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

Cited-By

1. Turbine Blade of Gas Turbine Engine Additional Unloading by Changing the Layout of the Gravity Centre of the Shroud Shelf
Ēriks Ozoliņš, Ilmārs Ozoliņš, Līga Ramāna
Transport and Aerospace Engineering  vol: 7  issue: 1  first page: 14  year: 2019  
doi: 10.2478/tae-2019-0002

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Copyright (c) 2018 Ilmārs Ozoliņš, Ēriks Ozoliņš, Valērija Fedotova

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