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首页> 外文会议>ASME(American Society of Mechanical Engineers) Turbo Expo vol.4 pt.B; 20070514-17; Montreal(CA) >THE USE OF CFD TO GENERATE HEAT TRANSFER BOUNDARY CONDITIONS FOR A ROTOR-STATOR CAVITY IN A COMPRESSOR DRUM THERMAL MODEL
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THE USE OF CFD TO GENERATE HEAT TRANSFER BOUNDARY CONDITIONS FOR A ROTOR-STATOR CAVITY IN A COMPRESSOR DRUM THERMAL MODEL

机译：压缩机转鼓热模型中使用CFD生成转子静腔的传热边界条件

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摘要

In an engine design process, thermo-mechanical analyses of compressor drums and casings are undertaken, to predict component temperatures and displacements, which are ultimately used for material selection, blade clearance control and lifing of components. The thermal boundary conditions are sourced from a small number of standard flow field and heat transfer solutions, leading to a reliance on engine thermocouple tests to provide calibration factors on the boundary conditions, which with changes in inlet flows and cavity geometry from the tested arrangements are unproven, limiting the ability to read-across the test information into new designs. Given that the thermal boundary conditions in compressor drum and casing components are largely driven by complex flow physics, in the absence of suitable test information, CFD methods can be used to provide boundary specification of the thermo-mechanical problem, incorporating the complex physics involved. Without the insight of the flow field solution in complex flow regions, specification of the boundary conditions is rather subjective and mostly based on intuition. This study shows the use of CFD to provide the boundary conditions for the rotor-stator cavity at the front of an IP compressor drum. The CFD is run adiabatically and through a set of unit heat transfer cases on separate sections of the cavity wall, at key points in the flight cycle. The analyses provide appropriately characterized thermal boundary conditions (specifically heat transfer coefficients and adiabatic wall temperatures) that are transferred into the thermo-mechanical model, which can then be run through a wide range of cycles without the need for further CFD calculations.
机译：在发动机设计过程中，对压缩机鼓轮和壳体进行了热机械分析，以预测部件的温度和位移，这些温度和位移最终用于材料选择，叶片间隙控制和部件起吊。热边界条件来自少量的标准流场和传热解决方案，导致依赖于发动机热电偶测试来提供边界条件的校准因子，随着条件的变化，进气道流量和模腔几何形状的变化都取决于测试条件。未经验证，限制了将测试信息读取到新设计中的能力。鉴于压缩机鼓和机壳部件中的热边界条件在很大程度上受复杂的流动物理学驱动，在没有合适的测试信息的情况下，CFD方法可结合所涉及的复杂物理学用于提供热力学问题的边界规范。如果不了解复杂流动区域中的流场解决方案，则边界条件的指定是相当主观的，并且主要基于直觉。这项研究表明，使用CFD为IP压缩机鼓前部的转子-定子腔提供边界条件。 CFD绝热运行，并在飞行周期中的关键时刻通过位于腔壁各个部分上的一组单元传热箱运行。这些分析提供了适当表征的热边界条件（特别是传热系数和绝热壁温），这些条件已转换为热机械模型，然后可以在宽范围的循环中运行，而无需进行进一步的CFD计算。

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