Gas turbine engine in-flight diagnostics using 3D vibration spectra

2018 Ural Symposium on Biomedical Engineering, Radioelectronics and Information Technology (USBEREIT) Pub Date : 2018-05-07 DOI:10.1109/USBEREIT.2018.8384603

F. Mirsaitov, K. Ignatkov

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引用次数: 14

Abstract

The sensor is designed for in-flight aeroengine turbine blade vibration monitoring. The sensor operation and construction are similar to liquid rocket engine flame parameters sensors. Three dimensional (3D) electromagnetic (EM) field structure and its fluctuation depending on regular, vibrating and damaged blade travel states have been researched in quasi-static approximation. Probing frequency varied from 4 to 40 GHz, and range from 28 to 37 GHz was accepted as preferable. Field structure impact on antenna current flow, its vector admittance, and reflectivity have been found out. Furthermore, computational EM simulation by FEKO software tool was applied. Then autodyne frequency response form was found out. During regular turbine rotation radio frequency (RF) spectrum is sampled. Sampling rate F is a multiplication of rotation frequency (hundreds of hertz) to number of blades (approximately one hundred hertz). Estimated samples amplitudes are stipulated by response form and modulated by vibration process.

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基于三维振动谱的燃气涡轮发动机飞行诊断

该传感器主要用于航空发动机涡轮叶片的飞行振动监测。该传感器的工作原理和结构类似于液体火箭发动机火焰参数传感器。在准静态近似下研究了叶片正常、振动和损伤行程状态下的三维电磁场结构及其波动。探测频率范围从4到40 GHz，范围从28到37 GHz被接受为较好。找出了场结构对天线电流、矢量导纳和反射率的影响。利用FEKO软件进行了计算仿真。找出了自激频率响应形式。在水轮机正常旋转过程中，对射频频谱进行采样。采样率F是旋转频率(数百赫兹)与叶片数量(大约100赫兹)的乘积。估计的样本幅值由响应形式规定，并由振动过程调制。

本文章由计算机程序翻译，如有差异，请以英文原文为准。

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2018 Ural Symposium on Biomedical Engineering, Radioelectronics and Information Technology (USBEREIT)

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