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Simulation load balancing method and device for aircraft engine crankcase strength tests

A technology for aircraft engine and strength test, applied in the field of aircraft engine, can solve the problems of small load range, difficult to meet high-strength test, etc., and achieve the effect of large load range

Active Publication Date: 2014-02-19
无锡市海航电液伺服系统股份有限公司
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  • Abstract
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  • Application Information

AI Technical Summary

Problems solved by technology

In the prior art, the strength test of the casing usually adopts the method of internal pressure loading, that is, the clamp seals the two ends of the cavity of the casing, and at the same time, a large-tonnage servo cylinder is used to inject hydraulic oil into the inner and outer cavity respectively to compress the casing. The strength of the casing is obtained by obtaining the pressure difference between the internal and external hydraulic oil. This method is undoubtedly relatively backward. It can only simply simulate the force of the casing. Cause damage, while the load range of simulated loading is small, it is difficult to meet the needs of high-strength tests

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  • Simulation load balancing method and device for aircraft engine crankcase strength tests
  • Simulation load balancing method and device for aircraft engine crankcase strength tests
  • Simulation load balancing method and device for aircraft engine crankcase strength tests

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Embodiment Construction

[0015] The present invention will be described in further detail below according to the drawings and embodiments.

[0016] Such as Figure 1 to Figure 3 As shown, the simulated load balance method of the aircraft engine casing strength test described in the embodiment of the present invention, the casing 10 has an inner cavity body 1 and an outer cavity body 2, and the outer cavity body 2 has an outer cavity upper flange 21, an outer cavity body 2, and an outer cavity body 2. The cavity lower flange 22 and the middle flange 23, the inner cavity body 1 has the inner cavity upper flange 11 protruding from the outer cavity body 2 and the inner cavity lower flange 12, and the middle flange 23 has a symmetrical first loading boss 231 And the second loading boss 232, take the central axis of the casing as the X axis, the connecting line direction of the first loading boss and the second loading boss as the Y axis, and take the horizontal vertical line on the same horizontal plane as...

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Abstract

The invention relates to a simulation load balancing method and device for aircraft engine crankcase strength tests. According to the method, X-axis force, symmetrical torque force, Y-axis lateral force and Z-axis lateral force are provided for different positions of a crankcase through a servo oil cylinder, and thus the stress conditions of the crankcase are synthesized. The method is reliably verified due to the fact that the device is provided with the servo oil cylinder, an annular outer pipe, an annular inner pipe, an annular piston, a pull rod, an inner pressing plate and an outer pressing plate. With the simulation load balancing method and device for aircraft engine crankcase strength tests, the stress conditions of the crankcase can be effectively simulated, the simulated loaded load range is wide, and thus the requirements of high-strength tests are met.

Description

technical field [0001] The invention relates to a simulated load balancing method and device for an aircraft engine casing strength test, belonging to the technical field of aircraft engines. Background technique [0002] With the continuous development of my country's aviation technology, my country's aviation industry has made great progress. However, when it comes to engine technology, it has always been a weakness and has been blocked by foreign technologies. The engine casing is one of the important basic parts of the aircraft engine, and its performance has a fatal impact on the running quality of the engine. Therefore, the performance test of the aircraft engine casing is particularly important. [0003] Since the casing of an aircraft engine is usually a thin-walled ring, and the cavities are distributed on different levels, it is required to test under different pressures. It is extremely difficult to ensure the smooth progress of the strength test. In the prior ar...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M13/00
Inventor 朱晓兵支晓阳
Owner 无锡市海航电液伺服系统股份有限公司
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