<abstract xmlns="http://www.w3.org/1999/xhtml">

<p>One of the major problems in the development of algorithms for monitoring the life of aircraft gas turbine engines is that the character of loading in real flight cycles is crucially different from the character of the static and dynamic loading during the testing of samples. This paper proposes a method for taking into account the effect of retentions at maximum stresses and cycle temperatures on the low-cycle fatigue (LCF) of the heat-resistant alloys used in engine parts. Regularities in repeated-static loading (RSL) are used in combination with the method of linear accumulation of damage due to the LCF and RSL, with retentions of a variable length. A non-linear equation is derived for the summation of these damages, the solution of which determines the durability (life) of the part while taking into account the retention duration. The theoretical results were verified by using the experimental characteristics of the GS-6K and EI-437B nickel-based alloys, previously reported by other researchers.</p>
</abstract>

One of the major problems in the development of algorithms for monitoring the life of aircraft gas turbine engines is that the character of loading in real flight cycles is crucially different from the character of the static and dynamic loading during the testing of samples. This paper proposes a method for taking into account the effect of retentions at maximum stresses and cycle temperatures on the low-cycle fatigue (LCF) of the heat-resistant alloys used in engine parts. Regularities in repeated-static loading (RSL) are used in combination with the method of linear accumulation of damage due to the LCF and RSL, with retentions of a variable length. A non-linear equation is derived for the summation of these damages, the solution of which determines the durability (life) of the part while taking into account the retention duration. The theoretical results were verified by using the experimental characteristics of the GS-6K and EI-437B nickel-based alloys, previously reported by other researchers.

Impact of Load Retention on Aircraft Engine Parts Under Real Flight Cycle Conditions in Service Life Monitoring

Department of Aircraft Engine Design, Faculty of Aviation Engines

National Aerospace University “Kharkiv Aviation Institute”

Transactions on Aerospace Research

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

One of the major problems in the development of algorithms for monitoring the life of aircraft gas turbine engines is that the character of loading in real...

Impact of Load Retention on Aircraft Engine Parts Under Real Flight Cycle Conditions in Service Life Monitoring

Publicado en línea: 08 oct 2021

Páginas: 47 - 57

DOI: https://doi.org/10.2478/tar-2021-0016

Palabras clave
gas turbine engine, service life, repeated-static loading, low-cycle fatigue, creep, retention of load

© 2021 Sergiy Yepifanov et al., published by Sciendo

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Impact of Load Retention on Aircraft Engine Parts Under Real Flight Cycle Conditions in Service Life Monitoring

Publicado en línea: 08 oct 2021

Páginas: 47 - 57

DOI: https://doi.org/10.2478/tar-2021-0016

Palabras clavegas turbine engine, service life, repeated-static loading, low-cycle fatigue, creep, retention of load

© 2021 Sergiy Yepifanov et al., published by Sciendo

This work is licensed under the Creative Commons Attribution-NonCommercial-NoDerivatives 4.0 International License.

Palabras clave
gas turbine engine, service life, repeated-static loading, low-cycle fatigue, creep, retention of load