CPC F02C 7/18 (2013.01) [F02C 9/18 (2013.01); F01D 25/12 (2013.01); F05D 2220/32 (2013.01); F05D 2230/80 (2013.01); F05D 2260/20 (2013.01)] | 20 Claims |
1. A method of modulating a cooling supply in a gas turbine engine for cooling components within the engine, the method comprising:
providing the gas turbine engine comprising a compressor section and a turbine section and including a cooling flow circuit, the cooling flow circuit supplying a cooling air flow from a compressor cavity in the compressor section to a blade ring cavity in the turbine section, wherein the cooling flow circuit includes a cooling air supply main line with a full capacity valve;
measuring a first pressure in the blade ring cavity;
measuring a second pressure in a combustor shell source;
adjusting, by a control system in the gas turbine engine, the opening of the full capacity valve to control the cooling air flow through the cooling air supply main line in order to maintain a target pressure ratio, the pressure ratio defined as a ratio of the first pressure to the second pressure,
wherein the method is performed in an ambient temperature operating range of the gas turbine engine.
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