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INVESTIGATION OF THE FLOW FIELD IN A HP TURBINE STAGE FOR TWO STATOR-ROTOR AXIAL GAPS: PART Ⅰ - 3D TIME-AVERAGED FLOW FIELD

机译:两个定子转子轴向间隙中HP涡轮机阶段流场的研究:第Ⅰ部分 - 3D时间平均流场

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An extensive experimental analysis on the subject of unsteady flow field in high pressure turbine stages was carried out at the Laboratorio di Fluidodinamica delle Macchine (LFM) of Politecnico di Milano. The research stage represents a typical modern HP gas turbine stage designed by means of 3D techniques, characterised by a leaned stator and a bowed rotor and operating in high subsonic regime. The first part of the program concerns the analysis of the steady flow field in the stator-rotor axial gap by means of a conventional five-hole probe and a temperature sensor. Measurements were carried out on eight planes located at different axial positions allowing the complete definition of steady flow field both in absolute and relative frame of reference. The evolution of the main flow structures, such as secondary flows and vane wakes, downstream of the stator are here presented and discussed in order to evidence the stator aerodynamic performance and, in particular, the different flow field approaching the rotor blade row for the two axial gaps. This results set will support the discussion of the unsteady stator-rotor effects presented in paper Part Ⅱ. Furthermore, 3D time-averaged measurements downstream of the rotor were carried out at one axial distance and for two stator-rotor axial gaps. The position of the probe with respect to the stator blades is changed by means of rotating the stator in circumferential direction, in order to describe possible effects of the non-uniformity of the stator exit flow field downstream of the stage. Both flow fields, measured for the nominal and for a very large stator-rotor axial gap, are discussed and results show the persistence of some stator flow structures downstream of the rotor, in particular for the minimum axial gap. Eventually the flow fields are compared to evidence the effect of the stator-rotor axial gap on the stage performance from a time-averaged point of view.
机译:对高压涡轮机阶段的非稳态流场主体进行了广泛的实验分析,在PoliteCnico di Milano的Laboratorio di Fluidinamica delle Macchine(LFM)处进行。研究阶段代表借助于3D技术设计的典型的现代HP燃气轮机级,其特征在于倾斜的定子和弓转子,并在高亚音速状态下操作。该程序的第一部分借助于传统的五孔探针和温度传感器对定子转子轴向间隙中的稳态流场的分析。在位于不同轴向位置的八个平面上进行测量,允许在绝对和相对参考框架中完全定义稳态流动。这里呈现并讨论了定子下游的主流结构的演变,例如二次流动和叶片唤醒,以证明定子空气动力学性能,特别是接近转子叶片的不同流场轴向隙。该结果设定将支持讨论纸张部分Ⅱ中所示的不稳定定子转子效应。此外,在转子下游的3D时间平均测量在一个轴向距离和两个定子转子轴向间隙处进行。探针相对于定子叶片的位置通过在圆周方向上旋转定子而改变,以便描述阶段下游的定子出口流场的不均匀性的可能效果。讨论了标称和非常大的定子转子轴向间隙的两个流场,并且结果示出了转子下游的一些定子流动结构的持久性,特别是对于最小轴向间隙。最终,将流场与证据进行比较,以证明定子转子轴向间隙对阶段性能的效果从时间平均的观点来看。

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