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Distributed multi-shaft gas turbine and hybrid power system

A gas turbine and hybrid power technology, which is applied in the direction of gas turbine devices, machines/engines, fuel cells, etc., can solve the problems of difficult design of single-shaft gas turbines, improve system efficiency and layout flexibility, improve design flexibility and efficiency, Easy to use effect

Pending Publication Date: 2021-01-15
SHANGHAI ADVANCED RES INST CHINESE ACADEMY OF SCI
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0004] In view of the shortcomings of the prior art described above, the purpose of the present invention is to provide a distributed multi-shaft gas turbine and a composite power system, which are used to solve the problem of difficult design of the existing single-shaft gas turbine

Method used

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  • Distributed multi-shaft gas turbine and hybrid power system
  • Distributed multi-shaft gas turbine and hybrid power system
  • Distributed multi-shaft gas turbine and hybrid power system

Examples

Experimental program
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Embodiment 1

[0065] Such as figure 1 As shown, this embodiment provides a distributed multi-shaft gas turbine. The distributed multi-shaft gas turbine 10 includes: a low-pressure shaft module 100, a first intercooler module 200, and a high-pressure shaft module 500 that are independent of each other and connected through pipelines. , regenerator module 600, combustor module 700 and power turbine drive module 800,

[0066] The low-pressure shaft module 100 includes: a low-pressure compressor 101 and a low-pressure turbine 102, the low-pressure compressor 101 and the low-pressure turbine 102 are coaxially connected through bearings;

[0067] The high-pressure shaft module 500 includes: a high-pressure compressor 501 and a high-pressure turbine 502, the high-pressure compressor 501 and the high-pressure turbine 502 are coaxially connected through bearings;

[0068] The power turbine drive module 800 includes: a power turbine 801 and a power output unit 802, the power turbine 801 and the powe...

Embodiment 2

[0078] Such as figure 2As shown, this embodiment provides a distributed multi-shaft gas turbine, which is different from Embodiment 1 in that the distributed multi-shaft gas turbine 10 in this example further includes: at least one middle final shaft module 300, and the middle final shaft module 300 It includes: an intermediate pressure compressor 301 and an intermediate pressure turbine 302, the intermediate pressure compressor 301 and the intermediate pressure turbine 302 are coaxially connected through bearings, at this time, the intermediate pressure compressor 301 is connected to the first room Between the air outlet of the cooler module 200 and the air inlet of the high-pressure compressor 501, the medium-pressure turbine 302 is connected between the air outlet of the high-pressure turbine 502 and the air inlet of the low-pressure turbine 102; When the distributed multi-shaft gas turbine 10 includes two or more intermediate pressure shaft modules 300, multiple intermedi...

Embodiment 3

[0086] Such as image 3 As shown, this embodiment provides a hybrid power system, and the hybrid power system 1 includes: the distributed multi-shaft gas turbine 10 and the high-temperature fuel cell 20 as described in Embodiment 1 or Embodiment 2, wherein the high-temperature The fuel cell 20 is connected between the air outlet of the regenerator module 600 and the air inlet of the combustor module 700; at this time, the distributed multi-shaft gas turbine 10 and the high-temperature fuel cell 20 are the direct top layer coupling, that is, the air that has been heat-exchanged by the regenerator module 600 directly enters the high-temperature fuel cell 20 and undergoes an electrochemical reaction with the fuel 2 therein, so as to heat the air that has not participated in the reaction, thereby further improving the air entering the high-temperature fuel cell 20. The temperature of the air in the combustor module 700 is improved to improve the combustion efficiency of the system...

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Abstract

The invention provides a distributed multi-shaft gas turbine and a hybrid power system. The distributed multi-shaft gas turbine comprises a low-pressure shaft module, a first intercooler module, a high-pressure shaft module, a heat regenerator module, a combustion chamber module and a power turbine driving module which are independent of one another and connected through pipelines, wherein the low-pressure shaft module comprises a low-pressure compressor and a low-pressure turbine, and the low-pressure compressor is coaxially connected with the low-pressure turbine through a bearing; the high-pressure shaft module comprises a high-pressure compressor and a high-pressure turbine, and the high-pressure compressor is coaxially connected with the high-pressure turbine through a bearing; and the power turbine driving module comprises a power turbine and a power output unit, and the power turbine is coaxially connected with the power output unit through a bearing. By means of the distributedmulti-shaft gas turbine, the problem that an existing single-shaft gas turbine is large in design difficulty is solved.

Description

technical field [0001] The invention relates to a gas turbine structure, in particular to a distributed multi-shaft gas turbine and a compound power system. Background technique [0002] The gas turbine continuously inhales air from the atmosphere through the compressor and compresses it. The compressed air enters the combustion chamber and is mixed with the injected fuel to burn into high-temperature gas, which then flows into the turbine and expands to do work to drive the turbine wheel. The impeller of the compressor rotates together; since the working capacity of the heated high-temperature gas is significantly improved, while the turbine drives the compressor, there is still surplus work as the output mechanical work of the gas turbine. [0003] The existing gas turbine dedicated to the ground is basically a single-shaft structure. In specific applications, a low-pressure shaft (low-pressure compressor + low-pressure turbine), a medium-pressure shaft (medium-pressure co...

Claims

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Application Information

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IPC IPC(8): F02C6/00F02C3/04F02C3/10F02C6/18F02C7/08H01M8/04014
CPCF02C6/00F02C3/04F02C3/10F02C3/103F02C6/18F02C7/08H01M8/04022Y02E60/50
Inventor 高闯黄伟光
Owner SHANGHAI ADVANCED RES INST CHINESE ACADEMY OF SCI
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