Turbocharger-based bleed-air driven fuel gas booster system and method
AssigneeGas Research Institute
InventorsHenry B. Faulkner, James B. Kesseli, Michael C. Swarden, Willem Jansen
Life of this patent
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Abstract
A method and system for increasing the pressure of gaseous fuel delivered to a fuel system of a gas turbine engine. A portion of pressurized gas or compressed air is discharged from a high-pressure section of the gas turbine engine and is communicated to a plurality of radial inflow turbines or axial flow turbines. Energy is transferred from each turbine to a plurality of compressors driven by the turbines. Gaseous fuel is supplied to an inlet of one of the compressors. The compressed gaseous fuel is then cooled downstream of the compressors. The aftercooled and compressed gaseous fuel is delivered to the fuel system of the gas turbine engine.
Claims19
A method for increasing fuel gas pressure to a fuel system of a gas turbine engine, the steps comprising:
- (a) discharging a portion of pressurized gas from a high-pressure section of a gas turbine engine to at least one of a plurality of turbines;
- (b) transferring energy from said turbines to a plurality of compressors where each of said turbines drives a corresponding compressor of said compressors;
- (c) supplying a gaseous fuel to an inlet of each of said compressors;
- (d) compressing said gaseous fuel through said compressors;
- (e) aftercooling the compressed gaseous fuel downstream, with respect to a direction of flow of said gaseous fuel, of said compressors;
- (f) delivering the aftercooled and compressed gaseous fuel to a fuel system of the gas turbine engine;
- and
- (g) controlling a delivery pressure of said gaseous fuel at a fuel inlet of the fuel system by varying a flowrate of said portion of pressurized gas introduced to at least one of said turbines as a function of a power demand of the gas turbine engine and by varying a pressure drop across at least one of said turbines.
A system for increasing fuel gas pressure to a fuel system of a gas turbine engine, the system comprising:
- a plurality of turbines, a plurality of compressors, each of said turbines driving one corresponding compressor of said compressors;
- discharge means for discharging a portion of pressurized gas from a high-pressure section of the gas turbine engine to at least one of said turbines;
- gas inlet means for supplying a gaseous fuel to a compressor inlet of at least one of said compressors;
- heat transfer means for aftercooling the compressed gaseous fuel downstream of said compressors;
- delivery means for delivering the aftercooled and compressed gaseous fuel to a fuel system of the gas turbine engine;
- and
- control means for controlling a delivery pressure of said gaseous fuel to the fuel system by varying a flowrate of said portion of pressurized gas introduced to at least one of said turbines as a function of a power demand of the gas turbine engine, said control means comprising a generally cylindrical sleeve slidably mounted along a longitudinal axis of said cylindrical sleeve between a turbine housing and a plurality of inlet vanes of a corresponding turbine of said turbines;
- said cylindrical sleeve having a sleeve opening, and a circumferential width of at least a portion of said sleeve opening gradually increasing along said longitudinal axis of said cylindrical sleeve.
A system for increasing fuel gas pressure to a fuel system of a gas turbine engine, the system comprising:
- a plurality of turbocharger units;
- discharge means for discharging a portion of pressurized gas from a high-pressure section of the gas turbine engine to said turbocharger units;
- gas inlet means for supplying a gaseous fuel to a compressor inlet of at least one of said turbocharger units;
- heat transfer means for aftercooling the compressed gaseous fuel downstream of said turbocharger units;
- delivery means for delivering the aftercooled and compressed gaseous fuel to a fuel system of the gas turbine engine;
- and
- control means for controlling a delivery pressure of said gaseous fuel to the fuel system by varying a flowrate of said portion of pressurized gas introduced to at least one of said turbochargers as a function of a power demand of the gas turbine engine, said control means comprising a generally cylindrical sleeve slidably mounted along a longitudinal axis of said cylindrical sleeve between a turbine housing and a plurality of inlet vanes of a corresponding turbine of said turbines;
- said cylindrical sleeve having a sleeve opening, and a circumferential width of at least a portion of said sleeve opening gradually increasing along said longitudinal axis of said cylindrical sleeve.
Dependencies are inferred from the claim text.