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首页> 外文会议>Conference on Verification of Design Methods by Test and Analysis 23-24 November 1998 London, UK >An Evalaution of the Performance of a Modern Shroudless HP Turbine Using Unsteady CFD
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An Evalaution of the Performance of a Modern Shroudless HP Turbine Using Unsteady CFD

机译：基于不稳定CFD的现代无罩HP涡轮机性能评估

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This paper presents a CFD analysis of the unsteady aerodynamics of an HP turbine, and compares the results with experimental data acquired on a transient turbine test facility. The 2D code UNSFLO and the 3D code Un-NEWT are shown to agree well with the measured mid span unsteady pressures. Use of these solutions to interpret the measured data indicates that the rotor pressure surface is strongly influenced by the NGV potential flow field, while the suction surface shows evidence of a wake shock/interaction. Loss generation within the stage is shown to be concentrated at the endwalls, with the rotor tip leakage flow being a major contributor. The Un-NEWT solution was modified to include a hot streak at stage inlet, representative of the exit temperature profile of a mdoern military combustor. Hot/cold fluid segregation is shown to occur in the rotor passage. Hot fluid migrates to the pressure surface, and is drawn over the tip of the unshrouded rotor, giving the potential for locally high heat transfer.
机译：本文介绍了高压涡轮机非定常空气动力学的CFD分析，并将结果与​​在瞬态涡轮机测试设备上获得的实验数据进行了比较。显示的2D代码UNSFLO和3D代码Un-NEWT与测得的中跨非稳态压力非常吻合。使用这些解决方案来解释测得的数据表明，转子压力表面受到NGV势流场的强烈影响，而吸力表面则表现出唤醒冲击/相互作用的迹象。如图所示，该级内的损耗集中在端壁处，其中转子头的泄漏流是主要的原因。 Un-NEWT解决方案经过修改，在阶段入口处包括热条纹，代表了现代军事燃烧器的出口温度曲线。已显示在转子通道中发生热/冷流体偏析。热流体迁移到压力表面，并被吸入未覆盖转子的尖端，从而可能产生局部高热量传递。

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