Material performance testing system under suspension type multi-field coupling action in supergravity environment

A material performance, testing system technology, applied in the direction of analyzing materials, measuring devices, strength characteristics, etc., can solve problems such as reducing the fatigue life of blades, and achieve the effect of short experimental preparation period and safe and reliable testing process.

CN110261216APending Publication Date: 2019-09-20ZHEJIANG UNIV
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Patent Information

Authority / Receiving Office
CN · China
Patent Type
Applications(China)
Current Assignee / Owner
Publication Date
2019-09-20

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Abstract

The invention discloses a material performance testing system under the suspension type multi-field coupling action in a supergravity environment. The material performance testing system comprises a hoisting sealed cabin, a bearing frame, a high-temperature furnace, a mechanical testing device and a buffer device; the bearing frame and the high-temperature furnace are fixedly installed inside the hoisting sealed cabin, the bearing frame covers the high-temperature furnace, the buffer device is installed at the bottom inside the high-temperature furnace, the upper end and the lower end of the mechanical testing device are connected to the top of the bearing frame and the bottom of the high-temperature furnace, and the sample is connected and installed at the tail end of the mechanical testing device. The material performance testing system solves the problem of material dynamic performance testing under the coupling action of volume force-surface force-temperature under the high-speed rotation state, and is simple in structure, convenient to operate, safe and reliable.
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Description

technical field

[0001] The invention relates to the technical field of material performance testing, in particular to a suspension type material performance testing system and method under the coupled action of body force-surface force-temperature in a supergravity environment. Background technique

[0002] As the thrust-to-weight ratio of modern aero-engines increases and the number of turbine stages decreases, the gas inlet temperature before the turbine has developed from 1400-1500K in the 1970s to 1600-1750K at the beginning of this century. Up to 2000-2200K, which puts forward higher performance requirements for the core hot end components of the engine. As one of the key components of the hot end components, the working blades of the high-pressure turbine work under coupled loading conditions such as high temperature, high pressure, high speed, and alternating load for a long time during service.

[0003] When in service, the working blades of the turbine rotate aroun...

Examples

Embodiment Construction

[0037] The present invention will be further described below in conjunction with drawings and embodiments.

[0038] Such as figure 1 As shown, the specific implementation system includes a hoisting airtight cabin 1, a load-bearing frame 2, a high-temperature furnace 3, a mechanical testing device 4, and a buffer device 5; The frame 2 is covered outside the high temperature furnace 3, the buffer device 5 is installed at the bottom of the high temperature furnace 3, the upper and lower ends of the mechanical testing device 4 are connected to the top of the bearing frame 2 and the bottom of the high temperature furnace 3, and the sample 6 is connected and installed in the mechanical testing Device 4 ends.

[0039] The specific implementation system is as follows:

[0040] Such as figure 2 As shown, the hoisting sealing cabin 1 includes an upper sealing dome 11 and a hoisting sealing cavity 12. The hoisting sealing cavity 12 is provided with a cavity inside, and the upper end...