出口宽高比及旋流角对双涵道S弯喷管温度分布的影响

孙鹏; 周莉; 王占学; 史经纬

doi:10.13224/j.cnki.jasp.20210149

出口宽高比及旋流角对双涵道S弯喷管温度分布的影响

doi: 10.13224/j.cnki.jasp.20210149

西北工业大学动力与能源学院，西安 710072

基金项目: 国家自然科学基金（51876176，52076180，51906204）；国家科技重大专项（J2019-Ⅱ-0015-0036）；陕西省杰出青年基金（2021JC-10）

详细信息

作者简介:
孙鹏（1991-），男，博士生，主要从事S弯异形喷管流动及气动变形方面的研究。

通讯作者:
周莉（1978-），女，教授、博士生导师，博士，研究领域为排气系统设计及流动控制技术。E-mail：zhouli@nwpu.edu.cn

中图分类号: V231.1
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出版历程
- 收稿日期: 2021-04-06
- 刊出日期: 2022-02-28

Effect of aspect ratio and swirl angle on temperature distribution of double serpentine nozzle for turbofan

School of Power and Energy，Northwestern Polytechnical University，Xi'an 710072，China

摘要

摘要: 采用数值方法研究了出口宽高比及旋流角对基于真实排气混合器构型的双涵道S弯喷管内/外流场温度分布的影响。结果显示：在圆转方弯曲构型的作用下，波瓣混合器及尾锥诱导产生的流向涡在第二弯通道及等直段内部卷吸着热流冲击S弯喷管壁面形成“热斑”。在完全遮挡高温部件准则的约束下，随着出口宽高比的增加，S弯喷管壁面的“热斑”温度先增大后减小，当出口宽高比为5时，壁面“热斑”温度最高，相比喷管基准模型增加1.3%。而出口宽高比的增加导致喷管出口下游尾焰的长度逐渐缩短。随着旋流角的增加，喷管下壁面的“热斑”温度先减小后增大，旋流角为10°时达到最小值，壁面温度峰值相比无旋流角工况降低15.9%。而旋流角增加导致喷管出口下游尾焰的宽度逐渐增大，长度逐渐缩短。
- 双涵道S弯喷管 /
- 出口宽高比 /
- 旋流角 /
- 热斑 /
- 尾焰
Abstract: The effects of the aspect ratio and the swirl angle on the temperature distributions of the internal flow and external jet fields of the double serpentine nozzle with real lobed mixer configuration were numerically investigated.The results indicated that，under the action of the bending configuration with the circular-to-rectangular transition，the streamwise vortices induced by the lobed mixer and the tail cone entrained the core flow to impact the nozzle wall，and the “hot streak” was formed at the wall surface of the second S passage and the linear section.Under the constraint of the criterion of completely shielding high temperature components，the tempera-ture of the “hot streak” on the nozzle wall first increased and then decreased as the aspect ratio raised gradually.The value of the temperature peak of the “hot streak” was up to maximum when the aspect ratio was 5.It rose by 1.3% compared with that in the benchmark nozzle model.The plume core region downstream the nozzle exit was shortened effectively with the increment of the aspect ratio.The temperature of the “hot streak” on the nozzle lower wall first decreased and then increased as the swirl angle raised sustainedly.The value of the temperature peak of the “hot streak” was up to minimum when the swirl angle was 10°.It dropped by 15.9% compared with that under the condition of 0° swirl angle.The lateral width of the plume core region downstream the nozzle exit was enlarged notably while its axial length was shortened effectively with the increment of the swirl angle.
- double serpentine nozzle /
- aspect ratio /
- swirl angle /
- hot streak /
- plume core region

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参考文献(21)

[1]	赵鸿燕，倪永平，王秀萍.红外探测器的发展及其在空空导弹上的应用[J].飞航导弹，2008（7）:46-49.
[2]	邓洪伟，尚守堂，金海，等.航空发动机隐身技术分析与论述[J].航空科学技术，2017（10）:1-7.
[3]	BARANWAL N，MAHULIKAR S P.Infrared signature of aircraft engine with choked converging nozzle[J].Journal of Thermophysics and Heat Transfer，2016，30（4）:854-862.
[4]	JOHANSSON M.FOT25 2003-2005 propulsion integration：final report[R].Stockholm,Sweden:Swedish Defence Research Agency，FOI-R-2017-SE，2006.
[5]	ERWIN L，MARKUS R.IR-signature of the MULDICON configuration determined by the IR-signature model MIRA[R].AIAA-2018-3166，2018.
[6]	RONALD J S.Design and control of a variable geometry turbofan with an independently modulated third stream[D].Columbus，US:The Ohio State University，2009.
[7]	AN C H，KANG D W，BAEK S T，et al.Analysis of plume infrared signatures of S-shaped nozzle configurations of aerial vehicle[J].Journal of Aircraft，2016，53（6）:1768-1778.
[8]	RAJKUMAR P，CHANDRA S T，KUSHARI A，et al.Flow characterization for a shallow single serpentine nozzle with aft deck[J].Journal of Propulsion and Power，2017，33（5）:1130-1139.
[9]	SUN Xiaolin，WANG Zhanxue，ZHOU Li，et al.Experimental and computational investigation of double serpentine nozzle[J].Proceedings of the Institution of Mechanical Engineers:Part G Journal of Aerospace Engineering，2015，299 （11）:2035-2050.
[10]	CROWE D S，MARTIN C L.Hot streak characterization in serpentine exhaust nozzles[R].AIAA-2016-4502，2016.
[11]	MARKUS R,SEBASTIAN K,ERWIN L.Numerical investigation of engine exhaust plume characteristics of unmanned combat air vehicles[R].AIAA-2014-2838，2014.
[12]	MATS D,LARS T.IR signature design effort on the MULDICON configuration[R].AIAA-2018-3167,2018.
[13]	HANEY M A.Topology optimization of engine exhaust-washed structures[D].Dayton,US:The Wright State Uni-versity，2006.
[14]	DEATON J D,GRANDHI R V.Thermal-structural analy-sis of engine exhaust-washed structures[R].AIAA-2010-9236，2010.
[15]	刘常春，吉洪湖.S弯二元喷管红外辐射特性实验[J].航空动力学报，2019，34（7）:1493-1500.
[16]	于明飞，吉洪湖，李宁，等.小偏距S弯二元喷管的红外辐射特性数值分析[J].航空动力学报，2015，30（9）:2080-2087.
[17]	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.
[18]	WEN Cheng，WANG Zhanxue，ZHOU Li，et al.Infrared signature of serpentine nozzle with different aspect ratio[R].International Symposium of Air Breathing Engine ISABE-2017-21357，2017.
[19]	SUN Xiaolin，WANG Zhanxue，ZHOU Li，et al.Flow characteristics of double serpentine convergent nozzle with different inlet configuration[J].Journal of Engineering for Gas Turbines and Power，2018，140（8）:082602.1-082602.12.
[20]	ROACHE P J.Quantification of uncertainty in computational fluid dynamics[J].Annual Review of Fluid Mechanics，1997，29（1）:123-160.
[21]	CROWE D S，MARTIN C L.Hot streak characterization of high performance double serpentine exhaust nozzles at design conditions[J].Journal of Propulsion and Power，2019，35（3）:501-511.