The Development of Fast Response Aerodynamic Probes for Flow Measurements in Turbomachinery
The Development of Fast Response Aerodynamic Probes for Flow Measurements in Turbomachinery
复制标题
用于涡轮机械流量测量的快速响应空气动力探头的开发
DOI：
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发表时间：
1994
期刊：
影响因子：
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通讯作者：
J. Batt
中科院分区：
文献类型：
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作者：
R. Ainsworth;J. L. Allen;J. Batt
新一代瞬态旋转涡轮模拟设备的出现，将发动机的雷诺数和马赫数值与相关的旋转参数同时匹配，以获得尺寸相似性（Dunn et al., 1988; Epstein and Guenette, 1984; Ainsworth et al., 1988），为开发用于研究这些阶段气动流动的改进仪器提供了刺激。过去使用热线和激光风速计进行了许多有用的工作。然而，热线风速计在正确雷诺数所需的高压流动中容易破裂。此外，一些激光技术需要比这些瞬态设备更长的运行时间，并且通常只能获得速度信息，而不能提供损失产量的数据。半导体气动探头的进步正开始满足这一需求。本文描述了二维和三维快速响应气动探头的设计、构造和测试方面的进展，其中半导体压力传感器直接安装在探头表面，使用了以前成功用于转子叶片表面的技术（Ainsworth等人，1991）。这些将用于测量可压缩非定常流场的马赫数和流动方向。在第一部分中，简要回顾了传感器和相关技术，这些技术的发展使快速响应气动探头的灵活设计成为可能。在此之后，描述了用于合适半导体尺度探针的候选几何形状的大规模空气动力学模型测试的广泛程序，并讨论了这些结果。这些针对涡轮代表性平均和非定常流动进行的实验得出的结论，为优化小型半导体探头的设计提供了新的信息，包括探头几何形状、传感器位置和气动性能。详细介绍了一系列楔形和金字塔半导体探头的构造，以及用于校准和测量的程序。在性能的差异进行了讨论，允许实验者选择适当的探针为特定的测量要求。最后，介绍了原型半导体探头在高压涡轮瞬态转子试验中的应用，并与非定常粘性流场的CFD解进行了比较。
The advent of a new generation of transient rotating turbine simulation facilities, where engine values of Reynolds and Mach number are matched simultaneously together with the relevant rotational parameters for dimensional similitude (Dunn et al., 1988 ; Epstein and Guenette, 1984 ; Ainsworth et al., 1988), has provided the stimulus for developing improved instrumentation for investigating the aerodynamic flows in these stages. Much useful work has been conducted in the past using hot-wire and laser anemometers. However, hot-wire anemometers are prone to breakage in the high-pressure flows requiredfor correct Reynolds numbers. Furthermore, some laser techniques require a longer run-time than these transient facilities permit, and generally yield velocity information only, giving no data on loss production. Advances in semiconductor aerodynamic probes are beginning to fulfill this perceived need. This paper describes advances made in the design, construction, and testing of two and three-dimensional fast response aerodynamic probes, where semiconductor pressure sensors are mounted directly on the surface of the probes, using techniques that have previously been successfully used on the surface of rotor blades (Ainsworth et al., 1991). These are to be used to measure Mach number and flow direction in compressible unsteady flow regimes. In the first section, a brief review is made of the sensor and associated technology that has been developed to permit a flexible design of fast response aerodynamic probe. Following this, an extensive program of testing large-scale aerodynamic models of candidate geometries for suitable semiconductor scale probes is described, and the results of these discussed. The conclusions of these experiments, conducted for turbine representative mean and unsteady flows, yielded new information for optimizing the design of the small-scale semiconductor probes, in terms ofprobe geometry, sensor placement, and aerodynamic performance. Details are given ofa range of wedge and pyramid semiconductor probes constructed, and the procedures used in calibrating and making measurements with them. Differences in performance are discussed, allowing the experimenter to choose an appropriate probe for the particular measurement required. Finally, the application of prototype semiconductor probes in a transient rotor experiment at HP turbine representative conditions is described, and the data so obtained are compared with CFD solutions of the unsteady viscous flow-field.