Structural tailoring of aircraft engine blade subject to ice impact constraints | Zendy

E.S. Reddy | Zendy; Galib Abumeri | Zendy; Pappu L. N. Murthy | Zendy; C. C. Chamis | Zendy

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Structural tailoring of aircraft engine blade subject to ice impact constraints

Author(s) -

E.S. Reddy,

Galib Abumeri,

Pappu L. N. Murthy,

C. C. Chamis

Publication year - 1992

Publication title -

5th symposium on multidisciplinary analysis and optimization

Language(s) - English

Resource type - Conference proceedings

DOI - 10.2514/6.1992-4710

Subject(s) - blade (archaeology) , aero engine , aerospace engineering , subject (documents) , computer science , aeronautics , engineering , marine engineering , mechanical engineering , world wide web

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.

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