Testing device for simulation and real-time detection of erosion of thermal barrier coatings of turbine blades

Abstract

The invention discloses a testing device for simulation and real-time detection of erosion of thermal barrier coatings of turbine blades, belonging to the field of simulation devices in a special service environment. The testing device comprises an erosion particle feeding system, a test testing platform (1), a temperature test system, an acoustic emission nondestructive testing system, a control platform and the like. An erect fixed shaft (101) is arranged on the test testing platform (1) and is connected with a horizontal supporting shaft. The testing device can be used for simulating the erosion service environment in which hard particles in a high-performance aero-engine repeatedly impact thermal barrier coatings of turbine blades due to the driving of airflow. By controlling the parameters such as erosion speed, angle, size and the like of erosion particles, the process that the coatings are eroded by different hard particles in the service process is realized and the real-time test and analysis of data, such as the temperature, the surface topography evolution, the interfacial oxidation of a sample and the like can be synchronously realized. The device can provide an important test platform for effectively assessing the erosion failure process and the failure mechanism of coatings of turbine blades in the special service environment.

Description

technical field [0001] The invention relates to a test device for simulating and real-time testing of erosion of high-temperature components, in particular to a service environment for simulating the high-temperature and erosion of turbine blades of thermal barrier coatings of aeroengines, and realizing real-time testing of multiple erosion failure parameters The test device belongs to the field of simulation devices for special service environments. Background technique [0002] In recent years, with the development of aeroengines, the thrust-to-weight ratio of the key parameters of the engine has been continuously improved, and the operating temperature of the high-temperature components of the engine has become higher and higher. By the time of the fourth-generation fighter jets, the inlet temperature of the gas turbine had reached 1700 °C. This puts forward higher requirements for the superalloy materials of the hot end parts of the engine. At present, the service limit...

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Problems solved by technology

In foreign countries, only NASA's high-speed gas simulation device and a certain combustion device at Cranfield University in the UK are similar to erosion devices, but there is no domestic test device that involves simulating and testing the erosion performance of turbine blades in aero-engines. The simulation of the high temperature erosion environment of the thermal barrier coating turbine blade has not been realized

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