亚声速部分进气涡轮数值模拟及优化设计  

Numerical simulation and design optimization of subsonic partial admission turbine

作　　者：毛凯[1] 王晓锋[1] 袁伟为 蒋建园 MAO Kai;WANG Xiaofeng;YUAN Weiwei;JIANG Jianyuan(Xi'an Aerospace Propulsion Institute,Xi'an 710100, China)

机构地区：[1]西安航天动力研究所,陕西西安710100

出　　处：《火箭推进》2019年第1期25-30,共6页Journal of Rocket Propulsion

基　　金：国家重大基础研究项目(613321)

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。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.

关 键 词：亚声速 部分进气 涡轮 损失分析 进排气结构 

分 类 号：V430[航空宇航科学与技术—航空宇航推进理论与工程]