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Development of Damping Support for a Turbine Pump Assembly of a Cryogenic Fuel Aviation Gas Turbine Engine

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Abstract

Theoretical studies and design studies have been conducted to demonstrate the possibility of using a long hydrodynamic damper in the supports of a hydrogen pump rotor was shown. The complex problem of rotor dynamics and design synthesis of a hydrodynamic damper for a turbopump assembly (TPA) was solved. The geometric parameters of the hydrodynamic damper are determined that ensure the necessary damping level, d = 3 × 103 N s/m. It is shown that at such a damping level, the amplitude of rotor oscillations does not exceed the value of clearances in supports and on blade shoulders.

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Authors and Affiliations

  1. Samara National Research University, 443086, Samara, Russia

    V. B. Balyakin

  2. Moscow Aviation Institute (National Research University), 125993, Moscow, Russia

    Yu. A. Ravikovich

Authors
  1. V. B. Balyakin
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  2. Yu. A. Ravikovich
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Correspondence to V. B. Balyakin.

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Balyakin, V.B., Ravikovich, Y.A. Development of Damping Support for a Turbine Pump Assembly of a Cryogenic Fuel Aviation Gas Turbine Engine. J. Frict. Wear 41, 273–276 (2020). https://doi.org/10.3103/S1068366620030034

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  • DOI: https://doi.org/10.3103/S1068366620030034

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