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Sub-scale simulated aero-engine rotation test device

A technology of aero-engine and rotation test, which is applied in the direction of engine test, measuring device, machine/structural component test, etc., and can solve the problems of high cost

Active Publication Date: 2017-02-22
NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

At present, foreign object swallowing and blade flying tests of real engines are mostly used in the world to verify the safety of the engine when it encounters the above-mentioned sudden loads, which is expensive

Method used

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  • Sub-scale simulated aero-engine rotation test device

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Embodiment Construction

[0014] Below in conjunction with accompanying drawing, further illustrate the present invention, it should be understood that these embodiments are only used to illustrate the present invention and are not intended to limit the scope of the controllable hail launching device for aero-engine environmental test of the present invention, after having read the present invention, those skilled in the art Modifications of various equivalent forms of the present invention by personnel fall within the scope defined by the appended claims of the present application.

[0015] see figure 1 As shown, the present invention discloses a sub-scale simulated aeroengine rotation test device, comprising a rotating shaft 9, a motor 13 for driving the rotating shaft 9 to rotate, a simulated blisk 21 located at the front end of the rotating shaft 9, a front fulcrum bearing 20 installed on the rotating shaft 9, The front simulation drum 19 installed on the front fulcrum bearing 20, the middle fulcru...

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Abstract

The invention discloses a sub-scale simulated aero-engine rotation test device which comprises simulated casings, a simulated support plate, a simulated rotor shaft, a simulated blade disc, a simulated drum, a front fulcrum bearing, a middle fulcrum bearing, a rear fulcrum bearing and simulated front and rear mounting sections. The sub-scale simulated aero-engine rotation test device is driven by a motor to rotate through a set of breaking shaft protection devices. The simulated casings are connected via mounting side bolts. The simulated support plate is in welded connection with the simulated casings. The simulated blade disc is connected with a mounting plate and a shaft via bolts. The simulated drum is connected with the simulated support plate via bolts. The simulated front mounting section is connected with a rigid mounting base via bolts and a suspend rod. The simulated rear mounting section is connected with the rigid mounting base via bolts and a hinge. The various components of the sub-scale simulated aero-engine rotation test device can be disassembled and assembled to meet the needs of different tests.

Description

technical field [0001] The invention relates to the technical field of aero-engine impact dynamics and airworthiness compliance verification. Background technique [0002] Aeroengines may encounter impacts from foreign objects such as flying birds and hailstones during operation, and may also encounter blade loss accidents due to failure of rotor blades. Due to the impact of foreign objects or the loss of blades, the stable working state of the aeroengine will be destroyed. When designing and using aero-engines, the impact of such sudden loads on the safe operation of the engine must be considered. At present, the foreign object swallowing and blade flying off tests of real engines are mostly used in the world to verify the safety of the engine when it encounters the above-mentioned sudden loads, which is expensive. In order to explore the structural safety analysis method of an aero-engine when it encounters a sudden load, it is necessary to use methods such as test, analy...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): G01M15/00G01M7/08
CPCG01M7/08G01M15/00
Inventor 刘璐璐赵振华陈伟张晟刘双丽
Owner NANJING UNIV OF AERONAUTICS & ASTRONAUTICS
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