Abstract
A shaft has been designed for the high-pressure rotor of a low-bypass military turbofan engine. The complex mission profile of the engine with high throttle excursion demands reliable operation of the shaft throughout the flight envelope maintaining structural integrity and life. Therefore, qualification of the shaft for a fighter class engine is a challenge from airworthiness point of view. This paper presents the methodology adopted and various stages of qualification and standards followed to demonstrate structural integrity and life of the shaft for fitment in engine and engine on aircraft. The shaft successfully completed the qualification procedure and thus ensured the airworthiness for aero engine fitment.
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Mishra, R.K., Subramanian, M.S. Qualification Approach for High-Pressure Spool Shaft of a Low-Bypass Turbofan Engine for Structural Integrity and Life. J Fail. Anal. and Preven. 23, 135–140 (2023). https://doi.org/10.1007/s11668-022-01565-9
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DOI: https://doi.org/10.1007/s11668-022-01565-9