Статья 11116

Title of the article

INVESTIGATION OF RESIDUAL STRESS INFLUENCE ON GTE BLADES FATIGUE RESISTANCE CONSIDERING FRACTOGRAPHIC CHARACTERISTICS 

Authors

Smyslov Anatoliy Mikhaylovich, Doctor of engineering sciences, professor, sub-department of mechanical engineering technology, Ufa State Aviation Technical University (12 K. Marksa street, Ufa, the Republic of Bashkortostan, Russia), tm@usatu.ru
Smyslova Marina Konstantinovna, Candidate of engineering sciences, associate professor, sub-department of welding production equipment and technology, Ufa State Aviation Technical University (12 K. Marksa street, Ufa, the Republic of Bashkortostan, Russia), tm@usatu.ru
Dubin Aleksey Ivanovich, Candidate of engineering sciences, senior lecturer, sub-department of mechanical engineering technology, Ufa State Aviation Technical University (12 K. Marksa street, Ufa, the Republic of Bashkortostan, Russia), tm@usatu.ru
Sazanov Vyacheslav Petrovich, Candidate of engineering sciences, associate professor, sub-department of strength of materials, Samara State Aerospace University named after academician S. P. Korolyov (National Research University) (34 Moskovskoe highway, Samara, Russia), sazanow@mail.ru
Pavlov Valentin Fedorovich, Doctor of engineering sciences, professor, head of sub-department of strength of materials, Samara State Aerospace University named after academician S. P. Korolyov (National Research University) (34 Moskovskoe highway, Samara, Russia), sopromat@ssau.ru

Index UDK

621.787:539.319

Abstract

Background. The research object is gas-turbine engine’s compressor blades made of the titanium alloy ВТ6 under complex vacuum ion-plasma processing (CVIPP). The research subject is the microstructure and residual stresses of the blades’ surface layer after CVIPP in comparison with the blades made by serial technology. The purpose of the work is to investigate CVIPP’s influence on compressor blades multicyclic fatigue and to explane the causes of an increased endurance limit.
Materials and methods. The authors investigated a microstructure, distribution of residual stresses in the surface layer, as well as multicyclic fatigue resistance of compressor blades by experimental methods.
Results. Application of CVIPP to the compressor blades made of the titanium alloy ВТ6 increases the endurance limit by 10% and ensures its lesser decrease under exploitation in comparison with the serial technology of blades processing.
Conclusions. Application of CVIPP to the blades’ surface ensures a greater level of compressive residual stresses and its higher relaxation strength in comparison with the serial technology that is the cause of an increased compressor blades’ endurance limit. The average integral residual stresses criterion can be used for estimation of CVIPP’s influence on endurance limit increase of the compressor blades made of the titanium alloy ВТ6 with the accuracy sufficient for practice.

Key words

compressor blade, complex vacuum ion-plasma processing, residual stresses, endurance limit

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References

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Дата создания: 01.07.2016 09:15
Дата обновления: 01.07.2016 11:07