Variable vane scheduling based on flight conditions for inclement weather
First Claim
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1. A method of protecting a gas turbine engine, the method comprising the steps of:
- determining a flight condition of an aircraft;
comparing the flight condition to a programmed condition; and
moving a plurality of compressor vanes of a compressor between a first position and a second position for deflecting foreign objects if the step of comparing the flight condition to the programmed flight condition determines the programmed flight condition is met, wherein the compressor includes a plurality of rotors, and an outer flowpath is defined between an outer diameter of the plurality of rotors and an outer casing of a gas turbine engine, and the plurality of compressor vanes direct the foreign objects into the outer flowpath for extraction through a duct with a downstream bleed.
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Abstract
A method of protecting a gas turbine engine according an exemplary aspect of the present disclosure includes, among other things, the steps of determining at least one flight condition of an aircraft and comparing the at least one flight condition to a programmed condition. The method further includes the steps of moving a plurality of inlet vanes of a low pressure compressor from a first position to a second position if the step of comparing the at least one flight condition to the programmed flight condition determines the programmed flight condition are met and deflecting any foreign objects with the plurality of inlet vanes.
68 Citations
22 Claims
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1. A method of protecting a gas turbine engine, the method comprising the steps of:
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determining a flight condition of an aircraft; comparing the flight condition to a programmed condition; and moving a plurality of compressor vanes of a compressor between a first position and a second position for deflecting foreign objects if the step of comparing the flight condition to the programmed flight condition determines the programmed flight condition is met, wherein the compressor includes a plurality of rotors, and an outer flowpath is defined between an outer diameter of the plurality of rotors and an outer casing of a gas turbine engine, and the plurality of compressor vanes direct the foreign objects into the outer flowpath for extraction through a duct with a downstream bleed. - View Dependent Claims (2, 3, 4, 5, 6, 7, 8, 9)
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10. A method of protecting a gas turbine engine, the method comprising the steps of:
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selecting flight conditions of an aircraft including at least an altitude and a power setting; comparing the flight conditions to programmed flight conditions; generating a signal in response to the step of comparing the flight conditions to the programmed flight conditions if the programmed flight conditions are met; and moving a plurality of vanes of a compressor from a non-diversion position to a diversion position for deflecting any foreign objects in response to the signal, wherein, an outer diameter of a plurality of rotors of the compressor and an outer casing of a gas turbine engine define an outer flowpath and the diversion position of the plurality of compressor vanes deflects foreign objects into the outer flowpath for extraction through a duct with a downstream bleed. - View Dependent Claims (11, 12, 13)
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14. A gas turbine engine comprising:
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a controller that determines flight conditions of an aircraft, compares the flight condition to a programmed flight condition, determines if the programmed flight condition is met, and generates a signal if the programmed flight condition is met; and a compressor including a plurality of compressor vanes constructed and arranged to move between a first position and a second position in response to the signal from the controller to deflect any foreign objects, wherein the compressor includes a plurality of rotors, and an outer flowpath is defined between an outer diameter of the plurality of rotors and an outer casing of a gas turbine engine, and the plurality of compressor vanes when in the second position direct the foreign objects into the outer flowpath for extraction through a duct with a downstream bleed. - View Dependent Claims (15, 16, 17, 18, 19, 20, 21, 22)
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Specification