Systems and methods for surge margin testing of gas turbine engine using an undersized load component
AssigneeDoosan Enerbility Co., Ltd.
InventorAlexander Bograd
Life of this patent
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Abstract
The present disclosure relates to off-grid testing of a gas turbine engine using an undersized load compressor as part of the testing apparatus. By lowering the pressure experienced by the gas turbine engine at its intake and/or exhaust, validation testing can be performed at the gas turbine's maximum combustion temperature and/or maximum cycle pressure ratio without exceeding the power output that the load compressor is able to absorb. Subsequently introducing compressed air from the load compressor into the combustor of the gas turbine engine allows for surge margin testing to be performed.
Claims20
A system for off-grid testing of a gas turbine engine with an undersized load compressor, the system comprising:
- the gas turbine engine comprising an intake, a compressor, a combustor, a turbine, and a rotary shaft;
- a load compressor mechanically coupled to the rotary shaft of the gas turbine engine, the load compressor having an exhaust port;
- a first conduit fluidly connecting the exhaust port of the load compressor with the combustor of the gas turbine engine;
- an exhaust hood fluidly connected to the gas turbine engine downstream of the turbine such that the exhaust emitted from the turbine is discharged into the exhaust hood;
- and
- a second conduit fluidly connecting the exhaust port of the load compressor with the exhaust hood.
A method of off-grid testing a gas turbine engine with an undersized load compressor, the method comprising:
- mechanically coupling a rotary shaft of the gas turbine engine with a rotary shaft of the undersized load compressor, wherein the gas turbine engine has a full-speed full-load (“FSFL”) design power output and the undersized load compressor has a maximum load smaller than the FSFL design power output of the gas turbine engine;
- simulating an operating condition for the gas turbine engine using a first portion of a total flow of high-pressure air generated by the undersized load compressor;
- inducing the gas turbine engine to operate beyond a design operating state and approach a compressor surge operating state;
- and
- generating test data based on the gas turbine engine operating beyond the design operating state.
A system for off-grid testing of a gas turbine engine having a full-speed full-load (“FSFL”) design power output, the gas turbine engine comprising a compressor having an air intake, a combustor, a turbine, and a rotary shaft coupling the turbine to the compressor, the system comprising:
- a load compressor having a maximum load smaller than the FSFL design power output of the gas turbine engine, the load compressor configured to be mechanically coupled to the rotary shaft of the gas turbine engine, the load compressor having an exhaust port;
- an intake throttle fluidly connected to the air intake of the gas turbine engine, the intake throttle configured to reduce the pressure of air entering the air intake;
- an exhaust hood configured to couple with the gas turbine engine downstream of the turbine such that exhaust gas is communicated from the turbine into the exhaust hood;
- an injection nozzle in fluid communication with the exhaust hood;
- a first conduit fluidly connecting the exhaust port of the load compressor with the combustor of the gas turbine engine;
- and
- a second conduit fluidly connecting the exhaust port of the load compressor with the injection nozzle for communicating high-pressure fluid to the exhaust hood.
Dependencies are inferred from the claim text.