Gas turbine cooling gas path and gas turbine

A gas turbine, cooling air technology, applied in the cooling of the engine, the cooling of the turbine/propulsion device, the machine/engine, etc., can solve the problems of loss of kinetic energy and inability to use it, so as to prevent gas intrusion, improve cooling effect, and dissipate small loss effect

Inactive Publication Date: 2016-10-12
SHANGHAI ELECTRIC GAS TURBINE CO LTD
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

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

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  • Gas turbine cooling gas path and gas turbine
  • Gas turbine cooling gas path and gas turbine
  • Gas turbine cooling gas path and gas turbine

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Embodiment Construction

[0038] Embodiments of the present invention are described below through specific examples, and those skilled in the art can easily understand other advantages and effects of the present invention from the content disclosed in this specification. The present invention can also be implemented or applied through other different specific implementation modes, and various modifications or changes can be made to the details in this specification based on different viewpoints and applications without departing from the spirit of the present invention. It should be noted that, in the case of no conflict, the following embodiments and features in the embodiments can be combined with each other.

[0039] It should be noted that the diagrams provided in the following embodiments are only schematically illustrating the basic ideas of the present invention, and only the components related to the present invention are shown in the diagrams rather than the number, shape and shape of the compo...

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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...

Claims

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Application Information

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IPC IPC(8): F01D5/08F01D5/18F01D11/00F01D25/12F02C7/18
CPCF01D5/08F01D5/18F01D11/00F01D11/003F01D25/12F02C7/18
Inventor 何院何磊计京津
Owner SHANGHAI ELECTRIC GAS TURBINE CO LTD
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