Aero-engine low-pressure turbine rotor and stator blade rub-impact test bench

Abstract

The invention belongs to the field of aero-engine tests, and particularly discloses an aero-engine low-pressure turbine rotor and stator blade rub-impact test bench. The bench comprises a sliding system, a driving system, a stator system and a rotor system, wherein a sliding platform of the sliding system is arranged above a guide rail and is fixed by a limiting cable; a motor and a detachable coupling of the driving system provide power for the rotor system and realize separation of the rotor system; the stator system comprises two stator blades which are symmetrically arranged; a rotating shaft in the rotor system is fixed to the sliding platform, one end of the rotating shaft is connected with a motor through a detachable coupler, and the other end of the rotating shaft is connected with rotor blades arranged in the middle of stator blades. The problem that an existing aero-engine related overrun test bench cannot carry out a low-pressure turbine rotor and stator blade rub-impact test is solved, the defect that the test bench is single in function can be avoided, and the test bench has the advantages of being simple in structure, convenient to install, use and maintain and low in cost.

Description

technical field [0001] The invention belongs to the field of aero-engine testing, and more particularly relates to a rubbing test bench of a low-pressure turbine rotor-stator blade of an aero-engine. Background technique [0002] The aeroengine rotor system generally consists of a high-pressure rotor part and a low-pressure rotor part. The high-pressure rotor part includes a high-pressure turbine and a high-pressure compressor. The high-pressure turbine drives the high-pressure compressor rotor to rotate at high speed through the high-pressure turbine shaft; Compressor and fan, the low-pressure turbine drives the low-pressure compressor rotor and fan to rotate at high speed through the low-pressure turbine shaft. Among them, the low-pressure turbine shaft is nested in the high-pressure turbine shaft, thus forming a typical double rotor structure. [0003] During the working process of the aero-engine, the probability of the high-pressure turbine shaft breaking is very small...

AI Technical Summary

Problems solved by technology

[0005] Aiming at the above defects or improvement needs of the prior art, the present invention provides an aero-engine low-pressure turbine rotor-stator vane rubbing test bench, in which the characteristics of the aero-engine low-pressure turbine itself and the process of shaft fracture are designed accordingly. Sliding system, driving system, stator system and rotor system, and the research and design of key components such as sliding platform, bearing structure and their specific setting methods can effectively solve the problem that the rubbing test of turbine rotor stator cannot be carried out. At the same time, it also has the advantages of low cost and simple test, so it is especially suitable for the application occasion of over-rotation test of aero-engine rotor system

Images