航天推进技术研究院主办
[1]张忠利,张蒙正,李福云.液体火箭发动机涡轮壳体温度偏高原因研究[J].火箭推进,2013,39(02):35-39.
ZHANG Zhong-li,ZHANG Meng-zheng,LI Fu-yun.Investigation on reason of overheating of turbine housing in liquid rocket engine[J].Journal of Rocket Propulsion,2013,39(02):35-39.
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ZHANG Zhong-li,ZHANG Meng-zheng,LI Fu-yun.Investigation on reason of overheating of turbine housing in liquid rocket engine[J].Journal of Rocket Propulsion,2013,39(02):35-39.
液体火箭发动机涡轮壳体温度偏高原因研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
39
期数:
2013年02期
页码:
35-39
栏目:
研究与设计
出版日期:
2013-04-30
- Title:
- Investigation on reason of overheating of turbine housing in liquid rocket engine
- 文章编号:
- 1672-9374(2013)02-0035-05
- 分类号:
- V434.2-34
- 文献标志码:
- A
- 摘要:
- 分析了液体火箭发动机001~003试车时发生器排气壳体和涡轮进排气壳体的温度变化情况。应用非稳态传热方法对实际结构仿真了003次试车时发生器在不同流量、不同效率时涡轮壳体温度的变化情况，得出了该次试车时涡轮壳体温度偏高的主要原因是发生器燃烧效率偏高。
- Abstract:
- The temperature variation of gas-generator exhausting shell and turbine's inlet-outlet housing are analyzed during No. 001~003 hot test of liquid rocket engine (LRE). With unsteady heat transfer methods, the temperature variation of turbine housing caused by the gas-generator working at different flow rate and efficient in the 003 time hot test were simulated. The simulation result shows that the overheating of turbine housing is because of too much high efficiency of gas-generator.
参考文献/References:
[1]朱宁昌, 董锡鉴, 王新龄, 等. 液体火箭发动机设计[M]. 北京: 中国宇航出版社, 1993.
[2]张金容, 靳爱国, 汪亮. 泵压式液体火箭发动机变推力方案选择[J]. 航空动力学报, 2008, 23(5): 921-926.
[3]李斌. 液体火箭发动机结构可靠性设计与分析[D]. 国防科学技术大学, 2006.
[4]张忠利. 高空滑行期间氧化剂泵壳体冷却方案研究[J]. 火箭推进, 2004, 30(5): 22-27.
[5]张忠利. 液体火箭发动机自引射工作过程传热研究[J]. 火箭推进, 2012, 38(1): 31-36.
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备注/Memo
收稿日期：2012-09-25；修回日期：2012-11-14
基金项目：国家863项目（2006AA702306)
作者简介：张忠利（1970—），男，高级工程师，研究领域为液体火箭发动机传热分析
更新日期/Last Update:
1900-01-01