Wall temperature calculation on integrated combustion and nozzle in TBCC
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摘要: 基于Navier Stokes(N-S)方程组对包括隔热屏、隔热屏内外流、大气外流在内的涡轮基组合动力(TBCC)发动机燃烧室/喷管进行了一体化的气/热耦合数值模拟,考虑了燃气组分输运、辐射换热等影响,研究了其在某典型飞行状态下TBCC冲压发动机燃烧室/喷管筒体及隔热屏内外壁壁面温度、辐射换热热流及对流换热热流分布.结果表明:燃烧室/喷管筒体与对称面上下交线的壁面温度在轴向距离为0.5~2.6m内变化较小,在轴向距离为2.6~3.1m内急剧增加,在轴向距离为3.1~3.5m内急剧下降.之后,上交线筒体壁面温度沿流向减小,下交线筒体壁面温度先升高后降低.筒体壁面温度最高点在喷管下调节板收缩段,为1577K.隔热屏内壁面辐射热流在370~500kW/m2变化,上下交线处的辐射热流较外壁面的辐射热流约高300kW/m2,辐射热流沿流向先减小后增加.隔热屏外壁面辐射热流在50~200kW/m2范围内分布.
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关键词:
- 涡轮基组合动力(TBCC)燃烧室/喷管 /
- 壁面温度 /
- 气/热耦合 /
- 辐射换热 /
- 热流
Abstract: Based on the Navier Stokes(N-S) equations, the numerical simulation of coupling gas and heat on the integrated computational domain of combustion and nozzle in TBCC(turbine based combined cycle), including the heat shield, internal and external flow of the heat shield and the outer flow field, was carried out, inconsideration of the gas composition and the radiation heat transfer. The wall temperature distribution of the cylinder and heat shield in the integrated computational domain of combustion and nozzle in TBCC under certain flight condition was mainly studied in addition to the radiation heat flux distribution of heat shield. Results showed that the wall temperature along the intersection of the symmetry and cylinder changed slightly within the range of axial distance from 0.5m to 2.6m. The wall temperature rapidly increased within the range of axial distance from 2.6m to 3.1m, and dramatically decreased within the range of axial distance from 3.1m to 3.5m.Then the wall temperature along the upper intersection decreased gradually, while the wall temperature along the lower intersection increased first and then decreased. The highest wall temperature point(1577K) of the cylinder was contraction section of lower adjusting plate of nozzle. The radiation heat flux of inner wall of the heat shield changed from 370kW/m2 to 500kW/m2, the radiation heat flux decreased first and then increased along the flow, the radiation heat flux of the two intersections was more than 300kW/m2 compare with outer wall,the radiation heat flux of outer wall of the heat shield changed from 50kW/m2 to 200kW/m2. -
[1] Marshall A W,Gupta A K,Lewis M J.Critical issues in TBCC modeling[R].AIAA-2004-3827,2004. [2] 陈大光.高超声速飞行与 TBCC方案简介[J].航空发动机,2006,32(3):10-13. CHEN Daguang.Brief introduction of hypersonic flight and TBCC concept[J].Aeroengine,2006,32(3):10-13.(in Chinese) [3] 陈宏,何国强.RBCC和TBCC组合发动机在 RLV上的应用[J].火箭推进,2008,34(3):40-42. CHEN Hong,HE Guoqiang.Application of RBCC and TBCC engines to RLVs[J].Journal of Rocket Propulsion,2008,34(3):40-42.(in Chinese) [4] Jinho L,Ralph W,Buehrle R J.The GENASA RTA hyperburner design and development[R].NASA-TM-213803,2005. [5] Shaw R J,Peddie C L.Overview of the turbine based combined cycle (TBCC) program[R].NASA-CP-212458,2003. [6] Hendrink P,Saint M M.ACES Saengertype T.S.T.O.family with common first stage[R].AIAA-98-3229,1998. [7] Bradford J E,Charania A,Wallace J,et al.Quicksat:a twostage to orbit reusable launch vehicle utilizing air breathing propulsion for responsive space access[R].AIAA2004-5950,2004. [8] Dusa D J.Exhaust nozzle system design considerations for turboramjet propulsion systems[R].International Society for Air Breathing Engines,ISABE 7077,1989. [9] Lam D W.Use of the PARC code to estimate the offdesign transonic performance of an over/under turboramjet nozzle[R].AIAA 95-2616,1995. [10] MO Jianwei,XU Jinglei,ZHANG Liuhuan,et al.The experimental and numerical study of the overunder TBCC exhaust system[R].AIAA-2011-2234,2011. [11] MO Jianwei,XU Jinglei,LI Chao,et al.The design and numerical study of the overunder TBCC exhaust system[R].AIAA-2009-5330,2009. [12] 顾瑞,徐惊雷,赵强,等.不同几何调节位置上的单边膨胀喷管流固耦合计算[J].推进技术,2013,34(3):300-306. GU Rui,XU Jinglei,ZHAO Qiang,et al.Primary analysis of fluidstructure interaction of adjustable single expansion ramp nozzle with different cowl position[J].Journal of Propulsion Technology,2013,34(3):300-306.(in Chinese) [13] 杨承宇,张靖周,单勇.单边膨胀喷管红外辐射换热特性的数值模拟[J].航空学报,2010,31(10):1920-1926. YANG Chengyu,ZHANG Jingzhou,SHAN Yong.Numerical simulation on infrared radiation characteristics of single expansion ramp nozzles[J].Acta Aeronautica et Astronautica Sinica,2010,31(10):1920-1926.(in Chinese) [14] 张少丽,单勇,张勇,等.膨胀边开槽对单边膨胀喷管性能影响的数值研究[J].推进技术,2012,33(3):437-442. ZHANG Shaoli,SHAN Yong,ZHANG Yong,et al.Numerical studies on the performances of the single expansion ramp nozzle with slots on the ramp[J].Journal of Propulsion Technology,2012,33(3):437-442.(in Chinese) [15] 单勇,陈著,尚守堂,等.与飞机融合的单边膨胀喷管排气系统气动和红外辐射换热特征数值计算[J].航空发动机,2014,40(2):1-5. SHAN Yong,CHEN Zhu,SHANG Shoutang,et al.Aerodynamic and infrared radiation characteristics numerical simulation on single expansion ramp nozzle within aircraft[J].Aeroengine,2014,40(2):1-5.(in Chinese) [16] Monta W J.Pitot survey of exhaust flow field of a 2-D scramjet nozzle at Mach 6 with air or freon and argon used for exhaust simulation[R].NASA-TM-4361,1992. [17] Oktay B.Flow analysis and design optimization methods for nozzle afterbody of a hypersonic[R].NASA-CR-4411,1992. [18] 刘友宏,刘宇.隔热屏位置对矢量喷管红外特征的影响[J].航空动力学报,2009,24(7):1438-1442. LIU Youhong,LIU Yu.Heat shield position on infrared characteristics of a vectored nozzle[J].Journal of Aerospace Power,2009,24(7):1438-1442.(in Chinese)
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