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

Ilmārs Ozoliņš, Ēriks Ozoliņš, Valērija Fedotova

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.

Keywords:
Bending stress; blade profile; shroud shelf; working blade

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References


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DOI: 10.2478/tae-2018-0007

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