Open AccessInfluence of aircraft engine compressor blades leading edge damage on their fatigue strength
Author(s) -
W. Obrocki,
A. Setkowicz,
M. Masłyk,
J. Sieniawski
Publication year - 2018
Publication title -
mechanik
Language(s) - English
Resource type - Journals
ISSN - 0025-6552
DOI - 10.17814/mechanik.2018.3.35
Subject(s) - gas compressor , structural engineering , aero engine , enhanced data rates for gsm evolution , blade (archaeology) , fatigue testing , fatigue limit , fatigue cracking , instrumentation (computer programming) , cracking , engineering , materials science , mechanical engineering , computer science , composite material , telecommunications , operating system
Article presents the research results of aircraft compressor blade damage length and its position influence on fatigue strength under high number cycles conditions. The criteria for blade damage detection classification and test research methodology were developed. Designed and tested the instrumentation for compressor blades fatigue tests. Fluorescent method was used to determine the source of fatigue cracking initiation and its propagation direction during fatigue test.