Inverse Design of Turbomachinery Blading Using Transpiration Method
by
Iman Firoozpour
Department of Aerospace Engineering, K.N.Toosi University of Technology, Tehran, Iran
Coauthors: H. Fazeli

An inverse blade design method, applicable for 2D flow in turbomachinery blading is developed and is implemented for the design of 2D cascades in compressible viscous flow. The prescribed design quantity is the pressure distribution on the blade surfaces. The blade modifications are based on transpiration principle. The transpiration flux is computed from the difference between the actual and the prescribed pressure distribution. Since the blade shape is not compatible with the required pressure distribution at first, a nonzero velocity component normal to the blade wall evolves from the new flow calculation. The inverse design method is validated for a typical turbine cascade geometries which can be used in modern gas turbine engines.

Date received: April 27, 2008

Copyright © 2008 by the author(s). The author(s) of this document and the organizers of the conference have granted their consent to include this abstract in Atlas Conferences Inc. Document # caxc-78.