Gas turbine with cooling of the last turbine stage
View Patent ↗An exhaust-gas section for a gas turbine, having a surrounding shroud having a first opening, which is arranged in a region of the exhaust-gas section that has a pressure lower than the air pressure of the outer environment of the gas turbine in an operating state of the gas turbine and which forms the outlet of an air channel, the inlet of which is connected to the outer environment of the gas turbine. The air channel has a chamber at the outlet-side end of the air channel, which chamber has a second opening, through which a specified gas mass flow is admitted into the chamber.
1. A gas turbine comprising:
a stator which comprises an exhaust-gas section, an inner shroud of which is separated from platforms of rotor blades of a blade wheel of a last turbine stage on a hot-gas side of a rotor of the gas turbine by an axial gap, the axial gap connecting the exhaust-gas section to a wheel-side space of the blade wheel, said wheel-side space, in one operating state of the gas turbine, comprising a lower pressure than an air pressure of the outside environment of the gas turbine and said wheel-side space comprising an air inlet which is connected to the outside environment of the gas turbine via an air duct,
wherein the air inlet is connected to the air duct via a chamber, the chamber comprising a first opening to the air duct and a second opening through which the chamber is acted upon by a predetermined gas mass flow.
2. The gas turbine as claimed in claim 1 ,
wherein the chamber adjoins the wheel-side space.
3. The gas turbine as claimed in claim 1 ,
wherein the chamber is designed in such a manner that a pressure in the chamber is less than 30 mbar above the lower pressure in the wheel-side space.
4. The gas turbine as claimed in claim 3 ,
wherein the pressure in the chamber is less than 10 mbar above the lower pressure in the wheel-side space.
5. The gas turbine as claimed in claim 1 ,
wherein the wheel-side space has a further opening through which flushing air is supplied.
6. The gas turbine as claimed in claim 1 ,
wherein a source of the predetermined gas mass flow is designed for a mass flow that is substantially constant with varying pressure in the wheel-side space.
7. The gas turbine as claimed in claim 1 ,
wherein there is a blower connected upstream of the second opening of the chamber.
8. The gas turbine as claimed in claim 1 ,
wherein there is a compressor connected upstream of the second opening of the chamber.
9. The gas turbine as claimed in claim 1 ,
wherein a sealing-air seal of a shaft of the gas turbine is assigned to the second opening of the chamber.
10. The gas turbine as claimed in claim 1 ,
wherein the chamber is of encircling design around a longitudinal axis of the gas turbine.
11. A power plant comprising
a gas turbine as claimed in claim 1 .
12. A gas turbine, comprising:
a turbine comprising a last stage comprising a blade wheel comprising rotor blades;
an exhaust gas section comprising an inner shroud separated from platforms of the rotor blades by an axial gap that connects a hot gas path in the exhaust gas section with a wheel side space of the blade wheel; and
a chamber in fluid communication with the wheel side space via an air inlet opening, the chamber comprising a first opening to an air duct that provides direct fluid communication between the chamber and a source of gas at ambient atmospheric pressure, and a second opening to a second flow path that provides direct fluid communication between the chamber and a source of compressed gas.
13. The gas turbine of claim 12 , further comprising a combustor and a compressor configured to supply compressed air to the combustor, wherein the source of compressed gas comprises the compressor.