Topic
Vibration fatigue
About: Vibration fatigue is a research topic. Over the lifetime, 3460 publications have been published within this topic receiving 46297 citations.
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TL;DR: In this paper, a formulated fatigue crack growth model derived from the concept of strain energy density is used to estimate the curve of crack propagation in the specimen and a new explanation of the phenomenon is given.
14 citations
01 Dec 1971
TL;DR: In this paper, the authors investigated the effect of cycle-dependent overloading on the LOCAL RESIDUAL STRESS at notches and found that a cycle-dependent overload could cause cyclcycled individuals to experience increased stress.
Abstract: CONSTANT AMPLITUDE FATIGUE TESTS WITH VARIOUS CONDITIONS OF OVERLOADS WERE CONDUCTED TO UNDERSTAND THE EFFECTS OF LOAD INTERACTION AND SEQUENCE IN NOTCHED COUPONS. THE RESULTS WERE ANALYZED WITH PARTICULAR EMPHASIS ON THE LOCAL RESIDUAL STRESSES AT NOTCHES. FATIGUE LIFE RESULTS FROM THE TESTS HAVING A VARIATION IN THE NUMBER OF CYCLES BETWEEN THE PERIODIC OVERLOADS WHICH REINFORCE THE CONCEPT OF A FADING RESIDUAL STRESS. OTHER FATIGUE LIFE TRENDS COULD BE PREDICTED BY ASSUMING A STABLE RESIDUAL STRESS. CONDITIONS WHICH COULD CAUSE CYCLE-DEPENDENT OVERLOAD RESIDUAL STRESSES ARE DISCUSSED. AN EXPONENTIAL ANALYSIS FORM IS SUGGESTED FOR CALCULATING THE CYCLE-DEPENDENT LOCAL STRESSES FOR APPLICATION TO CUMULATIVE DAMAGE PREDICTIONS. /ASTM/
14 citations
TL;DR: In this paper, the authors studied the fatigue variability of a turbine engine alloy Ti-6Al-4V and used crack propagation to predict the lower tail of the life distribution.
14 citations
TL;DR: In this paper, a detailed design method has been developed that relates the required fatigue life, the mean and alternating applied stresses, and the damage in terms of Kf to the residual stress at the fatigue initiation site required for the targeted HCF performance.
Abstract: High cycle fatigue (HCF) performance of turbine engine components has been known for decades to benefit from compressive surface residual stresses produced by shot peening. Recently laser shocking and low plasticity burnishing (LPB) have been shown to provide spectacular fatigue and damage tolerance improvement by introducing deep or through-thickness compression in fatigue critical areas. However, the lack of a comprehensive design method that defines the depth and magnitude of compression required to achieve a design fatigue life has prevented surface enhancement from being used for more than a safeguard against HCF damage initiation. The present paper describes a design methodology and testing protocol to allow credit to be taken for the beneficial compression introduced by surface enhancement in component design to achieve a required or optimal fatigue performance. A detailed design method has been developed that relates the required fatigue life, the mean and alternating applied stresses, and the damage in terms of Kf to the residual stress at the fatigue initiation site required for the targeted HCF performance. The method is applied to feature specimens designed to simulate the fatigue conditions in the trailing edge of a first stage low pressure Ti-6-4 compressor vane to provide the optimal trailing edge damage tolerance. A novel adaptation of the traditional Haigh diagram to estimate the compressive residual stress magnitude for optimal fatigue performance is introduced. Fatigue results on blade-edge feature samples are compared with analytical predictions provided by the design methodology.
14 citations
TL;DR: In this article, a detailed mathematical modelling of a newly designed fatigue-testing rig, description of the rig, experimental set-up and procedures, and sensor calibrations are presented.
14 citations