|Table of Contents|

Application of cold and hot state conversion of turbine blade profile in liquid rocket engine(PDF)

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

Issue:
2018年02期
Page:
33-38
Research Field:
研究与设计
Publishing date:

Info

Title:
Application of cold and hot state conversion of turbine blade profile in liquid rocket engine
Author(s):
REN Zhong; XU Kaifu; HAN Fei
Xi'an Aerospace Propulsion Institute,Xi'an 710100,China
Keywords:
liquid rocket engine;  turbine blade;  deformation influence analysis;  cold and hot state conversion
PACS:
V431-34
DOI:
-
Abstract:
As a key part of closed cycle liquid rocket engine,the turbine blade is inevitably deformed under the effect of flow field and thermal field,which leads to low efficiency and bad performance. In the traditional design of the turbine,the influent of blade deformation was not under consideration. A deformation compensation method(cold and hot state conversion)is proposed in this paper. The effect of turbine blade deformation on its aerodynamic performance was studied by means of fluid-themo-structure coupling method. It is found that the efficiency,mass flow and axial force of the deformed turbine blade have changed significantly. Therefore, an iterative method is used to conduct deformation compensation for the blade,that is,convert the cold blade profile from a hot blade profile in the aerodynamic design. The results reveal that the aerodynamic performance can be controled precisely by using this mechod which can be carried out for engineering application.

References:

[1] 张贵田. 高压补燃液氧煤油发动机[M]. 北京:国防工业出版社,2005.
[2] 李斌,王晓峰,陈本森,等. 大叶顶间隙高效率火箭发动机涡轮设计[J]. 宇航学报,2009,30(2):695-698;
[3] 庄毓南,张国舟,刘中祥,等. 液体火箭发动机高效率反力式涡轮的设计[J]. 北京航空航天大学学报,1999,25(6):696-699.
[4] 王鹏,廖平,岳莉莉,等. 透平叶片在气热固耦合场下的热变形分析[J]. 机械科学与技术,2015,34(3):348-351;
[5] 王延荣,黄钟山,付志忠,等. 基于热态叶型的小轮毂比弯掠叶片结构保形设计与优化[J]. 航空动力学报,2015,30(10):2305-2311;
[6] 王鹏. 多能场作用下透平叶片的服役变形机理与设计补偿[D]. 长沙:中南大学,2014.
[7] 廖建国,张弛. 一种BP神经网络算法的改进模型[J].火力与指挥控制,2009,34(11):57-60.
[8] 徐楠,安莎,白东安,等. 上面级发动机小功率冲击式涡轮性能试验研究[J].火箭推进,2016,42(6):43-47.
XU Nan,AN Sha,BAI Dongan,et al. Performance test for low-power impact turbo of upper stage liquid rocket engine [J]. Journal of rocket propulsion,2016,42(6): 43-47.
[9] 窦唯,叶志明,闫宇龙. 涡轮泵叶轮/转子配合间隙对稳定性的影响[J].火箭推进,2016,42(4):26-34.
DOU Wei,YE Zhiming,YAN Yulong. Effect of tolerance clearance between turbine rotor and impeller in liquid-propellant rocket engine on stability [J]. Journal of rocket propulsion,2016,42(4): 26-34.

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