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

A technology of aero-engine and high-pressure rotor, which is applied in the direction of jet engine testing, gas turbine engine testing, measuring devices, etc., to achieve the effect of ensuring accuracy

Pending Publication Date: 2021-11-16
BEIHANG UNIV
View PDF19 Cites 1 Cited by
  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

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

Method used

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
View more

Image

Smart Image Click on the blue labels to locate them in the text.
Viewing Examples
Smart Image
  • Aero-engine high-pressure rotor blade service environment simulation device
  • Aero-engine high-pressure rotor blade service environment simulation device
  • Aero-engine high-pressure rotor blade service environment simulation device

Examples

Experimental program
Comparison scheme
Effect test

Embodiment Construction

[0028] The following will clearly and completely describe the technical solutions in the embodiments of the present invention with reference to the accompanying drawings in the embodiments of the present invention. Obviously, the described embodiments are only some, not all, embodiments of the present invention. Based on the embodiments of the present invention, all other embodiments obtained by persons of ordinary skill in the art without making creative efforts belong to the protection scope of the present invention.

[0029] 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.

[0030] In order to make the above objects, features and advantages of th...

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

PUM

No PUM Login to view more

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. ...

Claims

the structure of the environmentally friendly knitted fabric provided by the present invention; figure 2 Flow chart of the yarn wrapping machine for environmentally friendly knitted fabrics and storage devices; image 3 Is the parameter map of the yarn covering machine
Login to view more

Application Information

Patent Timeline
no application Login to view more
Patent Type & Authority Applications(China)
IPC IPC(8): G01N17/00G01N3/60G01M15/14
CPCG01N17/006G01N3/60G01M15/14
Inventor 尚勇裴延玲张恒吴萌萌宫声凯
Owner BEIHANG UNIV
Who we serve
  • R&D Engineer
  • R&D Manager
  • IP Professional
Why Eureka
  • Industry Leading Data Capabilities
  • Powerful AI technology
  • Patent DNA Extraction
Social media
Try Eureka
PatSnap group products