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Experimental investigation of an actively controlled mechanical seal.

机译：主动控制机械密封的实验研究。

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This study experimentally investigates an actively controlled mechanical seal for aerospace applications. The seal of interest is a gas seal, which is considerably more compact than previous actively controlled mechanical seals that were developed for industrial use.; In a mechanical seal, the radial convergence of the seal interface has a primary effect on the film thickness. Active control of the film thickness is established by controlling the radial convergence of the seal interface with a piezoelectric actuator.; An actively controlled mechanical seal was initially designed and evaluated using a mathematical model. Based on these results, a seal was fabricated and tested under laboratory conditions. The seal was tested with both helium and air, at rotational speeds up to 3770 rad/sec, and at sealed pressures as high as 1.48 {dollar}times{dollar} 10{dollar}sp6{dollar} Pa. The seal was operated with both manual control and with a closed-loop control system that used either the leakage rate or face temperature as the feedback. The output of the controller was the voltage applied to the piezoelectric actuator.; The seal operated successfully for both short term tests (less than one hour) and for longer term tests (four hours) with a closed-loop control system. The leakage rates were typically 5-15 slm (standard liters per minute), and the face temperatures were generally maintained below 100{dollar}spcirc{dollar}C. When leakage rate was used as the feedback signal, the setpoint leakage rate was typically maintained within 1 slm. However, larger deviations occurred during sudden changes in sealed pressure. When face temperature was used as the feedback signal, the setpoint face temperature was generally maintained within 3{dollar}spcirc{dollar}C, with larger deviations occurring when the sealed pressure changed suddenly.; The experimental results were compared to the predictions from the mathematical model. The model was successful in predicting the trends in leakage rate that occurred as the balance ratio and sealed pressure changed, although the leakage rates were not quantitatively predicted with a high degree of accuracy. This model could be useful in providing valuable design information for future actively controlled mechanical seals.
机译：这项研究实验研究了用于航空航天应用的主动控制机械密封。感兴趣的密封件是气体密封件，它比以前为工业用途开发的主动控制机械密封件更加紧凑。在机械密封中，密封界面的径向收敛对薄膜厚度有主要影响。通过利用压电致动器控制密封界面的径向收敛来建立对膜厚度的主动控制。主动控制的机械密封最初是使用数学模型设计和评估的。基于这些结果，制造了密封件并在实验室条件下进行了测试。在高达3770 rad / sec的转速下，在高达1.48 {dollar}乘以{dollar} 10 {dollar} sp6 {dollar} Pa的密封压力下，用氦气和空气对密封件进行了测试。既可以手动控制也可以使用闭环控制系统，该系统使用泄漏率或工作面温度作为反馈。控制器的输出是施加到压电致动器的电压。在使用闭环控制系统的短期测试（少于一小时）和长期测试（四小时）中，密封件均能成功运行。泄漏速率通常为5-15 slm（每分钟标准升），并且表面温度通常保持在100℃以下。当泄漏率用作反馈信号时，设定值泄漏率通常保持在1 slm以内。但是，在密封压力突然变化期间会出现较大的偏差。当使用面部温度作为反馈信号时，设定面部温度通常保持在3摄氏度以下，当密封压力突然变化时会出现较大的偏差。将实验结果与数学模型的预测结果进行了比较。该模型成功地预测了随着平衡比和密封压力的变化而发生的泄漏率趋势，尽管并没有高度准确地定量预测泄漏率。该模型可用于为将来的主动控制机械密封提供有价值的设计信息。

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