|Table of Contents|

Dynamic response calculation and method of rocket engine turbine blades(PDF)

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

Issue:
2020年06期
Page:
45-51
Research Field:
研究与设计
Publishing date:

Info

Title:
Dynamic response calculation and method of rocket engine turbine blades
Author(s):
REN Zhong; XU Kaifu; ZHU Donghua
(Xi'an Aerospace Propulsion Institute, Xi'an 710100, China)
Keywords:
reusable rocket engine;  impact turbine;  dynamic response;  theoretical model;  fluid-solid coupling simulation;  high cycle fatigue
PACS:
V434.21
DOI:
-
Abstract:
With the development of reusable rocket engines, the high cycle fatigue of turbine blades must be studied in depth. A theoretical model to calculate the dynamic response of partial admission turbine blades under the excitation force was proposed in this paper, and the vibration equation and solution method were established. Both theoretical method and fluid-solid coupling three-dimension simulation method were applied to an engine turbine blade. Compared to three-dimension simulation method, the average dynamic stress at blade root calculated by theoretical method is 3.39% lower, the response frequency is 1.62% higher and the maximum response amplitude is 11.4% lower. Thus, the accuracy of theoretical method is verified, and this method can be applied to the high cycle fatigue design of rocket turbine blades.

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