...帝国理工大学的Sayma等首先提出了在大直径航空燃气轮机的转子叶尖处应用气控密封（air-riding seal）即气膜密封（gas film seal）的问题，提出了这种密封应有结构柔性和基于纳维- 斯托克斯方程的气弹性分析模型，但未提出具体结构形式。
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gas film face seal 端面气膜密封
gas-liquid film tandem seal 气液膜串联
gas-film spiral groove face seal 气膜螺旋槽密封
The structure, performance and features of a newly developed non-contacting gas film seal were introduced.
介绍了一种新型气膜密封结构、性能特点及其应用。
The paper introduced typical structure of the close clearance seals for blade tip seals in modern aero-turbine and the research progress of gas film seal for gas turbine.
本文介绍航空燃气轮机转子叶尖“紧间隙”密封的典型结构型式现状，转子内流系统应用气膜密封的有关研究进展。
With the increasing of seal face's positive taper, the stiffness of gas film would obviously increase, but the leakage of seal would also increase.
密封端面正锥度的增加能使密封气膜刚度显著提高，但同时也使密封的泄漏量有所增加。
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