Method and device for cooling a component of a turbine
A method for cooling a component of a turbine is provided, wherein a fluid with a pressure below 1 bar is guided away from the component. Moreover, a turbine is described comprising a component, a conduit which is connected to the component so that a fluid can be guided away from the component, and a fluid discharge which is connected to the conduit. The fluid discharge is constructed so that it removes a fluid with a pressure below 1 bar.
1. A method for cooling a turbine casing, comprising:
guiding cooling air from an inlet duct of a compressor to the turbine casing via a conduit connecting the compressor inlet duct and the turbine casing,
cooling the turbine casing with the cooling air,
guiding the cooling air with a pressure below 1 bar away from the turbine casing, after cooling the turbine casing, and
injecting the cooling air guided away from the turbine casing into the compressor in the area of a first stage of stator blades of the compressor and/or in the area of a first stage of rotor blades of the compressor.
2. The method as claimed in claim 1 , further comprising filtering the cooling air upstream of the compressor inlet duct.
3. The method as claimed in claim 1 , wherein the turbine casing is in contact with a turbine guide vane.
4. The method as claimed in claim 1 , wherein the air is ventilated.
5. The method as claimed in claim 1 , wherein the cooling air is injected into the compressor in the area of the first stage of stator blades of the compressor and/or in the area of the first stage of rotor blades of the compressor at a pressure within a range between 0.5 bar and 0.9 bar.
6. The method as claimed in claim 5 , wherein the pressure is in a range between 0.7 and 0.8 bar.
7. The method as claimed in claim 1 , wherein an ejector is used to pressure boost the cooling air before guiding the cooling air to the turbine casing.
8. The method as claimed in claim 1 , wherein the cooling air is guided through a sealed path in the component in order to cool the turbine casing.
9. A gas turbine engine, comprising:
a compressor having an inlet duct;
a turbine casing;
a first conduit connecting the inlet duct of the compressor to the turbine casing to guide a cooling air from the compressor inlet duct to the turbine casing;
a second conduit connected to the turbine casing so that the cooling air can be guided away from the turbine casing at a pressure below 1 bar after cooling the turbine casing and injected into the compressor in the area of a first stage of stator blades of the compressor and/or in the area of a first stage of rotor blades of the compressor;
a fluid discharge connected to the second conduit,
wherein the fluid discharge removes the cooling air with a pressure below 1 bar after cooling the turbine casing into the second conduit.
10. The turbine as claimed in claim 9 , further comprising an ejector which is located between the compressor and the turbine casing.