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

Ilmārs Ozoliņš | Zendy; Ēriks Ozoliņš | Zendy; Valērija Fedotova | Zendy

Open Access

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

Author(s) -

Ilmārs Ozoliņš,

Ēriks Ozoliņš,

Valērija Fedotova

Publication year - 2018

Publication title -

transport and aerospace engineering

Language(s) - English

Resource type - Journals

eISSN - 2255-9876

pISSN - 2255-968X

DOI - 10.2478/tae-2018-0007

Subject(s) - shroud , gas turbines , blade (archaeology) , gas compressor , engineering , aero engine , structural engineering , marine engineering , mechanical engineering , stress (linguistics) , turbine , turbine blade , philosophy , linguistics

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.

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