| TBCC燃烧室/喷管一体化壁面温度计算 |
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| 引用本文： | 刘友宏,郜晶晶.TBCC燃烧室/喷管一体化壁面温度计算[J].航空动力学报,2017,32(2):257-267. |
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| 作者姓名： | 刘友宏 郜晶晶 |
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| 作者单位： | 北京航空航天大学 能源与动力工程学院,北京 100091 |
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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 |
| 收稿时间： | 2015/5/18 0:00:00 |
Wall temperature calculation on integrated combustion and nozzle in TBCC |
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| LIU You-hong,GAO Jing-jing.Wall temperature calculation on integrated combustion and nozzle in TBCC[J].Journal of Aerospace Power,2017,32(2):257-267. |
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| Authors: | LIU You-hong GAO Jing-jing |
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| 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. |
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| Keywords: | combustion and nozzle in turbine based combined cycle (TBCC) wall temperature coupling aerodynamic and heat transfer radiation heat transfer heat flux |
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