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Aircraft engine shaft component supporting stiffness simulator

An aero-engine, stiffness simulation technology, applied in instruments, special data processing applications, electrical digital data processing, etc., can solve the problem of not having a rotor fulcrum, achieve good promotion significance, reduce radial stiffness, and eliminate test errors.

Inactive Publication Date: 2018-06-08
CHINA AIRPLANT STRENGTH RES INST
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0006] The purpose of the present invention is to provide a birdcage stiffness simulator capable of simulating the support stiffness of shaft parts in view of the current disadvantage that there cannot be a rotor fulcrum on the test shaft in the test of the shaft parts of the aero-engine

Method used

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  • Aircraft engine shaft component supporting stiffness simulator
  • Aircraft engine shaft component supporting stiffness simulator
  • Aircraft engine shaft component supporting stiffness simulator

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Embodiment Construction

[0021] The specific embodiments of the present invention will be further described below in conjunction with the accompanying drawings.

[0022] Taking the fan shaft of a turbofan engine with a large bypass ratio as an example, figure 1 It is a schematic diagram of fan shaft, bearing and related accessories, including inner steel sleeve 1, roller bearing 2, cup washer 3, nut 4, sealing grate A 5, sealing grate B 6, deep groove ball bearing 7 , Spring collar 8, stop piece 9, nut 10, bushing 11, adjusting pad 12. The "birdcage" stiffness simulator supports the test piece during the test and mainly bears the bending moment and axial load. The axial load is borne by the upper stiffness simulator through the deep groove ball bearing; the test piece undergoes swing deformation under the action of bending moment, and the upper and lower stiffness simulators are subjected to forces in opposite directions to form a force couple to balance the load borne by the test piece.

[0023] Ro...

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Abstract

The invention belongs to the field of aircraft engine shaft component structural strength testing, and particularly relates to an aircraft engine shaft component supporting stiffness simulator. By adopting the hollow cylindrical birdcage-shaped structure, the stiffness simulator is of a vertical stacked structure and is composed of an upper bearing pedestal, a lower bearing pedestal and a connecting bolt; the internal structure shape and size of the stiffness simulator are determined by the real structure of an aircraft engine shaft component, the real structures of bearings of an aircraft engine shafts and accessories, and the machining and assembling technologies are reserved; the external hollow structural shape and size of the stiffness stimulator are optimized and designed by a largefinite element software optimization design module according to the required geometric characteristic parameters. It is ensured that the enough axial stiffness is achieved while the radial stiffness of the simulator is lowered, and testing errors are eliminated.

Description

technical field [0001] The invention belongs to the field of structural strength tests of aero-engine shaft parts, and relates to a support stiffness simulator for aero-engine shaft parts. Background technique [0002] As a key technology in the model development, the research on the strength, life, stiffness and damage tolerance of the rotating parts of the engine is in urgent need of relevant test verification. The structure, strength, stiffness, and life tests of shaft components of high bypass ratio turbofan engines are one of the items that must be carried out in the process of airworthiness certification of commercial engines. A complete research system must be established to reduce the cost and risk of obtaining evidence and ensure the model development cycle. [0003] Usually the maximum working load of aero-engine shaft parts is much larger than that of the bench test run, and the complete engine test run on the test bench cannot effectively test and verify the fat...

Claims

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Application Information

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IPC IPC(8): G06F17/50
CPCG06F30/15G06F30/17G06F30/23
Inventor 孙万超李扬眉高翔燕群黄文超
Owner CHINA AIRPLANT STRENGTH RES INST
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