Citation

John SK, Balachandra Shetty P, Mishra RK. J. Fail. Anal. Prev. 2018; 18(4): 1034-1042.

Copyright

(Copyright © 2018, ASM International, Publisher Holtzbrinck Springer Nature Publishing Group)

DOI

10.1007/s11668-018-0495-4

PMID

unavailable

Abstract

Aero engines exhibit typical product life cycle operational reliability characteristics of infant mortality, useful period before the final wear out phase. The reliability of operations during the infant mortality phase of operation of a newly designed, developed and productionized components or systems is always less compared to the other phases of its life. Critical examination of various defects and problems that arise during this phase indicates that the problems are mainly due to design deficiency compared to manufacturing, quality issues etc. Systematic and scientific resolution of these design-related reliability problems can go a long way in maturing the system and enhancing their availability for operation through the design life. This paper presents a scientific approach for addressing various infant mortality problems encountered in a turbo-shaft engine enabled with the state-of-the-art technology features. A critical design-related defect affecting adversely the operational availability of the engines for helicopters has been considered in the paper as the model for explaining the above approach. Such model can be adopted for resolution of typical design-related problems of aero engines and its systems for improving the reliability of operations.

Language: en

Keywords

Bending load analysis; Breaking torque; Campbell diagram; Failure effects and contingency analysis; Fatigue analysis; Goodman diagram; Infant mortality period; Sensitivity analysis