航天推进技术研究院主办
[1]毛 凯,王晓锋,袁伟为,等.亚声速部分进气涡轮数值模拟及优化设计[J].火箭推进,2019,45(01):25-30.
MAO Kai,WANG Xiaofeng,YUAN Weiwei,et al.Numerical simulation and design optimization of subsonic partial admission turbine[J].Journal of Rocket Propulsion,2019,45(01):25-30.
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MAO Kai,WANG Xiaofeng,YUAN Weiwei,et al.Numerical simulation and design optimization of subsonic partial admission turbine[J].Journal of Rocket Propulsion,2019,45(01):25-30.
亚声速部分进气涡轮数值模拟及优化设计
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
45
期数:
2019年01期
页码:
25-30
栏目:
研究与设计
出版日期:
2019-02-28
- Title:
- Numerical simulation and design optimization of subsonic partial admission turbine
- 文章编号:
- 1672-9374(2019)01-0025-06
- 分类号:
- V430
- 文献标志码:
- A
- 摘要:
- 基于SST湍流模型,通过求解雷诺平均的Navier-Stokes方程组,对某亚声速、部分进气形式涡轮全流场进行三维粘性定常仿真计算。共计算了4种模型,分别包含不同的损失通道,获取了涡轮部件各通道的具体损失量值。计算结果表明:原涡轮叶片通道损失、泄漏损失、部分进气损失基本处于较低水平。涡轮进排气结构性能差,内部流动混乱,存在大量分离涡,对涡轮效率影响很大,具有较大提升空间。通过涡轮进气和排气结构的优化改进,采用切向进气和切向排气的变截面蜗壳形式结构,三维仿真结果表明:优化后涡轮部件效率从0.675提高至0.706,增加了4.59%,且涡轮轴向尺寸大幅度缩减。
- Abstract:
- Based on the SST turbulence model, by solving RANS-Navier-stokes equations, a three-dimensional, viscous, steady analysis was performed for turbine full flow field with partial admission and subsonic characteristics.In order to obtain the specific amount of loss of each channel, four models were calculated, which contain different loss passages.Results show that the original turbine's blade passage loss, leakage loss and partial admission loss are at a low level.The performance of intake and exhaust structure is poor, with messy internal flow and a large amount of separation vortexes, which has a great impact on turbine efficiency and great space for improvement.Finally, through the optimization of turbine intake and exhaust structure, the variable cross-section volute structure with tangential intake and tangential exhaust was adopted.Three-dimensional calculations show that efficiency of turbine components after optimization is increased from 0.675 to 0.706(an increase of 4.59%)and turbine axial size is greatly reduced.
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备注/Memo
收稿日期:2018-03-02
基金项目:国家重大基础研究项目(613321)
作者简介:毛 凯,(1987—),男,硕士,研究领域为液体火箭发动机涡轮泵设计
更新日期/Last Update:
2019-02-20