Transient turbine overtemperature control
AssigneeGeneral Electric Company
InventorsFerderick J. Pineo, Thomas A. Baxter
Life of this patent
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Abstract
A gas turbine engine includes a compressor joined to a turbine by a core rotor, with a combustor disposed therebetween for receiving compressed air from the compressor and fuel through a valve for producing combustion gas discharged to the turbine. A speed sensor measures speed of the core rotor, and a pressure sensor measures pressure at an inlet to the compressor. A controller is operatively joined to the sensors and the fuel valve and is configured for limiting fuel flow to the combustor in response to core acceleration rate and compressor inlet pressure to limit transient temperature of the combustor discharge combustion gas.
Claims12
A method of limiting transient turbine overtemperature in a gas turbine engine having a compressor joined to a turbine by a core rotor, with a combustor disposed therebetween for receiving compressed air from said compressor and fuel through a valve for producing combustion gas discharged to said turbine, comprising limiting fuel flow to said combustor in response to a ratio of core acceleration of said core rotor and inlet pressure of inlet air entering said compressor to limit transient temperature of said combustion gas discharged from said combustor into said turbine.
A gas turbine engine comprising:
- a compressor joined to a turbine by a core rotor;
- a combustor disposed between said compressor and turbine for receiving compressed air from said compressor and fuel through a valve for producing combustion gas discharged to said turbine;
- means for limiting fuel flow to said combustor in response to a ratio of acceleration of said core rotor and inlet pressure of inlet air entering said compressor to limit transient temperature of said combustion gas discharged from said combustor into said turbine.
Dependencies are inferred from the claim text.