of air entering an inlet of a gas turbine engine as a function of at least one of angle of attack and angle of side slip, the gas turbine engine having a compressor section with variable vanes, the variable vanes being moveable subject to a control parameter;
- and
- selectively modifying the control parameter in response to the aerodynamic distortion.
A gas turbine engine comprising:
- an engine inlet;
- a compressor section in communication with the engine inlet, the compressor section including variable vanes that are moveable subject to a control parameter;
- a combustor section in communication with the compressor section;
- a turbine section in communication with the combustor section;
- and
- a controller configured to calculate an aerodynamic distortion of air entering the engine inlet as a function of at least one of angle of attack and angle of side slip and selectively modify the control parameter in response to the aerodynamic distortion.
3 more elements
Dependencies are inferred from the claim text.