| Citation: | CHENG Jingli, HUANG Sheng, ZHOU Li, et al. Investigation on influence mechanism of aspect ratio on thermal-solid interaction response of serpentine nozzle[J]. Journal of Aerospace Power, 2025, 40（4）：20230480 doi: 10.13224/j.cnki.jasp.20230480
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In order to clarify the effect of the first bend width ratio on the flow heat transfer and structural response of the serpentine nozzle, the effects of the thermal-solid coupling responses under different first bend width ratios were investigated by using the two-way loose coupling method. The results showed that the structural characteristics of multiple bends and different cross sections along the path complicated the heat transfer inside the nozzle, the overall heat flux distribution of the serpentine nozzle was non-uniform, and the heat transfer was strongest on the upper wall at the first bend; with the increase of the width ratio of the first bend, the heat flux of the upper wall at the first bend increased; the vortex structures of the straight section of the nozzle exit made the heat transfer blocked and the heat flux lower; in the temperature response, all nozzles produced extreme values of temperature on the upper wall at the first bend, which were subsequently shifted to the inlet, and the nozzle with a width ratio of 0.715 of the first bend produced extreme values of temperature near the position of the inlet on the lower wall, unlike the rest of the nozzles; the stresses of all serpentine nozzles increased and then decreased with time. As the width ratio of the first bend increased, the moment of maximum stress in each nozzle was delayed and the maximum stress decreased; the nozzle with a width ratio of 0.715 at the first bend was the first to show a stress maximum of 159.346 MPa, which was 10.3 s earlier and 27.2% less compared with the nozzle of a configuration with a width ratio of 1.165 at the first bend.
| [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. ZHAO Hongyan,NI Yongping,WANG Xiuping. Development of infrared detector and its application in air-to-air missile[J]. Winged Missiles Journal,2008(7): 46-49. (in Chinese
ZHAO Hongyan, NI Yongping, WANG Xiuping. Development of infrared detector and its application in air-to-air missile[J]. Winged Missiles Journal, 2008(7): 46-49. (in Chinese)
|
| [2] |
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. doi: 10.2514/1.T4641
|
| [3] |
JOHANSSON M. FOT25 2003-2005 propulsion integration: final report: FOI-R-2017-SE[R]. Stockholm,Sweden: Swedish Defence Research Agency,2006.
|
| [4] |
LINDERMEIR E,RUETTEN M. IR-signature of the MULDICON configuration determined by the IR-signature model MIRA: AIAA2018-3166 [R]. Reston,US: AIAA,2018.
|
| [5] |
SUN X L,WANG Z X,ZHOU L,et al. Experimental and computational investigation of double serpentine nozzle[J]. Proceedings of the Institution of Mechanical Engineers: Part G Journal of Aerospace Engineering,2015,229(11): 2035-2050. doi: 10.1177/0954410014564402
|
| [6] |
SMITH J,DALENBRING M. Aeroelastic simulation of S-duct dynamics using structure-coupled CFD: FOI SE-164 90 [R]. Stockholm,Sweden: Swedish Defence Research Agency,2006.
|
| [7] |
孙鹏,周莉,王占学,等. 双S弯喷管的流固耦合特性研究[J]. 推进技术,2022,43(10): 210349. SUN Peng,ZHOU Li,WANG Zhanxue,et al. Fluid-structure interaction characteristic of double serpentine nozzle[J]. Journal of Propulsion Technology,2022,43(10): 210349. (in Chinese
SUN Peng, ZHOU Li, WANG Zhanxue, et al. Fluid-structure interaction characteristic of double serpentine nozzle[J]. Journal of Propulsion Technology, 2022, 43(10): 210349. (in Chinese)
|
| [8] |
李秋琳,周莉,孙鹏,等. 出口宽高比对S弯喷管流固耦合特性影响[J]. 航空学报,2023,44(14): 628204. LI Qiulin,ZHOU Li,SUN Peng,et al. Influence mechanism of aspect ratio on fluid-structure interaction characteristics of serpentine nozzle[J]. Acta Aeronautica et Astronautica Sinica,2023,44(14): 628204. (in Chinese
LI Qiulin, ZHOU Li, SUN Peng, et al. Influence mechanism of aspect ratio on fluid-structure interaction characteristics of serpentine nozzle[J]. Acta Aeronautica et Astronautica Sinica, 2023, 44(14): 628204. (in Chinese)
|
| [9] |
VOGEL R,GRANDHI R. Structural acoustic analysis and design of aircraft components: AIAA 2012-5557 [R]. Reston,US: AIAA,2012.
|
| [10] |
CROWE D S,MARTIN C L. Effect of geometry on exit temperature from serpentine exhaust nozzles: AIAA2015-1670 [R]. Reston,US: AIAA,2015.
|
| [11] |
CROWE D S,MARTIN C L. Hot streak characterization in serpentine exhaust nozzles: AIAA2016-4502 [R]. Reston,US: AIAA,2016.
|
| [12] |
HUI Z H,SHI J W,ZHOU L,et al. The influence of the adverse pressure gradient on the flow characteristics of a serpentine nozzle with film cooling[J]. Aerospace Science and Technology,2023,136: 108256. doi: 10.1016/j.ast.2023.108256
|
| [13] |
HUI Z H,SHI J W,ZHOU L,et al. Effect of inclination angle on the film cooling in a serpentine nozzle with strong adverse pressure gradient[J]. Physics of Fluids,2023,35(4): 046114. doi: 10.1063/5.0147749
|
| [14] |
FENRICH R W,ALONSO J J. Reliable multidisciplinary design of a supersonic nozzle using multifidelity surrogates: AIAA2017-3826 [R]. Reston,US: AIAA,2017.
|
| [15] |
DEATON J,GRANDHI R. Thermal-structural analysis of engine exhaust-washed structures: AIAA 2010-9236[R]. Reston,US: AIAA,2010.
|
| [16] |
DEATON J D,GRANDHI R V. Significance of geometric nonlinearity in the design of thermally loaded structures: AIAA 2015-1431[R] Reston,US: AIAA,2015.
|
| [17] |
NIGAM N,AYYALASOMAYAJULA S K,TANG Y Y,et al. Design optimization of advanced exhaust systems: AIAA 2017-3331 [R]. Reston,US: AIAA,2017.
|
| [18] |
URBANCZYK P S,ALONSO J J,NIGAM N,et al. Coupled multiphysics analysis for design of advanced exhaust systems: AIAA2017-0799 [R] Reston,US: AIAA,2017.
|
| [19] |
程经理,黄盛,周莉,等. 出口宽高比对S弯喷管热固耦合响应的影响[J]. 航空动力学报,2025, 40(2):20230228. CHENG Jingli,HUANG Sheng,ZHOU Li,et al. Investigation on influence mechanism of aspect ratio on thermal-solid interaction response of serpentine nozzle[J]. Journal of Aerospace Power,2025, 40(2):20230228. (in Chinese
CHENG Jingli, HUANG Sheng, ZHOU Li, et al. Investigation on influence mechanism of aspect ratio on thermal-solid interaction response of serpentine nozzle[J]. Journal of Aerospace Power, 2025, 40(2): 20230228. (in Chinese)
|
| [20] |
程经理,黄盛,周莉,等. 第一弯出口面积比对 S 弯喷管热固耦合响应影响研究[J]. 航空动力学报,2025, 40(3):20230229. CHENG Jingli,HUANG Sheng,ZHOU Li,et al. Investigation on influence mechanism of area ratio of first bend on thermal-solid interaction reponse of serpentine nozzle[J]. Journal of Aerospace Power,2025, 40(3):20230229. (in Chinese
CHENG Jingli, HUANG Sheng, ZHOU Li, et al. Investigation on influence mechanism of area ratio of first bend on thermal-solid interaction reponse of serpentine nozzle[J]. Journal of Aerospace Power, 2025, 40(3): 20230229. (in Chinese)
|
| [21] |
SUN X L,WANG Z X,ZHOU L,et al. Influences of design parameters on a double serpentine convergent nozzle[J]. Journal of Engineering for Gas Turbines and Power,2016,138(7): 072301. doi: 10.1115/1.4032338
|
| [22] |
孙啸林. 低可探测S弯喷管设计及性能评估方法研究[D]. 西安: 西北工业大学,2018. SUN Xiaolin. Investigation on design method and performance estimation of low observable S-shaped nozzle[D]. Xi’an: Northwestern Polytechnical University,2018. (in Chinese
SUN Xiaolin. Investigation on design method and performance estimation of low observable S-shaped nozzle[D]. Xi’an: Northwestern Polytechnical University, 2018. (in Chinese)
|
| [23] |
程稳. S弯喷管红外辐射特性预测及优化设计方法[D]. 西安: 西北工业大学,2019. CHENG Wen. Infrared signature prediction and optimization design method for serpentine nozzle[D]. Xi’an: Northwestern Polytechnical University,2019. (in Chinese
CHENG Wen. Infrared signature prediction and optimization design method for serpentine nozzle[D]. Xi’an: Northwestern Polytechnical University, 2019. (in Chinese)
|
| [24] |
夏刚,刘新建,程文科,等. 钝体高超声速气动加热与结构热传递耦合的数值计算[J]. 国防科技大学学报,2003,25(1): 35-39. XIA Gang,LIU Xinjian,CHENG Wenke,et al. Numerical simulation of coupled aeroheating and solid heat penetration for a hypersonic blunt body[J]. Journal of National University of Defense Technology,2003,25(1): 35-39. (in Chinese doi: 10.3969/j.issn.1001-2486.2003.01.008
XIA Gang, LIU Xinjian, CHENG Wenke, et al. Numerical simulation of coupled aeroheating and solid heat penetration for a hypersonic blunt body[J]. Journal of National University of Defense Technology, 2003, 25(1): 35-39. (in Chinese) doi: 10.3969/j.issn.1001-2486.2003.01.008
|
| [25] |
Fraunhofer Institute for Algorithms and Scientific Computing. MPCCI: mesh based parallel code coupling interface 4.1.0 user manual [R]. Sankt Augustin,German: Fraunhofer Institute for Algorithms and Scientific Computing,2011.
|
| [26] |
WIETING A. Experimental study of shock wave interference heating on a cylindrical leading edge: NASA-TM-100484 [R]. Hampton,US: NASA Langley Research Center,1987.
|
| [27] |
DECHAUMPHAI P,THORNTON E A,WIETING A R. Flow-thermal-structural study of aerodynamically heated leading edges[J]. Journal of Spacecraft and Rockets,1989,26(4): 201-209. doi: 10.2514/3.26055
|
| [28] |
DECHAUMPHAI P,WIETING A,THORNTON E. Flow-thermal-structural study of aerodynamically heated leading edges: AIAA 1988-2245 [R]. Reston,US: AIAA,1988.
|
| [29] |
郭帅. 高超声速飞行器关键部件的多物理场耦合研究[D]. 南京: 南京航空航天大学,2016. GUO Shuai. Multidisciplinary study of key components in hypersonic flight vehicle[D]. Nanjing: Nanjing University of Aeronautics and Astronautics,2016. (in Chinese
GUO Shuai. Multidisciplinary study of key components in hypersonic flight vehicle[D]. Nanjing: Nanjing University of Aeronautics and Astronautics, 2016. (in Chinese)
|
| [30] |
黄杰. 高超声速飞行器流热固多物理场耦合计算研究[D]. 哈尔滨: 哈尔滨工业大学,2013. HUANG Jie. Study on hypersonic vehicle fluid-thermal-structure multi-physics coupling calculation[D]. Harbin: Harbin Institute of Technology,2013. (in Chinese
HUANG Jie. Study on hypersonic vehicle fluid-thermal-structure multi-physics coupling calculation[D]. Harbin: Harbin Institute of Technology, 2013. (in Chinese)
|
| [31] |
BILLIG F S. Shock-wave shapes around spherical-and cylindrical-nosed bodies[J]. Journal of Spacecraft and Rockets,1967,4(6): 822-823. doi: 10.2514/3.28969
|
| [32] |
ZOPE A D,SCHEMMEL A,BHATIA M,et al. Development and validation of fluid-thermal interaction solver for high fidelity transient simulations: AIAA2020-3006 [R]. Reston,US: AIAA,2020.
|
| [33] |
KAMALI S,MAVRIPLIS D J,ANDERSON E M. Development and validation of a high-fidelity aero-thermo-elastic analysis capability: AIAA2020-1449 [R]. Reston,US: AIAA,2020.
|
| [34] |
LEE C,BOEDICKER C. Subsonic diffuser design and performance for advanced fighter aircraft: AIAA1985-3073 [R]. Reston,US: AIAA,1985.
|
| [35] |
李君哲,阎超,柯伦,等. 气动热CFD计算的格式效应研究[J]. 北京航空航天大学学报,2003,29(11): 1022-1025. LI Junzhe,YAN Chao,KE Lun,et al. Research on scheme effect of computational fluid dynamics in aerothermal[J]. Journal of Beijing University of Aeronautics and Astronautics,2003,29(11): 1022-1025. (in Chinese doi: 10.3969/j.issn.1001-5965.2003.11.014
LI Junzhe, YAN Chao, KE Lun, et al. Research on scheme effect of computational fluid dynamics in aerothermal[J]. Journal of Beijing University of Aeronautics and Astronautics, 2003, 29(11): 1022-1025. (in Chinese) doi: 10.3969/j.issn.1001-5965.2003.11.014
|
| [36] |
潘沙. 高超声速气动热数值模拟方法及大规模并行计算研究[D]. 长沙: 国防科学技术大学,2010. PAN Sha. Hypersonic aerothermal numerical simulation method and massive parallel computation research[D]. Changsha: National University of Defense Technology,2010. (in Chinese
PAN Sha. Hypersonic aerothermal numerical simulation method and massive parallel computation research[D]. Changsha: National University of Defense Technology, 2010. (in Chinese)
|
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