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首页> 外文会议>ASME Turbo Expo >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：CFD的使用在压缩机鼓热模型中为转子定子腔产生传热边界条件

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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，进行压缩机鼓和外壳的热机械分析，以预测元件温度和位移，最终用于材料选择，叶片间隙控制和部件提升。热边界条件是从少量标准流场和传热解决方案来源的，导致发动机热电偶测试依赖于在边界条件下提供校准因子，这与来自测试装置的入口流量和腔几何形状的变化未经证实，限制了将测试信息读到的新设计的能力。鉴于压缩机鼓和壳体部件中的热边界条件在很大程度上被复杂的流理物理学驱动，在没有合适的测试信息的情况下，CFD方法可用于提供热机械问题的边界规范，包括所涉及的复杂物理。如果没有复杂的流量区域中的流场解决方案的洞察，边界条件的规格是非常主观的，主要是基于直觉。该研究表明CFD的使用在IP压缩机鼓的前部提供转子定子腔的边界条件。 CFD以防止腔壁的分开部分的一组单元传热壳体，在飞行周期中的关键点处，通过一组单元传热盒。分析提供了转移到热机械模型中的适当表征的热边缘条件（特别是传热系数和绝热壁温度），然后可以通过各种循环进行，而无需进一步的CFD计算。

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