Gas turbine cooling gas path and gas turbine

Abstract

The invention provides a turbine cooling gas circuit of a gas turbine and a gas turbine, comprising a compressor, a fuel pressure cylinder, a compressor rotor, an intermediate disk, a turbine rotor and a rotor sealing ring, the fuel pressure cylinder is arranged on the outer circumference of the intermediate disk and the fuel pressure There is a rotor sealing ring between the cylinder and the intermediate disc. One end of the intermediate disc is connected to the compressor rotor, and the other end of the intermediate disc is connected to the turbine rotor. The space forms a static chamber; the rotor seal ring is provided with a cooling air channel; the turbine rotor is provided with a turbine cooling channel; the rotor seal ring separates the rotary chamber into a fuel pressure cylinder chamber and a turbine rotor forward static chamber. Chamber; the outlet of the compressor is connected with the chamber of the fuel pressure cylinder, the cooling air channel is connected with the chamber of the fuel pressure cylinder and the static chamber of the turbine rotor, and the static chamber of the turbine rotor is connected with the cooling passage of the turbine .

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to a turbine cooling gas path of a gas turbine and a gas turbine. Background technique [0002] At present, an effective method to improve the cycle efficiency of a gas turbine is to increase the gas inlet temperature of the turbine. Turbine blades work under extreme temperature conditions, which are much higher than the material can withstand, so some form of cooling is required for turbine stationary blades and turbine moving blades. The ideal method is to adopt advanced cooling technologies such as impingement cooling and film cooling on the turbine blades, and extract cooling air from different positions of the compressor according to the different temperature fields at the turbine end, so as to reduce the influence of air extraction on the efficiency of the compressor. . [0003] An unavoidable problem in the existing technical solution is that the temperature of the tur...

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Problems solved by technology

[0004] In view of the above-mentioned shortcomings of the prior art, the object of the present invention is to provide a gas turbine turbine cooling gas circuit and a gas turbine, which are used to solve the problem of a large number of cooling holes and disc cavities in the internal cooling channel of the prior art. Composed of a sudden expansion structure, the cooling air will lose about 70% of its kinetic energy when passing through the sudden expansion structure. This part of kinetic energy is converted into internal energy and cannot be used

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