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Heavy combustion engine assembling method for assembling rotor and front and rear supports in combining manner

A technology of front support and rear support, which is applied to gas turbine devices, mechanical equipment, jet propulsion devices, etc., can solve the problem that the rotor cannot be installed horizontally with the stator components, and achieve the effect of shortening the assembly cycle and convenient assembly.

Active Publication Date: 2012-01-25
SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Since the stator assembly is not a complete horizontal split structure, the rotor cannot be installed horizontally on the stator assembly; therefore, it is necessary to determine an assembly method so that the rotor and the inner whole-ring stator assembly can be assembled horizontally

Method used

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  • Heavy combustion engine assembling method for assembling rotor and front and rear supports in combining manner
  • Heavy combustion engine assembling method for assembling rotor and front and rear supports in combining manner
  • Heavy combustion engine assembling method for assembling rotor and front and rear supports in combining manner

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Embodiment Construction

[0025] Such as Figure 1~5 As shown, a method for assembling a heavy-duty gas turbine in which the rotor and the front and rear supports are assembled, includes the following steps:

[0026] Step 1: Assemble the front bearing assembly 12 and the front support cylinder 13 vertically to form the front support 10 through bolts; Assemble the rear bearing assembly 7 and the rear support cylinder 8 to form the rear support 6 through bolts;

[0027] Step 2: Place the gas turbine rotor 11 horizontally on a support seat fixed to the ground. The V-shaped front and rear supports of the support seat are respectively between the first and second stages of the rotor compressor, and the third and fourth stages of the turbine. The drum surface between the stages is in contact with the rubber pad in the middle, and the pin on the support seat is inserted into the radial exhaust hole of the gas turbine rotor 11 to achieve axial positioning;

[0028] Step 3: Mount the front support 10 and the rear sup...

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Abstract

The invention discloses a heavy combustion engine assembling method for assembling a rotor and a front and a rear supports in a combining manner, belonging to the technical field of combustion gas turbines. The heavy combustion engine comprises the steps of: vertically assembling a front bearing assembly and a front support cylinder into a front support, vertically assembling a rear bearing assembly and a rear support cylinder into a rear support; horizontally placing the rotor on a support base, horizontally arranging the front and the rear supports on the rotor, horizontally inserting a hollow shaft of a front hanging tool into a front shaft neck inner hole of the rotor; inserting a hollow shaft of a rear hanging tool into an rear shaft neck inner hole of the rotor of a combustion engine, vertically assembling an external stator assembly of the combustion engine, turning the external stator assembly to be in a horizontal state and then fixedly connecting with a combustion engine base, dismantling the upper half part of the external stator assembly; hoisting the front and the back of the rotor, hoisting the rotor with the front and the rear supports into the lower half part of the external stator assembly; fixedly connecting the front and the rear supports with the lower half part of the external stator assembly; and removing the front and the rear hanging tool and a rotor horizontal hanger, installing the upper half part of the external stator part, and horizontally assembling the rotor and the stator of the combustion engine.

Description

Technical field [0001] The invention belongs to the technical field of gas turbines, and particularly relates to a method for assembling a heavy-duty gas turbine in which a rotor and a front and rear support are combined. Background technique [0002] According to the different structural characteristics of heavy-duty gas turbines, there are two assembly methods: vertical assembly and horizontal assembly. The stator assembly of a heavy-duty gas turbine is a complete ring or a mixed structure of a complete ring and two halves. The vertical assembly method should be adopted, that is, the rotor and the stator are assembled vertically on a mounting platform, and the cylinder assembly of the complete machine is turned over to a horizontal state after installation. Then install the external pipelines and accessories; the gas turbine stator assembly should be horizontally assembled with all horizontal split structures, that is, the gas turbine rotor should be installed horizontally on t...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02C7/20
Inventor 孙远伟杨凯王敏陈克杰李景波
Owner SHENYANG LIMING AERO-ENGINE GROUP CORPORATION
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