By Theodore Nicholas
Dr Theodore Nicholas ran the excessive Cycle Fatigue software for the united states Air strength among 1995 and 2003 at Wright-Patterson Air strength Base, and is without doubt one of the world's major experts at the topic, having authored over 250 papers in major archival journals and books. Bringing his plethora of craftsmanship to this publication, Dr Nicholas discusses the topic of excessive cycle fatigue (HCF) from an engineering standpoint in accordance with a sequence of HCF disasters within the USAF and the concurrent consciousness that HCF mess ups regularly have been occurring universally in either civilian and armed forces engines. subject lined comprise: - consistent existence diagrams - Fatigue limits lower than mixed LCF and HCF - Notch fatigue lower than HCF stipulations - international item harm (FOD) * Brings years of the Author's US Air strength event in excessive cycle fatigue jointly in a single textual content * Discusses HCF within the context of modern overseas army and civilian engine disasters
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Extra resources for High Cycle Fatigue: A Mechanics of Materials Perspective
Durability, on the other hand, eliminates the task of excessive and unscheduled maintenance involving part replacement or added inspections. The remainder of this section is concerned with the concept of damage tolerance and its potential application to HCF. Introduction 17 While damage tolerance as applied to LCF has a limited role in HCF, the concepts and philosophical aspects are important to grasp in understanding how HCF problems can be addressed. Damage tolerance is a design philosophy that was adapted by the US Air Force for both airframe structures in the 1970s and for turbine engines in the 1980s.
The types of damage that must be addressed, if relevant, include fretting, galling, FOD, combined LCF–HCF, corrosion pitting, thermomechanical fatigue, creep, and their combinations. 4. Schematic of damage accumulation applicable to HCF. 3, and many variations thereof, were used numerous times as an illustration of how a damage tolerant approach could save costs in not having to replace engine components when they reached their design lifetimes. These schematic plots were created and used by Dr Walter Reimann of the Air Force Materials Laboratory many times to champion the Retirement for Cause (RFC) program that was eventually adopted by the US Air Force and produced cost savings approaching a billion dollars.
Methods, particularly accelerated methods, for obtaining such stress values are commonly obtained from S–N plots either by having data at the desired life or 36 Introduction and Background Maximum stress extrapolating data to the required life, often 107 cycles. 11. Here, points A, B, and C represent the FLS either directly from the data or by extrapolation to 107 cycles in this case. 11, the stress is plotted as the maximum stress although the stress range or alternating stress could also be used.
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