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Assembly tool for low-pressure turbine of engine

A low-pressure turbine and assembly tooling technology, applied in the direction of assembly machines, manufacturing tools, metal processing equipment, etc., can solve the problem of loss of bearings, etc., and achieve the effects of improved positioning accuracy, simple structure, and convenient installation and disassembly

Active Publication Date: 2020-06-12
AECC AVIATION POWER CO LTD
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] Aiming at the problem that the bearings are easily damaged during the installation process of the low-pressure turbine and the core engine of the existing engine, the invention provides an assem

Method used

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  • Assembly tool for low-pressure turbine of engine
  • Assembly tool for low-pressure turbine of engine
  • Assembly tool for low-pressure turbine of engine

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Embodiment Construction

[0047] The present invention will be further described in detail below in conjunction with the accompanying drawings, which are explanations rather than limitations of the present invention.

[0048] refer to Figure 1-11 , an assembly tool for a low-pressure turbine of an engine, including a positioning guide tool 5, a traction tool 6 and a torque multiplier 9.

[0049] The positioning guide tool 5 is coaxially connected with the low-pressure turbine shaft of the low-pressure turbine 1, the traction tool 6 is installed on the fan rotor 4, and the positioning guide tool 5 passes through the core machine 3 and the axis of the fan rotor 4 and is connected to the torque multiplier 9.

[0050] The positioning guide tool 5 includes a positioning shaft 51 , a traction shaft 52 , an adjustment shaft 57 and an adjustment rod 58 .

[0051] The traction shaft 52 and the positioning shaft 51 are both hollow shafts, one end of the positioning shaft 51 is embedded in one end of the tracti...

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Abstract

The invention provides an assembly tool for a low-pressure turbine of an engine. The assembly tool comprises a positioning guide tool and a traction tool, and the positioning guide tool is coaxially connected with a low-pressure turbine shaft. According to the assembly tool, in the assembly process, the traction shaft sequentially penetrates through a core machine, a traction shaft sleeve and a connecting shaft sleeve and extends to the outside of a fan rotor; in the assembly process of the low-pressure turbine, the torsion is applied to the traction shaft from the outside, the traction shaftand the connecting shaft sleeve synchronously rotate, the fan rotor drives the traction shaft to axially move through threads in the rotating process, and then the low-pressure turbine shaft has dualacting force of rotation and axial movement, and a bearing cylindrical roller on the low-pressure turbine shaft is gradually assembled into a bearing outer ring in the rotating process, so that the problem that a cylindrical roller mechanically collides with a bearing outer ring in the existing assembly process is solved.

Description

technical field [0001] The invention relates to the technical field of engine assembly, in particular to an assembly tool for an engine low-pressure turbine. Background technique [0002] The low-pressure turbine unit of the engine is a unit structure. The bearing inner ring, cage and bearing cylindrical roller of the four-point bearing of the engine are assembled on the low-pressure turbine shaft, which is a part of the low-pressure turbine unit; the bearing outer ring is assembled on the high-pressure turbine rotor. On the rear journal of the engine, it is part of the core engine unit. During assembly, each unit body is assembled horizontally, the low-pressure turbine unit body is horizontally assembled to the core machine unit body, the bearing cylindrical roller enters the bearing outer ring horizontally, and the gap between the bearing cylindrical roller outer diameter and the bearing inner ring is only 0.07mm. The length of the low-pressure turbine unit body is 1700mm...

Claims

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Application Information

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IPC IPC(8): B23P21/00
CPCB23P21/002
Inventor 马涛黄健宋树林崔宝锋焦晓冉任远哲张栋胡伟
Owner AECC AVIATION POWER CO LTD
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