基于液氮冷却方式的气动加热表面温度分布数值研究
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摘要
随着红外探测系统和制导武器的迅速发展,有效降低高速飞行器表面红外辐射特性已成为日益关注的红外隐身技术关键问题之一。由于飞行器蒙皮表面的温度分布是影响飞行器红外辐射特性的主要因素,因此开展飞行器蒙皮表面温度分布及其控制技术的研究是十分必要的。本文的研究工作主要包括两个方面:
其一、通过分析控制飞行器蒙皮温度场的传热过程,建立了包括蒙皮外部气动加热、辐射换热与内部对流换热的瞬态耦合传热数学模型。引入壁面气动热流函数,将蒙皮外部气动加热条件转化为浮动的热边界条件,对简化的二维平板模型进行气动加热条件下的温度场模拟计算,获得了不同飞行状况下表面的瞬态温度响应,分析了相关因素的影响。研究结果表明:飞行器在水平加速与降速阶段都存在明显的感应阶段;不同的蒙皮内表面冷却条件对其外表面的温度响应过程有较明显的影响。
其二,以Fluent软件为平台,对液氮狭缝通道沸腾换热和带气膜喷吹的液氮狭缝通道沸腾换热进行数值研究,分析在不同工作条件和冷却需求下的换热特性和冷却效果。
利用混合两相流模型和Lemmon提出的液氮物性表达式,通过编写用户自定义程序(UDFs)实现对液氮物性和气液相间传输项的模拟,从而对一侧表面模拟气动加热热流条件、另一侧表面为绝热条件的二维矩形狭缝通道内的液氮流动换热进行了数值模拟。结果表明,利用液氮狭缝通道换热可以实现气动加热表面的有效冷却;冷却通道沿程换热效果随着质量流率的增大而提高;在单位表面积质量流率一致的情况下,通道长度的增长有利于改善气动加热表面的冷却效果。
对带有单排气膜喷吹的液氮狭缝通道冷却结构的气膜侧绝热冷却效率以及其对机翼前缘表面的整体冷却效果进行了研究,归纳了气膜孔排布位置、吹风比(或主次流质量分配比)、外流马赫数等因素对于该冷却结构冷却效果的影响规律。研究结果表明,该冷却结构对高马赫数飞行条件下的气动加热表面具有较好的冷却效果;适当增大通道冷却结构的液氮入口质量流量和合理布置气膜孔能改善表面的冷却效果。
Suppressing the infrared singles from the aircraft skin has become even more important for the infrared stealthy technology as the development of IR detector system and guided weapons. As the aircraft skin temperature distribution is a key factor affecting the infrared radiation characteristics of aircraft, it is needed to investigate the temperature distribution and control for the aircraft skin. The present paper includes two main aspects:
1. By analyzing the heat transfer process governing the aircraft skin temperature, the physical and mathematical model for the transient heat transfer coupling the aerodynamic heating on the skin and radiative heat transfer and internal convective heat transfer was put forward. The aerodynamic heating condition on aircraft skin was transfered as the floating heat flux thermal boundary by introducing a wall heat flux function and the numerical simulations for a simplified two-dimensional flat plate were made to study the transient temperature response under various flight statuses. It is obtained that the thermal response lags were distinct during the acceleration and deceleration of aircraft, and the inner cooling condition affects the thermal response obviously.
2. The commercial flow solver FLUENT CFD software was utilized to numerically simulate the heat transfer of liquid nitrogen through a two-dimensional narrow rectangular channel and a three-dimensional narrow channel with a row of 30°angling film-cooling holes, respectively.
The mixture multiphase model and expressions of liquid nitrogen properties presented by Lemmon were adopted and the user-defined functions (UDFs) were introduced to simulate the properties of liquid nitrogen and the transfers between gas phase and liquid phase. The heat transfer of liquid nitrogen through a two-dimensional narrow rectangular channel, with one side surface simulating aerodynamic heating flux condition and the other side surface as adiabatic condition was numerically investigated. The results indicat that the liquid nitrogen enhanced heat transfer insides the narrow channel provides an efficient cooling on the surface suffering aerodynamic heating flux. The increase of liquid nitrogen mass-flux leads to heat transfer enhancement and the extending of channel length affects the cooling effectiveness positively with a constant ratio between mass flux and cooling area. The adiabatic film cooling effectiveness and overall cooling effectiveness for the liquid nitrogen cooling narrow channel with a row of film cooling holes were studied. The effects of the film holes arrangement, blowing ratio (or primary to secondary mass flux ratio) and primary flow Mach number on the cooling characteristics were concluded. The results show that the cooling configuration is an efficient cooling mode for the aerodynamic heating skin. The cooling effectiveness would be enhanced with a suitable mass-flux and better film holes arrangement.
其一、通过分析控制飞行器蒙皮温度场的传热过程,建立了包括蒙皮外部气动加热、辐射换热与内部对流换热的瞬态耦合传热数学模型。引入壁面气动热流函数,将蒙皮外部气动加热条件转化为浮动的热边界条件,对简化的二维平板模型进行气动加热条件下的温度场模拟计算,获得了不同飞行状况下表面的瞬态温度响应,分析了相关因素的影响。研究结果表明:飞行器在水平加速与降速阶段都存在明显的感应阶段;不同的蒙皮内表面冷却条件对其外表面的温度响应过程有较明显的影响。
其二,以Fluent软件为平台,对液氮狭缝通道沸腾换热和带气膜喷吹的液氮狭缝通道沸腾换热进行数值研究,分析在不同工作条件和冷却需求下的换热特性和冷却效果。
利用混合两相流模型和Lemmon提出的液氮物性表达式,通过编写用户自定义程序(UDFs)实现对液氮物性和气液相间传输项的模拟,从而对一侧表面模拟气动加热热流条件、另一侧表面为绝热条件的二维矩形狭缝通道内的液氮流动换热进行了数值模拟。结果表明,利用液氮狭缝通道换热可以实现气动加热表面的有效冷却;冷却通道沿程换热效果随着质量流率的增大而提高;在单位表面积质量流率一致的情况下,通道长度的增长有利于改善气动加热表面的冷却效果。
对带有单排气膜喷吹的液氮狭缝通道冷却结构的气膜侧绝热冷却效率以及其对机翼前缘表面的整体冷却效果进行了研究,归纳了气膜孔排布位置、吹风比(或主次流质量分配比)、外流马赫数等因素对于该冷却结构冷却效果的影响规律。研究结果表明,该冷却结构对高马赫数飞行条件下的气动加热表面具有较好的冷却效果;适当增大通道冷却结构的液氮入口质量流量和合理布置气膜孔能改善表面的冷却效果。
Suppressing the infrared singles from the aircraft skin has become even more important for the infrared stealthy technology as the development of IR detector system and guided weapons. As the aircraft skin temperature distribution is a key factor affecting the infrared radiation characteristics of aircraft, it is needed to investigate the temperature distribution and control for the aircraft skin. The present paper includes two main aspects:
1. By analyzing the heat transfer process governing the aircraft skin temperature, the physical and mathematical model for the transient heat transfer coupling the aerodynamic heating on the skin and radiative heat transfer and internal convective heat transfer was put forward. The aerodynamic heating condition on aircraft skin was transfered as the floating heat flux thermal boundary by introducing a wall heat flux function and the numerical simulations for a simplified two-dimensional flat plate were made to study the transient temperature response under various flight statuses. It is obtained that the thermal response lags were distinct during the acceleration and deceleration of aircraft, and the inner cooling condition affects the thermal response obviously.
2. The commercial flow solver FLUENT CFD software was utilized to numerically simulate the heat transfer of liquid nitrogen through a two-dimensional narrow rectangular channel and a three-dimensional narrow channel with a row of 30°angling film-cooling holes, respectively.
The mixture multiphase model and expressions of liquid nitrogen properties presented by Lemmon were adopted and the user-defined functions (UDFs) were introduced to simulate the properties of liquid nitrogen and the transfers between gas phase and liquid phase. The heat transfer of liquid nitrogen through a two-dimensional narrow rectangular channel, with one side surface simulating aerodynamic heating flux condition and the other side surface as adiabatic condition was numerically investigated. The results indicat that the liquid nitrogen enhanced heat transfer insides the narrow channel provides an efficient cooling on the surface suffering aerodynamic heating flux. The increase of liquid nitrogen mass-flux leads to heat transfer enhancement and the extending of channel length affects the cooling effectiveness positively with a constant ratio between mass flux and cooling area. The adiabatic film cooling effectiveness and overall cooling effectiveness for the liquid nitrogen cooling narrow channel with a row of film cooling holes were studied. The effects of the film holes arrangement, blowing ratio (or primary to secondary mass flux ratio) and primary flow Mach number on the cooling characteristics were concluded. The results show that the cooling configuration is an efficient cooling mode for the aerodynamic heating skin. The cooling effectiveness would be enhanced with a suitable mass-flux and better film holes arrangement.
引文
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