飞行器鼻锥凹腔-发散组合冷却数值模拟

doi:10.7527/S1000-6893.2020.23937

先进空间运输系统气动设计专栏

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飞行器鼻锥凹腔-发散组合冷却数值模拟

栾芸, 贺菲, 王建华

中国科学技术大学热科学和能源工程系中国科学院材料力学行为和设计重点实验室, 合肥 230026

收稿日期:2020-03-05 修回日期:2020-04-17 发布日期:2020-05-11
通讯作者: 贺菲 E-mail:hefeihe@ustc.edu.cn
基金资助:
国家自然科学基金（51806206）

Transpiration cooling of nose-cone with forward-facing cavity: Numerical simulation

LUAN Yun, HE Fei, WANG Jianhua

CAS Key Laboratory of Mechanical Behavior and Design of Materials, Department of Thermal Science and Energy Engineering, University of Science and Technology of China, Hefei 230026, China

Received:2020-03-05 Revised:2020-04-17 Published:2020-05-11
Supported by:
National Natural Science Foundation of China (51806206)

摘要/Abstract

摘要： 尖锐鼻锥冷却方案是可复用式航天飞行器研究领域一个十分重要的课题。传统发散冷却虽然可以有效降低鼻锥结构温度，但是由于驻点外极高的热流、压力，会出现驻点冷却效果差的问题。迎风凹腔结构是一种针对鼻锥驻点区域的减阻防热方案，尖锐唇口的分流作用可以使附近压力、热流降低。因此，提出一种新型冷却结构——凹腔-发散组合冷却，利用迎风凹腔结构对驻点的强化冷却解决发散冷却中驻点难以冷却的问题。以楔形鼻锥为物理模型，对发散冷却、迎风凹腔结构和凹腔-发散冷却3种冷却结构进行数值模拟，并和无冷却的纯鼻锥结构进行对比。结果表明，与传统发散冷却相比，使用凹腔-发散组合冷却可以使结构温度峰值下降16.8%；与没有冷却的纯鼻锥模型相比，鼻锥头部圆弧段表面平均温度降幅可达64%，证实了这种新型冷却结构的可行性和高效性。

关键词: 鼻锥, 热防护, 发散冷却, 迎风凹腔, 凹腔-发散组合冷却

Abstract: The thermal protection system of sharp nose-cones is an important subject in the investigation of reusable spacecraft. Transpiration cooling, with an ability to effectively reduce the temperature of the nose-cone, has been widely recognized as a promising thermal protection approach. However, the cooling effect at the stagnation point remains poor due to the extremely high heat flux and pressure there. The nose-cone with forward-facing cavity is a drag and heat reduction structure specifically designed for the stagnation region. It can reduce the heat flux and pressure there with the shutting effect of the sharp lip. Therefore, a new combined cooling structure is proposed in this paper: transpiration cooling with forward-facing cavity. It utilizes the cooling enhancement effect of the forward-facing cavity to solve the problem of low cooling efficiency at the stagnation region. Using a wedge-shaped nose cone as the physical model, the cooling performance of three structures, i.e., transpiration cooling, forward-facing cavity and transpiration cooling with the cavity, is studied and compared. The simulation results indicate that, using the new combined cooling structure, the maximum temperature of the nose-cone can be reduced by 16.8% compared with that of the traditional transpiration cooling, and the average circular surface temperature can drop by 64% compared with that on the pure nose-cone, confirming the feasibility and high efficiency of the new cooling structure.

Key words: nose-cones, thermal protection systems, transpiration cooling, forward-facing cavity, transpiration cooling with cavity

中图分类号:

V221.3

栾芸, 贺菲, 王建华. 飞行器鼻锥凹腔-发散组合冷却数值模拟[J]. 航空学报, 2021, 42(2): 623937-623937.

LUAN Yun, HE Fei, WANG Jianhua. Transpiration cooling of nose-cone with forward-facing cavity: Numerical simulation[J]. ACTA AERONAUTICAET ASTRONAUTICA SINICA, 2021, 42(2): 623937-623937.

参考文献

[1] DING F, LIU J, SHEN C B, et al. An overview of waverider design concept in airframe/inlet integration methodology for air-breathing hypersonic vehicles[J]. Acta Astronautica, 2018, 152:639-656.
[2] VOLAND R T, HUEBNER L D, MCCLINTON C R. X-43A hypersonic vehicle technology development[J]. Acta Astronautica, 2006, 59:181-191.
[3] HANK J, MURPHY J, MUTZMAN R. The X-51A scramjet engine flight demonstration program[C]//15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston:AIAA, 2008.
[4] WALKER S, MING T, MORRIS S, et al. Falcon HTV-3X-A reusable hypersonic test bed[C]//15th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston:AIAA, 2008.
[5] EGGERS T, SILVESTER T, PAULL A, et al. Aerodynamic design of hypersonic re-entry flight HIFiRE 7[C]//16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference. Reston:AIAA, 2009.
[6] KELLY H, BLOSSER M L. Active cooling from the sixties to NASP[J]. NASA Sti/recon Technical Report N, 1992,94:189-249.
[7] GLASS D. Ceramic matrix composite (CMC) thermal protection systems (TPS) and hot structures for hypersonic vehicles[C]//5th AIAA International Space Planes and Hypersonic Systems and Technologies Conference. Reston:AIAA, 2008.
[8] ECKERT E R G, LIVINGOOD N B. Comparison of effectiveness of convection-, transpiration-, and film-cooling methods with air as coolant:Tech. Rep. 1182[R].Cleveland:NACA Lewis Flight Propulsion Laboratory, 1954.
[9] LAGANELLI A. A comparison between film cooling and transpiration cooling systems in high speed flow[C]//8th Aerospace Sciences Meeting,1970.
[10] WANG J H, MESSNER J, STETTER H. An experimental investigation on transpiration cooling Part Ⅱ:Comparison of cooling methods and media[J]. International Journal of Rotating Machinery, 2004, 10:355-363.
[11] LANGENER T, VON WOLFERSDORF J, SELZER M, et al. Experimental investigations of transpiration cooling applied to C/C material[J]. International Journal of Thermal Sciences, 2012, 54:70-81.
[12] LIU Y Q, JIANG P X, JIN S S, et al. Transpiration cooling of a nose cone by various foreign gases[J]. International Journal of Heat & Mass Transfer, 2010, 53:5364-5372.
[13] DITTERT C, SELZER M, BOHRK H. Flowfield and pressure decay analysis of porous cones[J]. AIAA Journal, 2017, 55(3):874-882.
[14] DING R, WANG J, HE F, et al. Numerical investigation on the performances of porous matrix with transpiration and film cooling[J]. Applied Thermal Engineering, 2019,146:422-431.
[15] SU H, WANG J H, HE F, et al., Numerical investigation on transpiration cooling with coolant phase change under hypersonic conditions[J]. International Journal of Heat and Mass Transfer, 2019,129:480-490.
[16] SHEN L, WANG J H. Numerical investigation on the optimization of local transpiration cooling effectiveness[J]. Applied Thermal Engineering, 2017,127:58-69.
[17] WU N, WANG J, HE F, et al. Optimization transpiration cooling of nose cone with non-uniform permeability[J]. International Journal of Heat and Mass Transfer, 2018,127:882-891.
[18] ZHAO L, WANG J, MA J, et al. An experimental investigation on transpiration cooling under supersonic condition using a nose cone model[J]. International Journal of Thermal Sciences, 2014, 84:207-213.
[19] GAN H, ZHU Y, LIAO Z, et al. Experimental study on combined cooling method for porous struts in supersonic flow[J]. Journal of Heat Transfer, 2018,140:022201.
[20] JIANG P X, GAN H, ZHU Y, et al., Experimental investigation of combined transpiration and film cooling for sintered metal porous struts[J]. International Journal of Heat and Mass Transfer, 2017, 108:232-243.
[21] SHEN B, YIN L, LIU H, et al. Thermal protection characteristics for a combinational opposing jet and platelet transpiration cooling nose-tip[J]. Acta Astronautica, 2019, 155:143-152.
[22] SHEN B, LIU W. Insulating and absorbing heat of transpiration in a combinational opposing jet and platelet transpiration blunt body for hypersonic vehicle[J]. International Journal of Heat and Mass Transfer, 2019, 138:314-325.
[23] ENGBLOM W A, GOLDSTEIN D B, LADOON D, et al. Fluid dynamics of hypersonic forward-facing cavity flow[J]. Journal of Spacecraft & Rockets, 1997, 34:437-444.
[24] SILTON S I, GOLDSTEIN D B. Optimization of an axial nose-tip cavity for delaying ablation onset in hypersonic flow[C]//41st Aerospace Sciences Meeting and Exhibit,2003.
[25] SELVARAJ S, GOPALAN J, REDDY K P J. Investigation of missile-shaped body with forward-facing cavity at Mach 8[J]. Journal of Spacecraft & Rockets, 2009, 46:577-591.
[26] SUN X, HUANG W, OU M, et al. A survey on numerical simulations of drag and heat reduction mechanism in supersonic/hypersonic flows[J]. Chinese Journal of Aeronautics, 2019, 32(1):5-18.
[27] KARIMI M S, OBOODI M J. Investigation and recent developments in aerodynamic heating and drag reduction for hypersonic flows[J]. Heat and Mass Transfer, 2019, 55:547-569.
[28] SUDARSHAN B, DEEP S, JAYARAM V, et al., Experimental study of forward-facing cavity with energy deposition in hypersonic flow conditions[J]. Physics of Fluids, 2019, 31:106105.
[29] LU H, LIU W. Aerodynamic investigation of hypersonic vehicle with forward-facing cavity[C]//International Conference on Mechanical Engineering and Materials Science, 2011.
[30] YUCEIL K, DOLLING D. IR imaging an dshock visualization of flow over a blunt body with a nose cavity[C]//34th Aerospace Sciences Meeting and Exhibit,1996.

E-mail：hkxb@buaa.edu.cn

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飞行器鼻锥凹腔-发散组合冷却数值模拟

Transpiration cooling of nose-cone with forward-facing cavity: Numerical simulation

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