Turbine gas circuit of gas turbine

Abstract

The invention relates to the technical field of a gas turbine, and discloses a turbine gas circuit of a gas turbine. The turbine gas circuit comprises a gas compressor, a combustion pressure cylinder, a rotor and a turbine disc, wherein a gas outlet of the gas compressor is communicated with the combustion pressure cylinder; a cavity is arranged in the combustion pressure cylinder, and gas can circulate in the cavity; the combustion pressure cylinder is arranged at the outer circumference of the rotor, and the combustion pressure cylinder is sealed with the rotor by an intermediate sealing piece; one end of the rotor is connected with a last stage wheel disc of the gas compressor, and the other end of the rotor is connected with the turbine disc; a radial through hole is formed in the side wall of the combustion pressure cylinder opposite to the rotor; the radial through hole is formed between the gas outlet of the gas compressor and the intermediate sealing piece. The turbine gas circuit is reasonable in structural design, and is capable of improving the structural temperature of the last stage wheel disc of the gas compressor and the intermediate sealing piece, reducing heat stress and increasing the efficiency of the gas compressor.

Description

technical field [0001] The invention relates to the technical field of gas turbines, in particular to a turbine gas path of a gas turbine. Background technique [0002] With the continuous innovation and development of modern gas turbine technology, in order to improve the overall thermal efficiency of the gas turbine, the temperature before the turbine continues to rise. As a high-speed rotating part, the turbine blades work in an extremely high temperature environment at the same time, and the increase in the use temperature of materials alone cannot meet the actual use requirements. The turbine blades 7 must be cooled in a certain form. The cooling air for the turbine blades 7 generally comes from the air extraction of the compressor 1. As the cooling requirements become higher and higher, the demand for air extraction is also increasing, which will lead to a decrease in the thermal efficiency of the gas turbine. Therefore, a more ideal method is to further reduce the te...

AI Technical Summary

Problems solved by technology

[0003] An unavoidable problem in the existing technical solution is that the reinjected cold air forms the cooling air passage 11, and a part of the air flow through the air induction pipe 5 flows backward to form the first air passage 11a to cool the turbine blades 7; the other part of the gas will pass through The intermediate seal 2 flows forward to form the second gas path 11b. Since the reinjected cooling gas has been cooled by the cooler 4, its temperature is relatively low. When this part of gas flows along the second gas path 11b, it will reduce the intermediate The temperature of the sealing member 2 and the last stage disc 10 of the compressor 1, and the temperature of the retaining ring 9 is higher during the working state at the same time, so the temperature of the final stage disc 10 will be lower than that of the retaining ring 9, resulting in dynamic The blade top clearance is larger than the normal temperature state

And then affect the compressor efficiency and unit efficiency

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