NDLI: Structural tailoring of aircraft engine blade subject to ice impact constraints

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Structural tailoring of aircraft engine blade subject to ice impact constraints

Content Provider	NASA Technical Reports Server (NTRS)
Author	Reddy, E. S. Abumeri, G. H. Murthy, P. L. N. Chamis, C. C.
Copyright Year	1993
Description	Results are presented for the minimum weight design of SR2 unswept blade made of (titanium/graphite-epoxy/titanium) sub s fiber composite. The blade which is rotating at high RPM is subject to ice impact. The root chord length, blade thicknesses at five stations, and graphite-epoxy ply orientation are chosen as design variables. Design constraints are placed on the behavior variables: local leading edge strain and root damage parameter (combined stress failure criteria) as a function due to ice impact, maximum spanwise centrifugal stress at the root of the deformed blade due to local damage, first three natural frequencies, and resonance margin after impact. The method of feasible directions is employed to solve the inequality constrained minimization problem. The effect of ice speed and the ice impact location on the final design are discussed.
File Size	790615
Page Count	24
File Format	PDF
Alternate Webpage(s)	http://archive.org/details/NASA_NTRS_Archive_19930017810
Archival Resource Key	ark:/13960/t0wq4wc5q
Language	English
Publisher Date	1993-04-01
Access Restriction	Open
Subject Keyword	Structural Mechanics Structural Design Aircraft Construction Materials Fiber Composites Ice Aircraft Engines Laminates Design Analysis Optimization Resonant Frequencies Failure Analysis Centrifugal Force Graphite-epoxy Composites Ply Orientation Damage Leading Edges Impact Damage Combined Stress Ntrs Nasa Technical Reports Server (ntrs) Nasa Technical Reports Server Aerodynamics Aircraft Aerospace Engineering Aerospace Aeronautic Space Science
Content Type	Text
Resource Type	Article

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