Influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor blades
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 st...
| Main Authors: | , |
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| Format: | Article |
| Language: | English |
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Samara National Research University
2019-04-01
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| Series: | Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение |
| Subjects: | |
| Online Access: | https://journals.ssau.ru/index.php/vestnik/article/view/6538 |
| _version_ | 1818067422320525312 |
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| author | M. B. Sazonov L. V. Solovatskaya |
| author_facet | M. B. Sazonov L. V. Solovatskaya |
| author_sort | M. B. Sazonov |
| collection | DOAJ |
| description | 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. |
| first_indexed | 2024-12-10T15:23:26Z |
| format | Article |
| id | doaj.art-69f778bf676843cb9bf58ef68cb06e18 |
| institution | Directory Open Access Journal |
| issn | 2542-0453 2541-7533 |
| language | English |
| last_indexed | 2024-12-10T15:23:26Z |
| publishDate | 2019-04-01 |
| publisher | Samara National Research University |
| record_format | Article |
| series | Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение |
| spelling | doaj.art-69f778bf676843cb9bf58ef68cb06e182022-12-22T01:43:37ZengSamara National Research UniversityВестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение2542-04532541-75332019-04-0118110911710.18287/2541-7533-2019-18-1-109-1176147Influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor bladesM. B. Sazonov0L. V. Solovatskaya1Samara National Research University, Russian FederationSamara National Research University, Russian FederationDifferent 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.https://journals.ssau.ru/index.php/vestnik/article/view/6538Gas turbine enginecompressorbladesfinal strengthening treatmentsurface roughnessresidual stressesedge unrivetingprotection of edgeslimit of endurance |
| spellingShingle | M. B. Sazonov L. V. Solovatskaya Influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor blades Вестник Самарского университета: Аэрокосмическая техника, технологии и машиностроение Gas turbine engine compressor blades final strengthening treatment surface roughness residual stresses edge unriveting protection of edges limit of endurance |
| title | Influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor blades |
| title_full | Influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor blades |
| title_fullStr | Influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor blades |
| title_full_unstemmed | Influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor blades |
| title_short | Influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor blades |
| title_sort | influence of the stressed state of the surface layer on the endurance of gas turbine engine compressor blades |
| topic | Gas turbine engine compressor blades final strengthening treatment surface roughness residual stresses edge unriveting protection of edges limit of endurance |
| url | https://journals.ssau.ru/index.php/vestnik/article/view/6538 |
| work_keys_str_mv | AT mbsazonov influenceofthestressedstateofthesurfacelayerontheenduranceofgasturbineenginecompressorblades AT lvsolovatskaya influenceofthestressedstateofthesurfacelayerontheenduranceofgasturbineenginecompressorblades |