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

Transport and Aerospace Engineering 2018
Ilmārs Ozoliņš, Ēriks Ozoliņš, Valērija Fedotova

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
DOI
10.2478/tae-2018-0007

Ozoliņš, I., Ozoliņš, Ē., Fedotova, V. Development of a Method for Calculating the Working Blade Stress Profile of the Aviation Gas Turbine Engine for Student Training. Transport and Aerospace Engineering, 2018, Vol.6, pp.55-66. ISSN 2255-968X. e-ISSN 2255-9876. Available from: doi:10.2478/tae-2018-0007

Publication language
English (en)