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[1]李炎栋,赵强,胡海峰,等.壳体开槽对诱导轮空化性能影响的数值分析[J].火箭推进,2024,50(02):122-129.[doi:10.3969/j.issn.1672-9374.2024.02.013]
　LI Yandong,ZHAO Qiang,HU Haifeng,et al.Numerical analysis on effects of case grooving on cavitation performance of inducer[J].Journal of Rocket Propulsion,2024,50(02):122-129.[doi:10.3969/j.issn.1672-9374.2024.02.013]
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壳体开槽对诱导轮空化性能影响的数值分析

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V] 卷: 50 期数: 2024年02期 页码: 122-129 栏目: 目次 出版日期: 2024-05-30
Title:
Numerical analysis on effects of case grooving on cavitation performance of inducer
文章编号:
1672-9374202402-0122-08
作者:
李炎栋; 赵强; 胡海峰; 项乐
西安航天动力研究所 航天液体动力全国重点实验室,陕西 西安710100
Author(s):
LI Yandong;  ZHAO Qiang;  HU Haifeng;  XIANG Le
National Key Laboratory of Aerospace Liquid Propulsion,Xi'an Aerospace Propulsion Institute, Xi'an 710100, China
关键词:
壳体开槽;  空化数;  扬程系数;  空化性能
Keywords:
case grooving;  cavitation number;  head coefficient;  cavitation performance
分类号:
V434.21
DOI:
10.3969/j.issn.1672-9374.2024.02.013
文献标志码:
A
摘要:
为了提高诱导轮的空化性能,建立了壳体开槽诱导轮模型,采用数值计算方法对比了基准结构诱导轮和壳体开槽诱导轮的空化流动特性,通过分析不同空化数下叶片吸力面压力分布、诱导轮内部空化区的分布状态及扬程系数的变化,揭示了壳体开槽提高诱导轮空化性能的详细机理。结果表明:壳体开槽改变了叶尖泄漏流的发展方向,在叶尖附近形成大尺度涡流,减小了压力面和吸力面之间的压力梯度,改善了诱导轮内部的压力分布。壳体开槽诱导轮的初生空化数小于基准结构诱导轮,对空化的产生有抑制作用; 随着空化数从0.37减小到0.086,空化区域不断扩大,扬程系数几乎保持不变。相同空化数下,壳体开槽诱导轮的扬程系数略低于基准结构,但空化区明显较小,对空化的发展有一定的抑制作用。随着空化数的进一步减小,当空化数达到某个值附近,扬程系数先略微上升后再陡降直至发生空化断裂,壳体开槽诱导轮的临界空化数更小; 从空化初生至空化断裂,壳体开槽诱导轮较基准结构诱导轮空化性能均有所提升。
Abstract:
In order to improve the cavitation performance of the inducer, a case grooving inducer was established, cavitation performance and flow characteristics of the reference structure inducer and the case grooving inducer were compared with numerical computation method. The detailed mechanism of improving cavitation performance in case grooving manner was revealed by analyzing pressure distribution on the suction surface of the blade, the distribution of the cavitation area inside the inducer, and head coefficient change with different cavitation number. The results show that case grooving changes direction of the tip leakage flow, which makes a large-scale vortex near the tip, reduces pressure gradient between the pressure surface and the suction surface, and improves pressure distribution inside the inducer. The inception cavitation number of the case grooving inducer is smaller than that of the reference structure inducer, which has an inhibiting effect on cavitation. As the cavitation number decreases from 0.370 to 0.086, the cavitation area continues to expand, and head coefficient almost remains constant. At the same cavitation number, head coefficient of the case grooving inducer is slightly lower than the reference structure, but the cavitation area is significantly smaller, which has a certain inhibitory effect on the expansion of cavitation. As the cavitation number further decreases, when the cavitation number reaches a certain value, the head coefficient first rises slightly and then drops sharply until cavitation crisis occurs. The critical cavitation number of case grooving inducer is smaller. From cavitation inception to cavitation crisis, cavitation performance of the case grooving inducer improves compared with that of the reference structure inducer.

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相似文献/References:

[1]唐 飞,李家文,李 永,等.提高液体火箭发动机诱导轮汽蚀性能的研究[J].火箭推进,2013,39(03):44.
　TANG Fei,LI Jia-wen,LI Yong,et al.Study on improving cavitation performance of inducer for liquid rocket engine[J].Journal of Rocket Propulsion,2013,39(02):44.

备注/Memo

收稿日期:2023- 07- 10 修回日期:2023- 08- 26
基金项目:国家联合基金(U1737112)
作者简介:李炎栋(1993—),男,硕士,工程师,研究领域为液体火箭发动机流动、传热与燃烧。

更新日期/Last Update: 1900-01-01