A Procedure for Axial Blade Optimization

[+] Author and Article Information
P. F. W. de Neeve, R. V. Dukkipati

Pratt & Whitney Aircraft of Canada Ltd., Longueuil, Quebec J4K 4X9, Canada

J. Eng. Power 101(3), 315-319 (Jul 01, 1979) (5 pages) doi:10.1115/1.3446578 History: Received September 05, 1978; Online July 14, 2010


This paper proposes a method to modify the geometry of an axial blade to obtain a better stress distribution without compromising the aerodynamic design. The method is applied to an axial blade and is most relevant to those blades with a high degree of twist, such as for instance fan blades. The behavior of such blades is described by a finite element shell model. The initial aerodynamic definition of the axial blade is taken as the basic geometry. Variations of geometry are now considered, which maintain the essential aerodynamic characteristics, and the stresses are calculated. The stresses are expressed as a linear function of the geometric variations. A simple search technique is utilized to find the optimum combination of geometric variations. An example of a representative model shows that a quick convergence towards the final geometry is achieved.

Copyright © 1979 by ASME
Topics: Optimization , Blades
Your Session has timed out. Please sign back in to continue.





Some tools below are only available to our subscribers or users with an online account.

Related Content

Customize your page view by dragging and repositioning the boxes below.

Related Journal Articles
Related eBook Content
Topic Collections

Sorry! You do not have access to this content. For assistance or to subscribe, please contact us:

  • TELEPHONE: 1-800-843-2763 (Toll-free in the USA)
  • EMAIL: asmedigitalcollection@asme.org
Sign In