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Aero-engine rotor simplified equivalent test device for high-speed dynamic balance

A high-speed dynamic balance and test device technology, which is applied in the static/dynamic balance test, engine test, measuring device, etc., can solve problems that cannot be calculated theoretically and have complex structures, so as to promote research and development, simplify end-tooth connections, and reduce Calculate the effect of difficulty

Active Publication Date: 2021-09-24
NORTHEASTERN UNIV +2
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

This requires designers to carry out effective theoretical analysis and test simulation of the rotor system in the early stage of design. However, due to the complexity of the structure of aero-engine rotor parts, direct theoretical calculations cannot be performed.

Method used

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  • Aero-engine rotor simplified equivalent test device for high-speed dynamic balance
  • Aero-engine rotor simplified equivalent test device for high-speed dynamic balance
  • Aero-engine rotor simplified equivalent test device for high-speed dynamic balance

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Embodiment Construction

[0052] In order to better explain the present invention and facilitate understanding, the present invention will be described in detail below through specific embodiments in conjunction with the accompanying drawings.

[0053] Such as figure 1 and Figure 8 As shown: This embodiment provides a simplified equivalent test device for high-speed dynamic balancing of aviation rotors, including: T-slot platform 1, high-speed motor 2, spline drive shaft 3, slender shaft 4, short Shaft 9, moving turbine disk and supporting device; the high-speed motor 2, spline drive shaft 3, elongated shaft 4, short shaft 9 and moving turbine disk are arranged on the T-slot platform 1 by means of the supporting device ;

[0054]The high-speed motor 2 is connected to one end of the elongated shaft 4 by means of the spline transmission shaft 3; the other end of the elongated shaft 4 is connected to the short shaft 9 with an interference fit c; The turbine disk is installed on the short shaft 9; the ...

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Abstract

The invention relates to an aero-engine rotor simplified equivalent test device for high-speed dynamic balance. The aero-engine rotor simplified equivalent test device comprises a T-shaped groove platform, a high-speed motor, a spline transmission shaft, a slender shaft, a short shaft, a movable turbine disc and a supporting device. The high-speed motor, the spline transmission shaft, the slender shaft, the short shaft and the movable turbine disc are arranged on the T-shaped groove platform through the supporting device. The high-speed motor is in transmission connection with one end of the slender shaft through the spline transmission shaft; the other end of the slender shaft is in interference fit connection with the short shaft; the movable turbine disc is arranged on the short shaft; and the high-speed motor can drive the movable turbine disc to rotate by means of the slender shaft so as to simulate the dynamic evolution of an aero-engine rotor during operation. According to the simplified test device provided by the invention, complex parts are equivalent to simple disc and shaft parts through a certain simplification mode, so that the calculation difficulty can be greatly reduced, and meanwhile, the simplified test device also has great advantages in the aspect of processing and manufacturing of test pieces.

Description

technical field [0001] The invention belongs to the technical field of aeroengine rotor dynamics, in particular to a simplified equivalent test device for aeroengine rotors used for high-speed dynamic balancing. Background technique [0002] At present, with the improvement of the power performance requirements of the fifth-generation aircraft for aero-engines, the power-to-weight ratio of small and medium-sized turboshaft engines is also increasing day by day. The main reason for the improvement of the power performance of the aero-engine is the increase of the engine speed. Therefore, in the process of engine development and development, the importance of the dynamics research of the high-speed rotor of the aero-engine is greatly increased, especially the rotor dynamics of the aero-engine is particularly important. This requires designers to carry out effective theoretical analysis and experimental simulation of the rotor system in the early stage of design. However, due ...

Claims

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Application Information

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IPC IPC(8): G01M1/02G01M15/02
CPCG01M1/02G01M15/02
Inventor 韩朔夏华腾黄晓鸣陈凯卢崇劭韩清凯
Owner NORTHEASTERN UNIV
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