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An aero-engine multi-stage low-pressure turbine rotor assembly measurement device and method

A low-pressure turbine and measurement method technology, applied in the direction of measuring devices, instruments, etc., can solve problems affecting positioning accuracy, etc., and achieve the effects of improving measurement accuracy, ensuring rotor coaxiality, and ensuring quality

Active Publication Date: 2021-05-25
AECC SHENYANG ENGINE RES INST
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  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

It is required that the parts have a large and high-precision contact surface as a positioning reference, but there is no verticality requirement between the front end face of the low-pressure turbine primary disc assembly and the primary disc center, which affects positioning accuracy

Method used

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  • An aero-engine multi-stage low-pressure turbine rotor assembly measurement device and method
  • An aero-engine multi-stage low-pressure turbine rotor assembly measurement device and method

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Embodiment Construction

[0022] In order to make the purpose, technical solution and advantages of the application more clear, the technical solution in the embodiment of the application will be described in more detail below in conjunction with the drawings in the embodiment of the application.

[0023] In order to solve the problems of low positioning accuracy, low rotation accuracy, large data acquisition error in the installation process of the rotor disc and the stator casing in the prior art, which cannot meet the measurement accuracy requirements, and the unreliable rotor fixing method.

[0024] The present application provides a multi-stage low-pressure turbine rotor assembly measurement device and method for an aero-engine to solve the above problems.

[0025] Such as figure 1 As shown, the main measuring mechanism 1, the rotor clamping mechanism 2, the stator supporting mechanism 3, the turntable bearing 4, the self-aligning and tilting platform 5, the synchronous lifting mechanism 6, the ba...

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Abstract

This application discloses an assembly and measurement device for multistage low-pressure turbine rotors of aero-engines. For the overall preliminary leveling of the device, the rotor clamping mechanism is fixed on the centering and tilting platform for clamping the rotor disk. The self-aligning and tilting platform is connected with the turntable bearing and fixed on the base bracket for adjusting the rotor disk. The coaxiality of the stator support mechanism is set on the base bracket to support the stator casing, the synchronous lifting mechanism is fixed on the stator support mechanism, and the measuring mechanism is set on one side to measure the runout of the end face of the rotor disk. Compared with the prior art, this application can improve the measurement accuracy, which is beneficial to ensure the coaxiality of the rotor, and can effectively avoid the deformation of the primary disk center due to the bending moment formed by the clamping force, ensuring that the primary disk quality.

Description

technical field [0001] The application belongs to the technical field of aero-engine assembly, and in particular relates to an assembly measurement device and method for multi-stage low-pressure turbine rotors of an aero-engine. Background technique [0002] Such as figure 1 As shown, for the rotor-stator coupling assembly (assembled step by step in the order of the first-stage rotor and the first-stage guider), the rotor assembly is carried out synchronously during the turbine stator assembly process. At present, in the assembly of aero-engines, high-precision pads are generally used to directly contact the front surface of the first-stage turbine disc assembly and the first-stage turbine disc center cylinder for positioning, and the sliding friction pair drives the dial gauge to rotate to measure the beating of the turbine disc center cylinder. Positioning is carried out through the pad assembly of the assembly platform, the pressure plate assembly realizes the fixation o...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): G01B21/00
CPCG01B21/00
Inventor 牛孝霞龙洋韩晓娇
Owner AECC SHENYANG ENGINE RES INST
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