PSI - Issue 41

Available online at www.sciencedirect.com Available online at www.sciencedirect.com ScienceDirect Structural Integrity Procedia 00 (2022) 000–000

www.elsevier.com/locate/procedia

ScienceDirect

Procedia Structural Integrity 41 (2022) 298–304

2nd Mediterranean Conference on Fracture and Structural Integrity Fatigue crack propagation for an aircraft compressor under input data variability

Venanzio Giannella*, Raffaele Sepe, Roberto Citarella Department of Industrial Engineering, University of Salerno, Fisciano (SA), Italy

© 2022 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of the MedFract2Guest Editors. Abstract The quantification of all the uncertainty sources affecting the phenomenon of fatigue crack-growth is essential to enhance competitiveness in designing more high-performance products, e.g. aircraft engines. This work reports crack propagation simulations for a first-stage compressor of a turbo-fan engine, by considering the impact on life prediction accuracy given by geometrical tolerances, material variability and actual rotational speed. Crack-growth simulations were developed by Finite Element Method (FEM) considering the variability of the fillet radius between blades and disk, so as to derive the distribution of Stress Intensity Factors (SIF) along the crack size as a function of both fillet radius and rotational speed. Consequently, a NASGRO formulation, calibrated on Ti6Al4V test data, was implemented in a MATLAB routine in a stochastic way so as to derive the residual life predictions for the component. Statistical evaluations were made and the contributes of all the considered uncertainty sources were compared and classified. © 2022 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of the MedFract2Guest Editors Keywords: Aircraft compressor; crack-growth; geometrical tolerances; material scattering; load variability; Ti-6Al-4V; life predictions 1. Introduction Since the late 1970s, there has been a concerted effort in the gas turbine engine industry to enhance the safe-life design of rotating engine components by including damage tolerant methodologies in the design process. Damage tolerant approach had been in place for airframe structures since was introduced in standards in 1971 (MIL-A- competitiveness in designing more high-performance products, e.g. aircraft engines. This work reports crack propagation s an open a

* Corresponding author. Tel.: +39-089-964082; fax: +39-089-964082. E-mail address: vgiannella@unisa.it

2452-3216 © 2022 The Authors. Published by ELSEVIER B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of the MedFract2Guest Editors.

2452-3216 © 2022 The Authors. Published by Elsevier B.V. This is an open access article under the CC BY-NC-ND license (https://creativecommons.org/licenses/by-nc-nd/4.0) Peer-review under responsibility of the MedFract2Guest Editors. 10.1016/j.prostr.2022.05.035