DYNAMICS OF ROCKET ENGINE TURBOPUMP TURBINE SEAL CLEARANCE CHANGES


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Abstract

The article considers changes of liquid rocket engine turbopump turbine seal clearance. During operation. significant change in clearance occurs in comparison with the clearance between rotor and stator seal elements during assembly. The current approach does not involve taking into account the effect of turbine seal clearance changing to the unit parameters and characteristics during design. The report presents an approach to the analysis of seal clearance change, depending by turbopump and engine operating mode.

About the authors

A. V. Ivanov

JSC «NPO Energomash named after academician V.P. Glushko»; «Moscow Aviation Institute (National Research University)»

Author for correspondence.
Email: iav308@inbox.ru
Russian Federation, 1, Burdenko street, Khimki, 141001, Russian Federation; 4, Volokolamskoye shosse, Moscow, 125993, Russian Federation

References

  1. Dmitrenko A.I., Ivanov A.V. [About selection and improvement of seals of turbines of turbopump of LRE] In Russian. Trudi NPO Energomash. – 2017. № 34. – pp. 181–198.
  2. Ovsannikov B.V, Borovskyi B.I. [Theory and calculation of liquid rocket engines supply units] In Russian. Mashinostroenie. – 1986. 376 p.
  3. Ivanov A.V. [Analysis of contactless seal type impact on the pump characteristics of a rocket engine turbopump unit while operating mode changing] In Russian. Aerospace MAI Journal. – Vol. 28, № 3, 2021 – pp. 33-43. doi: 10.34759/vst-2021-3-33-45
  4. Ivanov A.V. [The influence of thermal deformations on clearance in a turbine seal of a liquid rocket engine’s turbopump] In Russian. Aviation engines. – 2021. № 4 (13). – pp. 31–38.
  5. Sulinov A.V., Shabliy L.S., Zubanov V.M. [Simulation Methodology of the Screw-Centrifugal Pump for Liquid Hydrogen] Journal of Physics: Conference Series. – 2017. Vol. 803. Issue 1.

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