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首页> 外文期刊>Journal of Engineering for Gas Turbines and Power >Heat Transfer in the Core Compressor Under Ice Crystal Icing Conditions
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Heat Transfer in the Core Compressor Under Ice Crystal Icing Conditions

机译：冰晶结冰条件下核心压缩机的传热

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It has been recognized in recent years that high altitude atmospheric ice crystals pose a threat to aircraft engines. Instances of damage, surge, and shutdown have been recorded at altitudes significantly greater than those associated with supercooled water icing. It is believed that solid ice particles can accrete inside the core compressor, although the exact mechanism by which this occurs remains poorly understood. Development of analytical and empirical models of the ice crystal icing phenomenon is necessary for both future engine design and this-generation engine certification. A comprehensive model will require the integration of a number of aerodynamic, thermodynamic, and mechanical components. This paper studies one such component, specifically the thermodynamic and mechanical processes experienced by ice particles impinging on a warm surface. Results are presented from an experimental campaign using a heated and instrumented flat plate. The plate was installed in the Altitude Icing Wind Tunnel (AIWT) at the National Research Council of Canada (NRC). This facility is capable of replicating ice crystal conditions at altitudes up to 9 km and Mach numbers up to 0.55. The heated plate is designed to measure the heat flux from a surface at temperatures representative of the early core compressor, under varying convective and icing heat loads. Heat transfer enhancement was observed to rise approximately linearly with both total water content (TWC) and particle diameter over the ranges tested. A Stokes number greater than unity proved to be a useful parameter in determining whether heat transfer enhancement would occur. A particle energy parameter was used to estimate the likelihood of fragmentation. Results showed that when particles were both ballistic and likely to fragment, heat transfer enhancement was independent of both Mach and Reynolds numbers over the ranges tested.
机译：近年来，已经认识到高海拔大气冰晶对飞机发动机构成威胁。记录到的损坏，喘振和停机情况明显高于与过冷水结冰有关的高度。可以相信，固冰颗粒会积聚在核心压缩机内部，尽管对此的确切机理仍知之甚少。开发冰晶结冰现象的分析模型和经验模型对于将来的发动机设计和这一代发动机认证都是必要的。一个全面的模型将需要集成许多空气动力学，热力学和机械组件。本文研究了一种这样的成分，特别是冰粒撞击在温暖表面上所经历的热力学和机械过程。结果是通过使用加热并装有仪器的平板进行的实验活动得出的。该板安装在加拿大国家研究委员会（NRC）的高度结冰风洞（AIWT）中。该设施能够复制高达9 km的冰晶条件和高达0.55的马赫数。加热板设计用于在变化的对流和结冰热负荷下，在代表早期核心压缩机的温度下测量来自表面的热通量。在测试范围内，传热增强与总水含量（TWC）和粒径均呈线性关系。证明大于1的斯托克斯数是确定传热是否会发生的有用参数。粒子能量参数用于估计碎片的可能性。结果表明，当颗粒都具有弹道性并可能破裂时，在测试范围内，传热增强与马赫数和雷诺数无关。

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