Cooling system for gas turbine, gas turbine equipment provided with same, and parts cooling method for gas turbine

  • US 10,634,058 B2
  • Filed: 01/25/2016
  • Issued: 04/28/2020
  • Est. Priority Date: 01/30/2015
  • Status: Active Grant
First Claim
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1. A method for cooling parts of a gas turbine, the gas turbine including a compressor configured to compress air, a combustor configured to burn a fuel in the air compressed by the compressor and to generate a combustion gas, and a turbine driven using the combustion gas, the method comprising:

  • a high pressure bleeding step of bleeding air from a first bleed position of the compressor as first air and sending the first air via a high pressure bleed line to a first hot part of the gas turbine which is in contact with the combustion gas the high pressure bleed line having a first end and a second end, the first end of the high pressure bleed line configured to connect to, and bleed the first air from, the first bleed position of the compressor, the second end of the high pressure bleed line being configured to connect to the first hot part;

    a cooling step of cooling, using a cooler, the first air sent to the first hot part in the high pressure bleeding step;

    a low pressure bleeding step of bleeding second air at a pressure lower than that of the first air from a second bleed position of the compressor and sending the second air via a low pressure bleed line to a second hot part of the gas turbine without passing through a cooler, the second hot part in contact with the combustion gas and disposed under a lower pressure environment than the first hot part;

    a mixing step of mixing the first air cooled in the cooling step into the second air sent to the second hot part;

    a first control step of using a first control unit to control a degree of valve opening of a first valve to control a flow rate of the first air mixed into the second air, the first valve being provided on a connecting line, the connecting line configured to connect together (1) a first position in the high pressure bleed line between the second end of the high pressure bleed line and the cooler and (2) the low pressure bleed line; and

    a second control step of using a second control unit to control a degree of valve opening of a second valve to control a flow rate of parts inflow air, the parts inflow air being a mixture of the first air and the second air, the flow rate of the first air being controlled in the first control step, the second valve being provided at a second position in the high pressure bleed line between the first end of the high pressure bleed line and the cooler,wherein, in the first control step, the flow rate of the first air to be mixed into the second air is controlled by the first control unit based on at least one of (1) an intake temperature that is a temperature of air suctioned by the compressor or (2) an output correlation value that is either a gas turbine output or a value correlated with the gas turbine output, andin the second control step, the flow rate of the parts inflow air is controlled by the second control unit based on the at least one of the intake temperature or the output correlation value.

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