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Dynamics Optimal Design Method Based on Whirl Direction Reversal of Counter-rotating Dual Rotors

A technology of reverse rotation and optimized design, which is applied in the direction of mechanical equipment, engine components, machines/engines, etc., can solve the problem that there is no method for estimating the reversal point of the reverse rotation double rotor whirl direction, and there is no whirl direction reversal Phenomena research and other issues

Active Publication Date: 2021-08-10
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
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  • Application Information

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Problems solved by technology

However, there is no research on the reversal phenomenon of the whirl direction, and no method for estimating the reversal point of the whirl direction of the counter-rotating dual rotors is given.

Method used

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  • Dynamics Optimal Design Method Based on Whirl Direction Reversal of Counter-rotating Dual Rotors
  • Dynamics Optimal Design Method Based on Whirl Direction Reversal of Counter-rotating Dual Rotors
  • Dynamics Optimal Design Method Based on Whirl Direction Reversal of Counter-rotating Dual Rotors

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Experimental program
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Embodiment Construction

[0077] This embodiment proposes a method for estimating the reversing rotational speed of the counter-rotating dual rotors in the whirl direction for the dual rotor system to be optimized. The specific process is:

[0078] Step 1. Determine the parameters of the dual-rotor system to be optimized:

[0079] The parameters of the dual-rotor system to be optimized include structural parameters and other parameters.

[0080] Ⅰ Determine the structural parameters of the dual-rotor system to be optimized:

[0081] The structural parameters include the length, outer radius, inner radius, density, modulus of elasticity and Poisson's ratio of each shaft segment, the quality of each disc, the moment of inertia of the axis center and the moment of inertia of the diameter; the determination process is respectively:

[0082] The length, outer radius, and inner radius of each shaft section are determined by the engineering drawings of the dual-rotor system to be optimized, and the density,...

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Abstract

A dynamics optimization design method based on counter-rotating dual-rotor whirl direction commutation, the unbalance of the dual-rotor system is brought into the genetic algorithm, and the unstable operating speed margin stipulated in the aeroengine design criteria is used as the calculation target , calculated by the genetic algorithm. The threshold value of the unbalance amount of the dual-rotor system includes a threshold value of the unbalance amount of the high-pressure rotor and a threshold value of the unbalance amount of the low-pressure rotor. The invention makes up for the deficiencies of the existing aero-engine structural dynamics design criteria, improves the aero-engine structural dynamics design capability, and performs aero-engine structural dynamics design according to the unstable operating speed margin specified in the aero-engine design criteria, and can The working speed of the aero-engine avoids the reversing point in the whirl direction, thereby improving the service life and reliability of the aero-engine.

Description

technical field [0001] The invention relates to the field of aero-engine dynamics design, and relates to an optimal design method for aero-engine rotor structure dynamics. [0002] technical background [0003] At present, aero-engines mostly adopt dual-rotor structure design. For counter-rotating dual-rotor systems, due to the unbalance of high and low pressure rotors, the whirl of the rotor system is sometimes mainly caused by high-pressure unbalance, and sometimes mainly by low-pressure unbalance. Stirring, therefore, there is a phenomenon of whirl direction reversal during the operation of the engine. If the design is not proper, the engine works for a long time near the reversing point of the whirl direction, resulting in frequent changes in the whirl direction of the rotor, and the intermediate bearing will be in a bad working condition for a long time, which will cause reliability problems of the aero-engine. Even cause structural damage to components, resulting in fl...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F01D5/06F01D25/00F01D21/00
CPCF01D5/06F01D21/003F01D25/00
Inventor 王俨剀廖明夫程盼李波
Owner NORTHWESTERN POLYTECHNICAL UNIV