High-speed dynamic balancing method satisfying assembly and usage of rocket engine turbopump

A high-speed dynamic balancing and rocket engine technology, applied in the field of high-speed dynamic balancing, can solve the problems of small dispersion of the balance effect of the turbo pump, and the accuracy of the high-speed dynamic balancing method cannot be applied to the assembly and use conditions of the turbo pump, and achieves good balance quality consistency. , Conducive to balancing quality assurance and balancing the effect of high quality

Active Publication Date: 2018-02-16
BEIJING AEROSPACE PROPULSION INST
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  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

[0003] The technical problem solved by the present invention is to overcome the deficiencies of the prior art and propose a high-speed dynamic balancing method that satisfies the assembly and use of rocket engine turbopumps. The balance quality is high, the balance effect is consistent, and it is not subject to repeated assembly of the

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  • High-speed dynamic balancing method satisfying assembly and usage of rocket engine turbopump

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Embodiment 1

[0080] At present, among the turbine pump rotors using this invention for high-speed dynamic balancing, one of the turbine pump rotors is a two-stage centrifugal pump structure driven by the turbine. It is a flexible rotor working between the second-order critical speed and the third-order critical speed. High-speed dynamic balance , there are 4 concentrated mass disks on the shaft system: the first-stage centrifugal wheel, the second-stage centrifugal wheel, the turbine disc, and the shaft connection flange. The steps of applying the present invention for high-speed dynamic balancing of this type of turbo pump rotor are as follows:

[0081] Step 1: Preparation before balance. This step carries out theoretical calculation and balance preparation before high-speed dynamic balance. According to the structure and characteristics of the rotor, the high-speed dynamic balance parameters and indicators of the flexible rotor of the turbo pump are determined by using the combination o...

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Abstract

A high-speed dynamic balancing method satisfying the assembly and usage of a rocket engine turbopump comprises the following steps of 1 utilizing a finite element method to calculate the dynamic characteristics of a turbopump flexible rotor, and combining a high-speed dynamic balancing quality consistency control method to determine the high speed dynamic balancing parameters and indexes of the turbopump flexible rotor; 2 assembling the turbopump flexible rotor, installing the turbopump flexible rotor on a high speed dynamic balancing machine, and installing and debugging a displacement sensor; 3 carrying out the repeated assembly and disassembly consistency tests of the de-weight balancing and high speed dynamic balancing effects on the turbopump flexible rotor; 4 according to the test results in the steps 1 to 3, assembling the turbopump. The high-speed dynamic balancing method of the present invention solves the problem that other high-speed dynamic balancing methods and precisionsare not suitable for the turbopump assembly and usage conditions.

Description

technical field [0001] The invention relates to a high-speed dynamic balancing method, in particular to a high-speed dynamic balancing method that satisfies the assembly and use of rocket engine turbo pumps. Background technique [0002] The turbopump is a key component of the liquid engine to deliver propellant, and its operating status directly affects the reliability and safety of the engine. In particular, the turbopump of the hydrogen-oxygen engine has a high working speed, and a flexible rotor that works between the first and second order or even the second and third order critical speed is often used. The high speed brings challenges to the smooth operation of the turbopump rotor. It must be balanced by high-speed dynamic balancing process so that the rotor can run smoothly in the full speed range and the rotor amplitude is within the allowable range of the design. For the turbo pump rotor with high working speed (>40000r / min), the over-critical vibration problem ...

Claims

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Application Information

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IPC IPC(8): G01M1/04G01M1/22
CPCG01M1/04G01M1/22
Inventor 窦唯刘洋姜绪强闫宇龙刘洪杰吴霖李铭张召磊叶小明夏德新
Owner BEIJING AEROSPACE PROPULSION INST
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