Structural dynamic design method for high-pressure rotor of aircraft engine

A technology for aero-engines and high-pressure rotors, which is applied in the direction of engine components, machines/engines, mechanical equipment, etc., and can solve problems such as limited application range and difficulty in applying aero-engines

Active Publication Date: 2014-05-28
NORTHWESTERN POLYTECHNICAL UNIV +1
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Problems solved by technology

This paper provides an effective method to avoid rotor instability due to internal friction, but the application of this method

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  • Structural dynamic design method for high-pressure rotor of aircraft engine
  • Structural dynamic design method for high-pressure rotor of aircraft engine
  • Structural dynamic design method for high-pressure rotor of aircraft engine

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Embodiment Construction

[0074] This embodiment is a high-pressure rotor dynamics design method for a dual-rotor experimental device.

[0075] Step 1, establishing a high-pressure rotor dynamics model and dynamic equations.

[0076] High pressure rotor model such as figure 2 shown. In this model, the high-pressure shaft and disc are supported between two elastic supports, and a damper is installed at the front fulcrum. In this model, the mass of the rotor is M; the pole moment of inertia is I p The distance between the center of gravity and the front fulcrum is a; the distance between the center of gravity and the rear fulcrum is b; the moment of inertia of the rotor around the center of gravity is I; the damping coefficient is d; two elastic supports, the stiffness of the front fulcrum support is S b1 , the support stiffness of the rear fulcrum is S b2 ; The distance between the two fulcrums is L; the position of the centroid is x c .

[0077] Firstly, the free vibration differential equation ...

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Abstract

Disclosed is a structural dynamic design method for a high-pressure rotor of an aircraft engine. The relationship between high-pressure rotor model design parameters and rotor vibration characteristics is determined, so that the design method and criterions are provided for dynamic design of the high-pressure rotor, and the method is of great guiding significance to the design of the high-pressure rotor of the aircraft engine. The method includes: establishing a dynamic model and a dynamic equation of the high-pressure rotor to obtain a nondimensionalization characteristic equation; introducing an equivalent critical speed, and determining a two-order critical speed range of a high-pressure rotor system according to the equivalent critical speed; changing a conventional equilibrium amount configuration method by configuring residual disequilibrium amount phases; configuring a ratio of rotor pole rotation inertia to mass center rotation inertia in design according to a specific design objective; establishing configuration criterions for a rotor bearing stiffness ratio. A conventional design process is changed, structural dynamic active design of the high-pressure rotor is realized, the design process is optimized beneficially, design cycle is shortened, and the method has important construction value.

Description

technical field [0001] The invention relates to the field of aero-engine dynamics design, and relates to a design method for the structural dynamics of a high-pressure rotor of an aero-engine. Background technique [0002] The high-pressure rotor of an aero-engine consists of a high-pressure compressor, a high-pressure turbine and a support system. In general, the rotor is designed as a rigid rotor, while the support is elastic, and the elastic support and squeeze film damper are arranged at the front fulcrum, such as GE90 and GEnx engines, which adopt this design scheme. [0003] For the design of high-pressure rotors, the current research focuses on the configuration of the critical speed of the rotor and the analysis and verification of vibration characteristics. That is to say, the first-order critical speed (translation mode) is required to be below the engine idle speed, while the second-order critical speed (pitch mode) is within the working speed range. Every time ...

Claims

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Application Information

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IPC IPC(8): F01D5/10
Inventor 廖明夫谭大力耿建明王四季王俨剀杨伸记刘展翅
Owner NORTHWESTERN POLYTECHNICAL UNIV
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