Development of a Method for Calculating the Working Blade Stress Profile of the Aviation Gas Turbine Engine for Student Training

Authors

  • Ilmārs Ozoliņš Institute of Aeronautics, Faculty of Mechanical Engineering, Transport and Aeronautics, Riga Technical University, Riga, Latvia
  • Ēriks Ozoliņš Institute of Aeronautics, Faculty of Mechanical Engineering, Transport and Aeronautics, Riga Technical University, Riga, Latvia
  • Valērija Fedotova JSC Air Baltic Corporation, Riga, Latvia

DOI:

https://doi.org/10.2478/tae-2018-0007

Keywords:

Bending stress, blade profile, shroud shelf, working blade

Abstract

The paper presents a method of calculation gas turbine engine compressor or low-pressure turbine working blade profile for student training. This method of calculation was prepared for working blades with and without shroud shelves. This method provides a calculation technique to reduce the load on blade root part and the determination of blade profile stress distribution and the comparison before and after reduction of load.

References

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Published

22.03.2021

Issue

Vol. 6 No. 1 (2018): Transport and Aerospace Engineering

Section

Articles