Abstract
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.
Highlights
Современные газотурбинные двигатели (ГТД) должны обладать высокой надёжностью и долговечностью
Возможностью увеличения выносливости лопаток компрессора является увеличение уровня напряжений сжатия у поверхности до максимального значения
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
Summary
Современные газотурбинные двигатели (ГТД) должны обладать высокой надёжностью и долговечностью. Для увеличения надёжности и долговечности лопаток компрессора необходимо в поверхностном слое создать остаточные напряжения сжатия с оптимальным уровнем и глубиной, а также благоприятный рельеф поверхности. В зависимости от материала лопаток компрессора при таких видах упрочняющеотделочной обработки можно получить шероховатость Ra 0,4 – 0,08 мкм и сжимающие остаточные напряжения до 400 – 600 МПа с максимальными значениями, которые достигаются на глубине 40 – 60 мкм [1; 2]. Остаточные напряжения у поверхности снижаются до 100 – 400 МПа
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