Abstract
This publication presents an assessment of the influence of a surface treatment such as shot-peening on the fatigue life of a compressor blade exposed to resonant vibrations. As part of the work, a geometric model of the blade was developed, and a numerical modal and fatigue analysis were performed. The fatigue analysis was based on the Manson–Coffin–Basquin and Ramberg–Osgood models. Additionally, the location of the highest equivalent stresses was established. Based on the results of the strength analysis, two points were identified where a fatigue crack may potentially occur. As part of the work, the influence of different values of residual stresses on the results of the fatigue life was determined. The obtained results were compared to the literature values of fatigue life for this blade. A secondary objective of the study was to determine the size of the grains at various points of the blade, as well as the thickness of the layer plasticized as a result of peening. The relationship between the location of the highest values of the equivalent stresses and the thickness of the plasticized layer was determined. An explanation of the effect of shot-peening on the increase in the fatigue life of the blade was proposed.
Highlights
Compressor blades are often called the critical elements of the turbine aircraft engine.This statement is connected to the blade geometry, work conditions, and potential failures
In his work [17], observed that in the case of brittle steel (SAE 9245), the increase in fatigue life was equal to 30% when the residual stress was equal to −480 MPa and the depth of the plasticized layer was equal to 33 μm
The main goal of the present paper is to show the impact of shot-peening on the fatigue life of the compressor blade, under controlled geometry with a notch created by machining, subjected to resonance vibrations
Summary
Compressor blades are often called the critical elements of the turbine aircraft engine. Chengfang [11] observed that, in the case of a titanium alloy (super alloys) with residual stress equal to −750 MPa, the specimens achieved a 67 times higher fatigue life. Gao [12] showed that after shot-peening up to a residual stress level of −350 MPa, the specimens achieved a five-fold increase in fatigue life. In his work [17], observed that in the case of brittle steel (SAE 9245), the increase in fatigue life was equal to 30% when the residual stress was equal to −480 MPa and the depth of the plasticized layer was equal to 33 μm. The main goal of the present paper is to show the impact of shot-peening on the fatigue life of the compressor blade, under controlled geometry with a notch created by machining, subjected to resonance vibrations. The obtained results are of great importance for the safety of the air transport
Sign-in/Register to view highlights & summary Sign-in/Register to access full text options 
Talk to us
Join us for a 30 min session where you can share your feedback and ask us any queries you have
Schedule a call
