Aero-engine high-pressure rotor blade service environment simulation device

Abstract

The invention discloses an aero-engine high-pressure rotor blade service environment simulation device, and relates to the technical field of aero-engine blade service environment simulation equipment. The aero-engine high-pressure rotor blade service environment simulation device comprises a sample rotating table and a heating system; a blade sample is fixed to the sample rotating table; and the heating system comprises a main spray gun which is used for heating the blade sample and spraying a corrosion medium to the surface of the blade sample, and a plurality of auxiliary spray guns for heating the rotating area of the blade sample. According to the device of the invention, thermal shock of the corrosion medium on the blade sample is realized, a severe service environment of the high-pressure rotor blade is truly simulated, and a failure mechanism of a thermal barrier coating on the surface of the blade sample is researched more accurately; and the plurality of auxiliary spray guns are further arranged to heat the rotating area of the blade sample, so that it can be guaranteed that the rotating area of the blade sample is kept at a high temperature, the accuracy of service environment simulation is guaranteed, and the influence of repeated changes of the surface temperature of the blade sample on the failure process of the thermal barrier coating is avoided.

Description

technical field [0001] The invention relates to the technical field of aero-engine blade service environment simulation equipment, in particular to an aero-engine high-pressure rotor blade service environment simulation device. Background technique [0002] Aeroengines are known as "the jewel in the crown of industry" and are an important symbol to measure a country's industrial level. With the continuous improvement of the thrust-to-weight ratio of aero-engines, the temperature at the front-end inlet of the turbine also continues to increase. The temperature at the front-end inlet of the F119 turbine of the aero-engine F22 of the fifth-generation aircraft in the United States has reached 1900K. Ni-based single crystal superalloy and Ni 3 Al-based single crystal alloys currently have a temperature bearing capacity between 1400K and 1500K, and the remaining temperature gap of 400K to 500K is filled by gas film hole cooling technology and thermal barrier coating technology. ...

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide an aero-engine high-pressure rotor blade service environment simulation device to solve the problems existing in the prior art, to truly simulate the harsh service environment of the high-pressure rotor blade, and to update the failure mechanism of the thermal barrier coating on the surface of the blade sample. accurate research

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