Investigation of the influence of the operation of the cooling system on the temperature of the low-pressure turbine blade

Authors

  • Nikolai Sergeevich Senyushkin Ufa University of Science and Technology (UUST), Russia
  • Victoria Alekseevna Zamuragina Ufa University of Science and Technology (UUST), Russia
  • Irina Ilyinichna Salimova Ufa University of Science and Technology (UUST), Russia

Keywords:

blade, afterburner, cruising, low-pressure turbine, cooling system, gas-dynamic calculation, boundary layer, grid

Abstract

The turbine is a very heat-stressed unit, and the reliability and service life of the turbine depend on properly organized cooling. In this work, the influence of the cooling system on the temperature of the low-pressure turbine blade is investigated. The gas-dynamic and thermal calculation of the blade was performed in the ANSYS CFX system with an assessment of the thermal state. The calculation was performed in three modes: with full afterburner, takeoff and cruising mode. Based on the calculation results, it can be said that the maximum blade temperature for three modes of operation of the engine with impaired cooling changes insignificantly, for the second design mode, the relative temperature increase was 1.4%.

Author Biographies

Nikolai Sergeevich Senyushkin, Ufa University of Science and Technology (UUST), Russia

Deputy Dean of the Faculty of Aircraft Engines, Energy and Transport (UUST), Acting Head of the Department of Aviation Thermal Power Engineering and Thermal Engineering, Candidate of Technical Sciences, Associate Professor.

Victoria Alekseevna Zamuragina, Ufa University of Science and Technology (UUST), Russia

master student of the Department of Aviation Thermal Power Engineering and Thermal Engineering, certified bachelor - thermal power engineer (UGATU, 2016).

Irina Ilyinichna Salimova, Ufa University of Science and Technology (UUST), Russia

graduate (UGATU, 2015).

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Published

2023-05-04

Issue

Vol. 27 No. 1 (2023)

Section

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