航天推进技术研究院主办
[1]任 众,许开富,韩 飞.涡轮叶型冷热态转换在液体火箭发动机中的应用[J].火箭推进,2018,44(02):33-38.
REN Zhong,XU Kaifu,HAN Fei.Application of cold and hot state conversion of turbine blade profile in liquid rocket engine[J].Journal of Rocket Propulsion,2018,44(02):33-38.
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REN Zhong,XU Kaifu,HAN Fei.Application of cold and hot state conversion of turbine blade profile in liquid rocket engine[J].Journal of Rocket Propulsion,2018,44(02):33-38.
涡轮叶型冷热态转换在液体火箭发动机中的应用
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
44
期数:
2018年02期
页码:
33-38
栏目:
研究与设计
出版日期:
2018-04-30
- Title:
- Application of cold and hot state conversion of turbine blade profile in liquid rocket engine
- 文章编号:
- 1672-9374(2018)02-0033-06
- Keywords:
- liquid rocket engine; turbine blade; deformation influence analysis; cold and hot state conversion
- 分类号:
- V431-34
- 文献标志码:
- A
- 摘要:
- 闭式循环液体火箭发动机涡轮叶片载荷大,温度分布复杂,叶片变形对气动参数影响显著。在以往的液体火箭发动机涡轮设计中,一般将设计出的叶片直接进行加工,而不考虑工作变形的影响。提出了一种叶片冷热态转换的方法,并以某发动机主涡轮为研究对象,首先通过气热固耦合仿真对比叶片变形对气动性能的影响,变形后的涡轮效率、流量、轴向力等参数均发生了显著变化,然后通过修正迭代对该叶片进行变形补偿,将热态工作叶片转化为冷态加工叶片。结果表明,该方法可以使叶型的气动参数得到精确控制,可开展工程应用。
- 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.
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备注/Memo
收稿日期:2017-04-23
作者简介: 任众(1987—),男,硕士,工程师,研究领域为液体火箭发动机涡轮泵设计
更新日期/Last Update:
1900-01-01