Газодинамическое и прочностное совершенствование осевой турбины газотурбинного двигателя вертолёта

E. S. Goriachkin; Горячкин Е. С.; G. M. Popov; Попов Г. М.; V. N. Matveev; Матвеев В. Н.; A. I. Shcherban; Щербань А. И.; I. A. Kudryashov; Кудряшов И. А.; S. A. Melnikov; Мельников С. А.

doi:10.18287/2541-7533-2022-21-1-42-56

Gasdynamic and strength improvement of the axial flow turbine of a helicopter gas turbine engine

Authors: Goriachkin E.S.¹, Popov G.M.¹, Matveev V.N.¹, Shcherban A.I.¹, Kudryashov I.A.¹, Melnikov S.A.¹
Affiliations:
1. Samara National Research University
Issue: Vol 21, No 1 (2022)
Pages: 42-56
Section: MECHANICAL ENGINEERING
URL: https://journals.ssau.ru/vestnik/article/view/10244
DOI: https://doi.org/10.18287/2541-7533-2022-21-1-42-56
ID: 10244

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Abstract

The article presents the results of the development of proposals to increase the safety margin of the blades and the efficiency of a single-stage axial flow turbine compressor of a small-sized turbo-shaft engine being modernized with the use of multidiscipline optimization methods. Analysis of the initial version of the turbine showed that the margin of safety of the working blades is significantly lower than that required by the strength standards. To eliminate the problem encountered the task of blade development was initially solved only according to strength characteristics, without taking into account gas dynamic processes. As a result, the geometry of the working blades that met the strength requirements was obtained. It was used as a starting point for solving the joint task of optimizing the blading, taking into account gas dynamic and deformation processes. As a result of joint optimization, a turbine version meeting the strength standards was obtained, although we had to slightly reduce the efficiency of the turbine by 0,2%.