Birotor aero-engine intermediate bearing offset angle determination and control method

Abstract

The invention belongs to the technical field of birotor aero-engine intermediate bearing offset angle determination and control, and particularly relates to a birotor aero-engine intermediate bearing offset angle determination and control method. The method comprises the steps that the offset angle of a low-pressure rotor component is calculated, wherein t42 is the eccentricity of a four-fulcrum bearing relative to the fulcrum of a two-fulcrum bearing, t12 is the eccentricity of a one-fulcrum bearing relative to the fulcrum of the two-fulcrum bearing, e4 is the radial clearance of the four-fulcrum bearing, e1 is the radial clearance of the one-fulcrum bearing, and L14 is the axial distance between the one-fulcrum bearing and the fulcrum of the four-fulcrum bearing; the offset angle of a high-pressure rotor component is calculated, wherein t32 is the eccentricity of a three-fulcrum bearing relative to the fulcrum of the two-fulcrum bearing, e3 is the radial clearance of the three-fulcrum bearing, e2 is the radial clearance of the two-fulcrum bearing, and L23 is the axial distance between the two-fulcrum bearing and the fulcrum of the three-fulcrum bearing; and the offset angle theta of the three-fulcrum bearing is calculated according to the formula: theta = |theta low-theta high|.

Description

technical field [0001] The application belongs to the technical field of determining and controlling the deflection angle of an intermediary bearing of a dual-rotor aero-engine, and specifically relates to a method for determining and controlling the deflection angle of an intermediary bearing of a dual-rotor aero-engine. Background technique [0002] The dual-rotor aero-engine mainly includes a low-pressure rotor part 1, a high-pressure rotor part 2, and a stator part 3, such as figure 1 As shown, wherein, the low-pressure rotor part 1 is supported on the stator part 3 through a one-point bearing 4 and four-point bearing 5; the high-pressure rotor part 2 is supported on the stator part 3 through two fulcrum bearings 6, and is supported on the On low pressure rotor part 1. [0003] The one-point bearing 4 and the two-point bearing 6 in the dual-rotor aeroengine are ball bearings, which can bear radial load and axial load. The three-point bearing 7 and the four-point bearing...

AI Technical Summary

Problems solved by technology

[0006] The three-point bearing 7, as an intermediary bearing assembled between the low-pressure rotor part 1 and the high-pressure rotor part 2, bears relatively large complex loads, and when the deflection angle θ is large, it is prone to damage, resulting in catastrophic accidents

[0007] At present, the deflection angle θ of the three-point bearing 7 is mostly analyzed by experience, lacks specific quantification methods, and relies heavily on the experience of technicians, which is subject to greater subjective arbitrariness and uncontrollability, and cannot be clearly defined for three-point bearings. 7 The constraint relationship of the influence factors of the deflection angle θ cannot provide guidance for the control of the deflection angle θ of the three-point bearing

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