Multiple staged compressor with last stage airfoil cooling
View Patent ↗An industrial gas turbine engine in which a compressor includes later stage airfoils that are cooled using a coolant from an external closed loop cooling circuit or from a heat recovery steam generator. Cooling air compressed by a compressor external to the IGT engine can be used for cooling of the main compressor airfoils with a heat exchanger to preheat a fuel used in the combustor. Or, water and steam from a heat recover steam generator can be used to cool the compressor airfoils in which steam can be bled off from the steam generator for cooling and then reintroduced into the HRSG at a downstream stage. Steam is used to cool the rotor blades while water is used to cool the stator vanes.
1. A gas turbine engine comprising:
a multiple stage compressor with stages of stator vanes and rotor blades;
a combustor;
a turbine;
a heat exchanger;
a compressor driven by a motor;
the compressor providing compressed air to the combustor that is burned with a fuel to produce a hot gas stream that is passed through the turbine; and,
a closed loop cooling circuit passing through the compressor and the heat exchanger and a row of stator vanes or rotor blades of the multiple stage compressor to provide cooling for the row of stator vanes or rotor blades.
2. The gas turbine engine of claim 1 , and further comprising:
the heat exchanger uses a fuel to cool the cooling air for the row of stator vanes or rotor blades while preheating the fuel prior to introduction into the combustor.
3. The gas turbine engine of claim 1 , and further comprising:
the row of stator vanes or rotor blades is a last row of the compressor.
4. A power plant comprising:
an industrial gas turbine engine with a compressor and a combustor and a turbine to drive a first electric generator to produce electrical energy;
a heat recovery steam generator to produce steam from a turbine exhaust and drive a steam turbine to drive a second electric generator and produce electrical energy;
the compressor of the industrial gas turbine engine having a row of stator vanes or rotor blades with cooling passages formed therein;
the heat recovery steam turbine having a closed loop fluid path for water and steam that is used to drive the steam turbine; and,
the cooling passages of the compressor connected to the heat recovery steam generator closed loop fluid path to provide cooling for the row of stator vanes or rotor blades of the compressor.
5. The power plant of claim 4 , and further comprising:
the rotor of stator vanes is cooled with water from the heat recovery steam generator; and,
the row of rotor blades is cooled with steam from the heat recovery steam generator.
6. The power plant of claim 4 , and further comprising:
the row of rotor blades is cooled with steam from the heat recovery steam generator that is bled off from the steam turbine at a lower pressure and then reintroduced into the steam turbine at a stage having a higher pressure.
7. The power plant of claim 4 , and further comprising:
the row of stator vanes is cooled with water from the heat recover steam generator; and,
the water is turned to steam and reintroduced into the heat recovery steam generator at a location between the steam turbine outlet and a condenser inlet.
8. The power plant of claim 4 , and further comprising:
the row of stator vanes is cooled with water from the heat recover steam generator closed loop fluid path; and,
the water is reintroduced into the heat recovery steam generator closed loop fluid path at a location upstream or downstream from a pump.