航天推进技术研究院主办
[1]毛 凯,李昌奂,张 聃,等.高压液氧涡轮泵孔型/蜂窝阻尼密封的设计[J].火箭推进,2021,47(02):47-53.
MAO Kai,LI Changhuan,ZHANG Dan,et al.Design of the hole-pattern/honeycomb seals in the high-pressure liquid oxygen turbopump[J].Journal of Rocket Propulsion,2021,47(02):47-53.
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MAO Kai,LI Changhuan,ZHANG Dan,et al.Design of the hole-pattern/honeycomb seals in the high-pressure liquid oxygen turbopump[J].Journal of Rocket Propulsion,2021,47(02):47-53.
高压液氧涡轮泵孔型/蜂窝阻尼密封的设计
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
47
期数:
2021年02期
页码:
47-53
栏目:
研究与设计
出版日期:
2021-04-21
- Title:
- Design of the hole-pattern/honeycomb seals in the high-pressure liquid oxygen turbopump
- 文章编号:
- 1672-9374(2020)06-0000-07
- Keywords:
- liquid oxygen turbopump; hole-pattern/honeycomb seal; optimization design; sealing performance
- 分类号:
- V434.21
- 文献标志码:
- A
- 摘要:
- 针对某型火箭发动机高压液氧涡轮泵离心轮的前、后凸肩动密封,采用孔型/蜂窝阻尼密封代替原始迷宫密封方案,并对密封结构参数进行优化设计,旨在减小泵内动静间隙泄漏,提高泵容积效率。采用经水工质孔型密封泄漏量实验数据验证的,基于k-ε湍流模型和三维定常Reynolds-Averaged Navier-Stokes(RANS)方程的液体孔型密封泄漏量数值计算方法,研究了孔深、孔径对液氧孔型阻尼密封、蜂窝阻尼密封泄漏特性的影响规律,并与迷宫密封的封严性能进行了比较。计算分析了8种孔径(0.3～2.0 mm)下、孔深在0.1～2.0 mm范围内连续变化时孔型阻尼密封的泄漏量。结果表明:相同孔径和孔深下,孔型阻尼密封和蜂窝阻尼密封具有相近的封严性能,均优于迷宫密封; 有限的密封轴向长度下,液氧孔型/蜂窝阻尼密封泄漏量随孔径的增大(轴向孔数目减小)先减小后增大,孔型/蜂窝阻尼密封最佳孔径为1.4 mm; 不同孔径下,液氧孔型/蜂窝密封均存在最佳深径比0.5,泄漏量达到最小值; 相比于原始迷宫密封方案,优化设计的孔型/蜂窝阻尼密封使液氧涡轮泵离心轮前、后凸肩动密封泄漏量分别减小了约19%和21%。
- Abstract:
- To reduce the leakage flow rates and improve the operation efficiency of the turbopump, as the replacement sealing scheme of the conventional labyrinth seal, the hole-pattern seal and honeycomb seal were designed and optimized for the front and rear shoulder rotating seals of the high-pressure liquid oxygen turbopump in a liquid rocket engine.The present numerical method based on the RNG k-ε turbulence model and steady RANS solutions were validated by comparisons to experiment data of leakage flow rates of a water-fed hole-pattern seal at different rotational speeds.The influences of the hole depth and hole diameter on the leakage performance of the hole-pattern and honeycomb seals were numerically investigated, and comparisons to the conventional labyrinth seal were also presented.The leakage flow rates were computed for the hole-pattern seal with continuously variable hole depth(0.1～2.0 mm)at eight hole diameters(0.3～2.0 mm).The results show that with the same hole geometry parameters(depth and diameter), the hole-pattern seal and the honeycomb seal possess the similar sealing performance which are both better than the conventional labyrinth seal.With the constant seal axial length, the leakage flow rates of the hole-pattern/honeycomb seals firstly decrease and then increase with the increasing hole diameter whose optimum value is 1.4 mm in this paper.For all the hole diameter cases, the hole-pattern/honeycomb seal possess the optimum ratio of the hole depth to diameter 0.5, where the best sealing performance were obtained.Compared to the conventional labyrinth seal, the leakage flow rates through the front and rear rotating seals of the high-pressure liquid oxygen turbopump were reduced by about 19% and 21% respectively, when the optimized hole-pattern/honeycomb seal were introduced.
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备注/Memo
收稿日期:2019-06-20
基金项目:国家重大基础研究项目(613321)
作者简介:毛凯(1987—),硕士,研究领域为液体火箭发动机涡轮泵。
更新日期/Last Update:
1900-01-01