A high-speed dynamic balancing method that satisfies the assembly and use of rocket engine turbopumps

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 ...

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 shafting structure. -The impact of decomposition, the balance quality control is excellent, the level of balance effect of each turbo pump is close, and the dispersion is small, which solves the problem that other high-speed dynamic balancing methods and their accuracy cannot be applied to the assembly and use conditions of turbo pumps

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