Disc-type rod fastening rotor structure for heavy-duty gas turbine

A tie-rod rotor and gas turbine technology, which is applied in the direction of gas turbine devices, mechanical equipment, jet propulsion devices, etc., can solve the problems of low assembly efficiency and affecting the dynamic balance of rotors, and achieve high assembly efficiency, high centering accuracy and repeatability, good effect on neutral

Inactive Publication Date: 2011-07-06
XI AN JIAOTONG UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Practice has found that this assembled rotor is not as easy to control the centering of each part as the common integral rotor, which directly affects the dynamic balance of the rotor, and at the same time, the assembly efficiency is low

Method used

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  • Disc-type rod fastening rotor structure for heavy-duty gas turbine
  • Disc-type rod fastening rotor structure for heavy-duty gas turbine
  • Disc-type rod fastening rotor structure for heavy-duty gas turbine

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Embodiment Construction

[0012] The structural principle and working principle of the present invention will be described in further detail below in conjunction with the accompanying drawings.

[0013] refer to figure 1 and figure 2 , a disc tie-rod rotor structure for heavy-duty gas turbines, including compressor discs 1 with 10 or more stages in the compressor section, the compressor discs 1 are connected by axial transmission and twist pins 2, and finally One end of the first-stage compressor disc 1 and the middle combustion chamber section 3 is connected by an axial twist pin 2, and the central tie rod 4 passes through the central holes of the compressor discs 1 and the middle combustion chamber section 3 of each stage, and passes through the pre- Tighten the central tie rod 4 and the central tie rod nut 8 to connect the compressor discs 1 of each stage of the compressor section and the intermediate combustion chamber section 3 into a whole, and the other end of the intermediate combustion chamb...

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Abstract

The invention discloses a disc-type rod fastening rotor structure for a heavy-duty gas turbine, which comprises multistage compressor wheel discs in a compressor section, wherein the compressor wheel discs are connected and the compressor wheel discs and a middle combustion chamber section are connected through axial twist transmission pins; all stages of compressor wheel discs and the middle combustion chamber section are connected into a whole through central draw rods; the middle combustion section is connected with multistage turbine wheel discs in a turbine section; all stages of turbine wheel discs and the middle combustion chamber section are connected into a whole through prestressed circumferential draw rods; all stages of turbine wheel discs are engaged and the turbine wheel discs and the middle combustion chamber section are engaged through face teeth; therefore, the coaxiality of all stages of compressor wheel discs and the middle combustion chamber section and the coaxiality of all stages of turbine wheel discs and the middle combustion chamber section are guaranteed so as to guarantee the integral centrality of a rotor. The structure has the advantages of high centrality and high assembling efficiency.

Description

technical field [0001] The invention relates to the technical field of rotors of heavy gas turbines, in particular to a disc tie-rod rotor structure for heavy gas turbines. Background technique [0002] The disc tie rod rotor is an extremely important rotor form, which has been widely used in large rotating machinery such as heavy gas turbines. The disc tie rod rotor can be roughly divided into three parts: the compressor section, the intermediate combustion chamber section and the turbine section. The machine section generally has more than ten stages of discs, and the turbine section generally has more than three stages of discs. These discs are assembled in various forms through pre-tensioned tie rods to form a disc tie rod rotor. Practice has found that this assembled rotor is not as easy to control the centering of each part as the common integral rotor, thus directly affecting the dynamic balance of the rotor, and at the same time, the assembly efficiency is low. Con...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/20
Inventor 耿海鹏卢明剑戚社苗徐国徽虞烈
Owner XI AN JIAOTONG UNIV
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