Operating line control of a compression system with flow recirculation
AssigneeGeneral Electric Company
InventorBryce Alexander Roth
Life of this patent
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Abstract
A system for controlling the operating lines of a gas turbine engine comprising a compression system which compresses an incoming flow of a gas, a bleed system which extracts gas from a bleed location in the compression system prior to the gas entering a throttling orifice, a recirculation system which reintroduces at least a portion of the gas extracted by the bleed system into a feed location in the compression system or upstream from it, a control system which controls the recirculated gas such that the operating lines of the compression system are changed such that the stall margin of the compression system is increased.
Claims20
A system for controlling the operating lines of a compression system comprising:
- a compression system which compresses an incoming flow of a gas;
- a bleed system which extracts gas from a bleed location;
- a recirculation system which reintroduces at least a portion of the gas extracted by the bleed system at a feed location located upstream from the bleed location;
- a control system which controls the recirculated gas such that the operating line of the compression system is changed whereby the stall margin of the compression system is increased.
A compression system for compressing a gas comprising:
- an axial compressor having a plurality of compression stages;
- a bleed means for extracting gas from a bleed location;
- a recirculation means for reintroducing at least a portion of the gas extracted by the bleed means at a feed location located upstream from the bleed location;
- a control means for controlling the amount of gas recirculated such that the operating line of the compression system is changed whereby the stall margin of the compression system is increased.
A gas turbine engine comprising:
- a fan that pressurizes at least a portion of the incoming air and flows it into a bypass stream;
- a compressor that compresses at least a portion of the incoming air;
- a bleed means for extracting air from a bleed location;
- a recirculation means for reintroducing at least a portion of the air extracted by the bleed means at a feed location located upstream from the bleed location;
- a control means for controlling the amount of air recirculated by the recirculation means such that the operating line of the fan is changed whereby the stall margin of the fan is increased.
A gas turbine engine according to claim 111 wherein the recirculation means reintroduce at least a portion of the air extracted by the bleed means at a plurality of feed locations in a casing located upstream from the compressor.
A gas turbine engine comprising:
- a fan that pressurizes at least a portion of the incoming air and flows it into a bypass stream;
- a compressor that compresses at least a portion of the incoming air;
- a bleed means for extracting air from a bleed location;
- a recirculation means for reintroducing at least a portion of the air extracted by the bleed means at a feed location located upstream from the bleed location;
- a control means for controlling the amount of air recirculated by the recirculation means such that the operating line of the compressor is changed whereby the stall margin of the compressor is increased.
A method of controlling a gas turbine engine comprising the steps of:
- raising the pressure of a gas entering the engine using a compression system;
- extracting a portion of the gas from a bleed location in the engine;
- reintroducing at least a portion of the gas extracted from the bleed location at a feed location upstream from the bleed location;
- controlling the amount of the gas reintroduced such that the operating line of the compression system is changed whereby the stall margin of the compression system is increased.
Dependencies are inferred from the claim text.