Inlet fluid flow and impingement angle control
OwnerSteven William TILLERYinventor
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Abstract
A compressor of a gas turbine system comprises a fluid flow control device and an impingement angle control device downstream of the fluid flow control device. The fluid flow control device controls a fluid flow rate of fluid entering an inlet of the compressor, and the impingement angle control device controls an impingement angle of the fluid flowing to rotor blades in the compressor. The fluid flow control device and the impingement angle control device are independently operable.
Claims19
A compressor of a gas turbine system arranged to compress fluid for combustion in a combustor with fuel, the compressor comprising:
- a fluid flow control device arranged to control a fluid flow rate of fluid entering an inlet of the compressor;
- and
- an impingement angle control device downstream of the fluid flow control device and arranged to control an impingement angle of the fluid flowing to rotor blades in the compressor,
- wherein the fluid flow control device and the impingement angle control device are arranged to be independently operable.
A gas turbine system, comprising:
- a compressor arranged to compress fluid;
- a fuel delivery unit arranged to deliver fuel;
- a combustor arranged to mix the compressed fluid discharged from the compressor with the fuel from the fuel delivery unit and combust the fuel and fluid mixture;
- a turbine arranged convert heat energy released from the combustion of the fuel and fluid mixture to mechanical energy for driving a load (160);
- and
- a system controller arranged to control an overall operation of the gas turbine system,
- wherein the compressor comprises
- a fluid flow control device arranged to control a fluid flow rate of fluid entering an inlet of the compressor based on a fluid flow rate control signal from the system controller;
- and
- an impingement angle control device downstream of the fluid flow control device and arranged to control an impingement angle of the fluid flowing to rotor blades in the compressor based on an impingement angle control signal from the system controller, and
- wherein the fluid flow control device and the impingement angle control device are arranged to be independently operable.
A method performed at or on behalf of a system controller of a gas turbine system to control a fluid flow rate of fluid entering an inlet of a compressor of the gas turbine system and/or to control an impingement angle of the fluid flowing to rotor blades in the compressor, the method comprising:
- receiving one or more sensor signals from one or more of the compressor, a fuel delivery unit, a combustor and a turbine of the gas turbine system or receiving one or more externally provided operation input signals or receiving both;
- setting a desired fluid flow rate or setting a desired impingement angle or setting both based on the sensor and/or operation input signals;
- and
- transmitting a fluid flow rate control signal in accordance with the desired fluid flow rate to a fluid flow control device or transmitting (360) an impingement angle control signal in accordance with the desired impingement angle to an impingement angle control device or transmitting both.
Dependencies are inferred from the claim text.