非对称波瓣上外扩张角对S弯二元喷管性能影响

推进技术 ›› 2015, Vol. 36 ›› Issue (11): 1616-1623.

非对称波瓣上外扩张角对S弯二元喷管性能影响

刘友宏,陈中原

北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点实验室，北京 100191,北京航空航天大学能源与动力工程学院/航空发动机气动热力国家级重点实验室，北京 100191

发布日期:2021-08-15
作者简介:刘友宏(1963—)，男，教授，博士，研究领域为发动机气动热力等。

Effects of Upward-Outward Penetration Angle of Asymmetric Lobed Mixer on Aerothermodynamic Performance of an S-Shaped Two-Dimensional Nozzle

National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics/School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China and National Key Laboratory of Science and Technology on Aero-Engine Aero-Thermodynamics/School of Energy and Power Engineering，Beijing University of Aeronautics and Astronautics，Beijing 100191，China

Published:2021-08-15

摘要/Abstract

摘要： 为了明确非对称波瓣上外扩张角对涡扇发动机S弯二元喷管流场、流向涡涡量场、热混合效率、总压恢复系数和壁面最高温度的影响，采用基于 Navier-Stokes(N-S)方程的三维数值模拟方法对不同非对称波瓣上外扩张角模型进行了定量研究，并得到了气动热力性能的影响规律。结果表明:非对称波瓣上外扩张角在5°～25°变化时，在波瓣尾缘处，流向涡的无量纲涡量随上外扩张角的增大而增大。在S弯二元喷管出口截面处，热混合效率随上外扩张角的增大而增大，总压恢复系数随上外扩张角的增大呈现出增大-减小-增大的趋势。S弯二元喷管的壁面最高温度随上外扩张角的增大先下降后升高，其中上外扩张角为10°壁面温度最低，约为426K。

关键词: S弯二元喷管；非对称波瓣；上外扩张角；热混合效率；总压恢复系数；壁面最高温度

Abstract: In order to clarify the effects of upward-outward penetration angle of asymmetric lobed mixer on flow field，streamwise vorticities，thermal mixing efficiency，total-pressure recovery factor and maximum wall temperature of the turbofan S-shaped two-dimensional nozzle，quantitative study on different upward-outward penetration angle of asymmetric lobed mixer was carried out through the three dimensional numerical simulation based on Navier-Stokes equations，and the principle of effects on aerothermodynamic performance was obtained. The results show that，when upward-outward penetration angle of asymmetric lobed mixer varies from 5° to 25°，non-dimensional streamwise vorticities increase at the trailing edge of the lobed mixer with the growing upward-outward penetration angle. At the exit section of the S-shaped two-dimensional nozzle，thermal mixing efficiency augments as the upward-outward penetration angle increases，and the total-pressure recovery coefficient has the trend of increasing，decreasing and increasing again. The maximum wall temperature of the S-shaped two-dimensional nozzle firstly decreases，and then increases with the growing upward-outward penetration angle，while the minimum wall temperature is at 10°，about 426K.

Key words: S-shaped two-dimensional nozzle；Asymmetric lobed mixer；Upward-outward penetration angle；Thermal mixing efficiency；Total-pressure recovery factor；Maximum wall temperature

刘友宏,陈中原. 非对称波瓣上外扩张角对S弯二元喷管性能影响[J]. 推进技术, 2015, 36(11): 1616-1623.

LIU You-hong,CHEN Zhong-yuan. Effects of Upward-Outward Penetration Angle of Asymmetric Lobed Mixer on Aerothermodynamic Performance of an S-Shaped Two-Dimensional Nozzle[J]. Journal of Propulsion Technology, 2015, 36(11): 1616-1623.

参考文献

[1] Rao G A, Mahulikar S P. Aircraft Powerplant and Plume Infrared Signature Modelling and Analysis[R]. AIAA 2005-221.
[2] 刘长春, 吉洪湖, 黄伟, 等. 一种双S弯二元喷管的红外辐射特性数值研究[J]. 航空动力学报, 2013, 28(7): 1482-1488.
[3] 章叶川, 王占学, 史经纬, 等. 双S弯喷管流动特性及红外辐射特性分析[J]. 航空动力学报, 2013, 28(11): 2468-2474.
[4] Presz W M. Mixer/ejector Noise Suppressors[R]. AIAA 91-2243.
[5] Presz W M, Reynolds G, Mccormick D C. Thrust Augment Using Mixer-Ejector-Diffuser Systems[R]. AIAA 94-0020.
[6] 张靖周, 李立国, 高潮, 等. 波瓣喷管红外抑制系统的实验研究[J]. 航空动力学报, 1997, 12(2): 212-214.
[7] 单勇, 张靖周, 邵万仁, 等. 某型涡扇排气系统缩比模型红外辐射特性实验[J]. 航空动力学报, 2009, 24(10): 2228-2234.
[8] Skebe S A, Paterson R W, Barber T J. Experimental Investigation of Three-Dimensional Forced Mixer Lobed Flow Fields[R]. AIAA 88-3785.
[9] 单勇, 张靖周. 波瓣喷管结构参数对引射混合器性能影响的数值研究[J]. 航空动力学报, 2005, 20(6): 973-977.
[10] 姜卫星. 波瓣喷管引射特性实验与流场数值计算[D]. 南京:南京航空航天大学, 1997.
[11] 刘友宏, 张少鹏, 杨旭, 等. 波瓣尾缘切角对涡扇发动机混合排气系统气动热力性能影响[J]. 推进技术, 2013, 34(6): 734-740. (LIU You-hong, ZHANG Shao-peng, YANG Xu, et al. Effects of Cut Angles at Trailing Edge of Lobe on Aerothermodynamic Performance of Forced Mixing Exhaust System in Turbofan Engine[J]. Journal of Propulsion Technology, 2013, 34(6): 734-740.)
[12] 刘友宏, 郭楠. 后缘切角对波瓣混合器性能影响[J]. 航空动力学报, 2009, 24(9): 1917-1922.
[13] 刘友宏, 谢翌, 郭楠. 尾缘凹扇及综合修型对波瓣混合器性能影响[J]. 航空动力学报, 2010, 25(2): 234-250.
[14] 谢翌, 阮登芳, 钟晨, 等. 波瓣帽罩结构和脊线对混合排气系统性能影响[J]. 推进技术, 2014, 35(3): 314-319. (XIE Yi, RUAN Deng-fang, ZHONG Chen, et al. Effects of Lobe Cap and Crest Line on Performance of Mixing Exhaust System[J]. Journal of Propulsion Technology, 2014, 35(3): 314-319.)
[15] Nathan J Cooper, Parviz Merati, Hui Hu. Numerical Simulation of the Vortical Structures in a Lobed Jet Mixing Flow[R]. AIAA 2005-635.
[16] 李立国, 张靖周. 航空用引射混合器[M]. 北京:国防工业出版社, 2007.
[17] Waitz I A, Qiu Q J. Enhanced Mixing with Streamwise Vorticity[J]. Progress in Aerospace Sciences, 1997, 33(5-6): 323-351.
[18] Frost T H. Practical Bypass Mixing Systems for Fan Jet Aero-Engines[J]. Aeronautical Quarterly, 1966, 17: 141-160.
[19] XIE Yi, LIU You-hong. A Modified Thermal Mixing Efficiency and Its Application to Lobed Mixer Nozzle for Aero-Engines[J]. Heat Transfer Research, 2011, 42(4): 317-335.
[20] Xie Y, Liu Y. Numerical Investigation of Mixing Length on Performance of Lobed Forced Mixer Nozzles[J]. Heat Transfer—Asian Research, 2011, 40(3): 205-216.
[21] 刘友宏, 李立国. 有中心锥圆排波瓣喷管引射器内流场模拟[J]. 推进技术, 2002, 23(2): 150-153. (LIU You-hong, LI Li-guo. Numerical Simulation of Flow Field in Circularly Lobed Exhaust Ejector Mixer with a Central Plug[J]. Journal of Propulsion Technology, 2002, 23(2): 150-153.)
[22] 刘友宏, 陈锵, 李立国. 圆排波瓣圆柱混合管的气动特性实验研究[J]. 南京航空航天大学学报, 2000, 32(4): 375-380.(编辑:朱立影)　　　　　　　　　　　　　*　收稿日期:2014-07-04；修订日期:2014-11-03。作者简介:刘友宏(1963—),男,教授,博士,研究领域为发动机气动热力等。E-mail: liuyh@buaa.edu.cn