|Table of Contents|

Vibration analysis and modification design of partial admission turbine disk for a liquid rocket engine(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2023年01期
Page:
80-83
Research Field:
目次
Publishing date:

Info

Title:
Vibration analysis and modification design of partial admission turbine disk for a liquid rocket engine
Author(s):
LI Kangdi1;  WANG Jun2;  XU Zili1;  YAN Song2;  WANG Zhen2
(1.State key Laboratory for Strength and Vibration of Mechanical Structures, School of Aerospace Engineering, Xian Jiaotong University, Xian 710049, China2.Science and Technology on Liquid Rocket Engine Laboratory, Xian Aerospace Propulsion Institute,
Keywords:
liquid rocket engine partial admission turbine disk Kick effect blade-disk coupling
PACS:
V434.221
DOI:
-
Abstract:
Aiming at the problem of fatigue cracks at the root and back areas of the free standing blade turbine disk of a liquid rocket engine after many test runs, the three-dimensional elastoplastic finite element method was used to calculate the static strength of turbine disk and obtain the static stress of blade, considering the Kick effect generated by partial admission.Considering the influence of prestress caused by multi-field environment, the modes of turbine disk were calculated, and the natural frequencies and main vibration mode of the turbine disk were obtained.The dynamic response and dynamic stress of turbine disk under partial admission were calculated by using the full-loop model.On the basis of analyzing the cause of crack, the turbine disk was modified by adding integral-shroud at the top of the blade, and the turbine disk with integral-shrouded blade was analyzed.The results show that the static stress of the blades decreases by 50 after the modification, and the dynamic bending stress of the blades under the action of airflow force decreases by 65.The coupling effect between blades and disk is obviously enhanced, and the natural vibration mode of turbine disk changes, which avoids the forced vibration of blades near the resonant frequencies.After the modification, the static stress and dynamic bending stress of turbine disk are significantly reduced, and the risk of crack generation is reduced.

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