翅片位置对复合式减涡器减阻性能影响数值模拟

doi:10.13675/j.cnki.tjjs.190647

推进技术 ›› 2020, Vol. 41 ›› Issue (10): 2197-2203.DOI: 10.13675/j.cnki.tjjs.190647

翅片位置对复合式减涡器减阻性能影响数值模拟

侯晓亭，王锁芳，张凯，夏子龙

南京航空航天大学能源与动力学院，航空发动机热环境与热结构工业和信息化部重点实验室，江苏南京 210016

发布日期:2021-08-15
作者简介:侯晓亭，硕士生，研究领域为发动机流动与冷却。E-mail：1085972278@qq.com
基金资助:
国家科技重大专项（2017-III-0011-0037）。

Numerical Investigation on Effects of Fins Position on Drag Reduction Performance of Composite Vortex Reducer Device

Key Laboratory of Aero-Engine Thermal Environment and Structure，Ministry of Industry and Information Technology，College of Energy and Power Engineering，Nanjing University of Aeronautics and Astronautics，Nanjing 210016，China

Published:2021-08-15

摘要/Abstract

摘要： 为了探索翅片-管复合式减涡器的翅片安装位置对共转盘腔径向内流压力损失的影响规律，对不同转速、翅片周向位置及安装角度下的去旋系统开展了数值研究，得到了不同工况下共转盘腔径向内流的流场结构及压力损失分布曲线。研究结果表明：减涡管能引导流体径向流入，并降低流体的旋流比；相比于管式减涡器，翅片-管复合式减涡器能明显降低盘腔内的总压损失；在不同旋转雷诺数下，翅片的周向安装位置α及安装角β均存在最佳值；在中、高旋转雷诺数下，最佳值分别为α=9°，β=30°，最佳结构下总压损失较基础模型低40%左右；改变翅片周向位置及安装角度可以明显改变气流进入减涡管的角度，在较优情况下，可以减小流体流入减涡管的阻力及在减涡管内的流动阻力，整体上减小了盘腔内总压损失。

关键词: 压气机;共转盘腔;减涡器;涡流;流场结构;总压损失

Abstract: To research the effects of the fins installation position of the fins-tube composite vortex reducer on the radial inflow pressure loss of the co-rotating cavity， numerical simulation was carried out to calculate the de-swirl system under different rotating speed， circumferential position and the installation angle. The flow field structure and pressure loss curve of the radial inflow in the co-rotating cavity under different working conditions were obtained. The results show that the tube can guide the radial inflow of fluid and reduce the swirl ratio of fluid. Compared with the vortex reducer with tube， the fins-tube composite vortex reducer can obviously reduce the total pressure loss in the disc cavity. Under different rotation Reynolds numbers， the circumferential installation position α and the installation angle β of the fins have the best value. At the middle and high rotating Reynolds numbers， the optimum values are α=9° and β=30°， respectively， the total pressure loss under the optimum structure is about 40% lower than that of the basic model. Changing the circumferential position and the installation angle of the fins can obviously change the angle of the air flow into the tube. Under the better condition， the flow resistance of the fluid flowing into the tube and the flow resistance in the tube can be reduced， and the total pressure loss in the disc cavity can be reduced as a whole.

Key words: Compressor;Co-rotating cavity;Vortex reducer;Vortex flow;Flow structure;Total pressure loss

侯晓亭，王锁芳，张凯，夏子龙. 翅片位置对复合式减涡器减阻性能影响数值模拟[J]. 推进技术, 2020, 41(10): 2197-2203.

HOU Xiao-ting, WANG Suo-fang, ZHANG Kai, XIA Zi-long. Numerical Investigation on Effects of Fins Position on Drag Reduction Performance of Composite Vortex Reducer Device[J]. Journal of Propulsion Technology, 2020, 41(10): 2197-2203.

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翅片位置对复合式减涡器减阻性能影响数值模拟

Numerical Investigation on Effects of Fins Position on Drag Reduction Performance of Composite Vortex Reducer Device

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