Influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor blades

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Different types of final strengthening treatment of gas turbine engine (GTD) compressor blades are considered. The influence of each type of treatment on the formation of roughness of the surface with favorable microrelief, as well as on the level and depth of distribution of residual compressive stresses in the compressor blade airfoil is analyzed. The causes of blade fatigue failure are described and methods of controlling this kind of failure are presented. The results of testing special specimens made of VT9 titanic alloy are presented to establish the influence of final strengthening treatment modes on the compressor blade resistance to fatigue stress. The results of testing residual stress distribution along the thickness of compressor blade airfoil are presented. A method of improving dynamic strengthening of specimens due to the protection of compressor blade edges is discussed. The results of semi-graphical analysis of the stressed state of low-pressure and medium-pressure compressor blades made of VT9 alloy are presented. They take into account residual stresses, as well as operating load stresses in the process of operation. We show that it is possible to increase the limit of the blade endurance due to the optimization of residual stress diagrams by improving the final strengthening technology with the use of dust blasting.

About the authors

M. B. Sazonov

Samara National Research University

Author for correspondence.

Candidate of Science (Engineering)
Associate Professor of the Department of Engine Production Technology

Russian Federation

L. V. Solovatskaya

Samara National Research University


Senior Lecturer, Department of Engine Production Technology

Russian Federation


  1. Mitryaev K.F., Krivenko M.P., Sazonov M.B. Vliyanie uprochnyayushchey obrabotki mikrosharikami na ustalostnuyu prochnost' obraztsov iz splava VT9. Sbornik nauchnykh trudov «Vysokoeffektivnye metody obrabotki rezaniem zharoprochnykh i titanovykh splavov». Kuybyshev: Kuybyshev Aviation Institute Publ., 1982. P. 54-59. (In Russ.)
  2. Yelenevsky D.S., Solyannikov V.A. Prediction of turbomachinery parts service life basing upon simulation of loading operating conditions. Izvestiya Samarskogo Nauchnogo Tsentra RAN. 2001. V. 3, no. 2. P. 227-231. (In Russ.)
  3. Davydova I.S. Materialovedenie: ucheb. posobie [Materials Science]. Moscow: RIOR Publ., 2006. 240 p.
  4. Mitryaev K.F., Sazonov M.B., Krivenko M.P. Vliyanie uprochnyayushchey obrabotki mikrosharikami na naklep i ostatochnye napryazheniya titanovykh splavov. Sbornik nauchnykh trudov «Optimizatsiya protsessov rezaniya zharo- i osoboprochnykh materialov». Ufa: Ufa Aviation Institute Publ., 1982. P. 161-167. (In Russ.)
  5. Birger I.A. Ostatochnye napryageniya [Residual stresses]. Moscow: Mashgiz Publ., 1963. 232 p.

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