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Microminiature turbine jet rotor swirling control method

A turbojet and engine technology, which is applied in the direction of engine components, engine lubrication, turbine/propulsion device lubrication, etc., can solve the problem of payload reduction of engine performance indicators, etc., and achieve light weight, simple damping structure and wide application range Effect

Inactive Publication Date: 2010-06-09
BEIHANG UNIV
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  • Abstract
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

The traditional way to deal with vibration is to add a high damping structure to the bearing seat or install a squeeze oil film damper. For the rotor of a micro turbojet engine, these high damping devices increase the structural complexity of the engine, and the payload will be greatly reduced. Thereby affecting the performance index of the engine

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  • Microminiature turbine jet rotor swirling control method
  • Microminiature turbine jet rotor swirling control method
  • Microminiature turbine jet rotor swirling control method

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Embodiment 1

[0037] The micro turbojet engine rotor whirl control method of the present invention is illustrated below by a specific embodiment, and is carried out according to the following steps:

[0038] Step 1. Determine the number of flat gaskets by performing damping calculations.

[0039] Calculate the whirl energy W of the rotor system according to formula (1) W ,Calculated as follows:

[0040] W W = t 3 ×mR×R×(0.4×2πn / 60) 2 / 2+t 4 ×W Q (1)

[0041] Among them, n=1.2×10 5 rpm, m=1×10 -4 Kg, R=1×10 -3 m, W Q =3.5×10 -2 J,t 3 = 1, t 4 =1.

[0042] Measure the length of the corresponding two shoulders of the bearing seat sleeve 11 and the shaft 12, and calculate the initial gasket compression space in the axial direction of the rotor to be 5.34×10 -3 m, and then obtain the initial compression amount of the wave gasket according to the axial preload requirement x=1.3×10-3 m, the total thickness of the flat gasket is 9×10 -4 m, use the following formula to...

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Abstract

The invention discloses a whirling control method of the rotor of a mini-size turbojet engine, which is characterized in that in the scalar system, the axial pre-tightening force or the waveform gasket compression amount, the waveform gasket rigidity, the rotor speed, the rotor quality and the unbalance information are adopted to accurately compute the thickness, the quantity and mounting mode ofthe coulomb damp gasket for the attenuation whirling through the energy equivalent theory; the damping rubber is combined to adjust the damping of the rotor and mount structurally; thereby, the whirling of the engine rotor is controlled accurately and the stable operation requirement under the higher rotational speed is realized for the mini-size turbojet engine. The whirling control method of therotor of a mini-size turbojet engine has the advantages of accurate coulomb damping computation, accurate whirling attenuation control, simple damp structure, light weight and convenient adjustment,wide application range, being applicable to the different forms of whirling of the mini-size turbojet and the whirling under the different frequencies.

Description

technical field [0001] The invention belongs to the technical field of micro engines, and relates to a method for controlling whirl of a rotor, and more particularly relates to a method for controlling whirl of a rotor of a micro turbojet engine. Background technique [0002] During the working process of the engine, the vibration control of the rotor is an important guarantee for the stable operation of the entire engine. The impact of rotor whirl on the stable operation of the entire engine cannot be ignored, especially for micro-sized high-speed rotors with a maximum speed of 80,000-160,000rpm, the impact of whirl has far exceeded the impact of other factors on the stable operation of the engine, and it will cause If it is rubbed, it will cause the bearing to burn out or the shaft to fatigue and deform. There are many reasons for whirl, such as the centrifugal force and bending moment caused by the unbalanced mass of the rotor, the impeller top clearance force, the frict...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02C7/06
Inventor 韩树军丁水汀郑东亚杜发荣陶智徐国强
Owner BEIHANG UNIV
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