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High-fidelity rotor gap measurements in a short-duration turbine rig

机译：短时涡轮机设备中的高保真转子间隙测量

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摘要

The distance between the tip of rotating airfoils and the stationary casing, i.e., the tip clearance, is a vital parameter to characterize turbomachinery performance. The larger the tip clearance, the lower the turbine efficiency due to the increased loss associated with the hot jet flowing through the gap without generating work. Following the increasing demands in efficiency, these small clearances must be surveyed to avoid mechanical rubbing. The appropriate design of control systems to adjust these small clearances requires a constant monitoring during the whole engine envelope. This paper describes the complete implementation of a high-frequency capacitive sensor on the shroud of a large transonic turbine stage. The presented system and data analysis procedure allow the accurate measurement of the tip clearance of each rotating airfoil. The measurement system performances are first assessed in a simplified test bench and uncertainty analysis is provided. The technique is demonstrated in an aero-propulsion turbine, tested in a short duration rig. The turbine facility has running times of less than 0.5 s, characterized by temperature and rotor speed transients, which requires parti cular in-situ sensor calibrations. Extensive running tip clearance measurements of the large aero-engine turbine stage validate the system concept and design.
机译：旋转翼型件的尖端与固定壳体之间的距离，即尖端间隙，是表征涡轮机械性能的重要参数。尖端间隙越大，由于与流过间隙而不产生功的热射流相关的损失增加，涡轮效率越低。随着对效率的要求不断提高，必须对这些小间隙进行测量，以避免机械摩擦。调整这些小间隙的控制系统的适当设计需要在整个发动机外壳内进行连续监控。本文介绍了在大型跨音速涡轮机级罩上的高频电容传感器的完整实现。提出的系统和数据分析程序可以精确测量每个旋转翼型的叶尖间隙。首先在简化的测试台中评估测量系统的性能，并提供不确定性分析。这项技术已在短时间内进行测试的航空涡轮机中得到证明。涡轮机设备的运行时间少于0.5 s，其特征在于温度和转子速度的瞬变，这需要特殊的原位传感器校准。大型航空发动机涡轮级的大量运行尖端间隙测量结果验证了系统的概念和设计。

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