Integrated Combustor Turbine Design for Improved Aerothermal Performance: Effect of Dilution Air Control
Integrated Combustor Turbine Design for Improved Aerothermal Performance: Effect of Dilution Air Control
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DOI：
10.1115/1.4006671
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发表时间：
2012-09
影响因子：
1.5
通讯作者：
A. Basol;R. Kai;A. Kalfas;R. Abhari
中科院分区：
文献类型：
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作者：
A. Basol;R. Kai;A. Kalfas;R. Abhari
研究了燃烧室掺混空气控制对非轴对称端壁轴流式涡轮机热负荷分布的影响。端壁轮廓是新型发动机中更常见的设计特征，因为它可以有效减少二次流及其相关损失。在目前的工作中，稀释空气控制的效果是通过使用两种不同的周向不均匀的热斑形状进行检查，这两种情况下，在其展向的程度不同的定子的两侧，因此，代表不同的稀释空气控制的方法。该数值研究详细说明了这两种不同的稀释空气控制策略对转子叶片热负荷分布的影响。入口边界条件模拟了在ETH苏黎世的轴向研究涡轮机设施丽莎中进行的实验。定子内部热斑展向迁移模式的周向不均匀性被观察到，发现端壁仿形的效果可以减轻。由于观察到的定子内部的展向迁移模式，两种热斑情况导致转子叶片上的热负荷分布有很大不同，这强调了综合燃烧室涡轮机方法的重要性。最后，为了实现真实的燃烧室中的模拟热斑形状，讨论了衬里上的稀释空气控制的含义。
The effect of dilution air control in a combustor on the heat load distribution of an axial turbine with nonaxisymmetric endwall profiling is examined. Endwall profiling is a more common design feature in new engine types, due to its effectiveness in reducing secondary flows and their associated losses. In the present work, the effect of dilution air control is examined by using two different circumferentially nonuniform hot-streak shapes; the two cases differ in their spanwise extents either side of the stator and, therefore, represent different approaches for dilution air control. This numerical study details the impact of these two different strategies for dilution air control on the rotor blade heat load distribution. The inlet boundary conditions simulate the experiment that is conducted in the axial research turbine facility LISA at ETH Zurich. A circumferential nonuniformity in the spanwise migration pattern of the hot streak inside the stator is observed that is found to be alleviated by the effect of the endwall profiling. Due to the observed spanwise migration pattern inside the stator the two hot-streak cases result in considerably different heat load distributions on the rotor blade, emphasizing the importance of the integrated combustor turbine approach. Finally, the implications for dilution air control on the liner are discussed for the realization of the simulated hot-streak shapes in real combustors.