Using sweep and dihedral to control three-dimensional flow in transonic stators of axial compressors

The paper describes an advanced three-dimensional blading concept for highl y loaded transonic compressor stators. The concept rakes advantage of the t he aerodynamic effects of sweep and dihedral. To the knowledge of the autho rs this is the first approach reported in the open literature that combines those two basic types of lean in an engine-worthy aerofoil design. The pap er makes a contribution to the understanding of the endwall effect of both features with special emphasis put on sweep. The advanced three-dimensional blading concept was applied to an Engine Section Starer (ESS) of an aero-e ngine fan. In ai-der to demonstrate how three-dimensional flow can be contr olled numerical analysis of the flow structure in a conventional and an adv anced stator configuration was performed using a three-dimensional Navier-S tokes solver. The numerical analysis showed the advanced blade improving bo th radial loading distribution and the three-dimensional endwall boundary l ayer development In particular, a strong hub corner stall could be largely alleviated High-speed rig testing of the advanced ESS confirmed the concept and showed good qualitative agreement between measurement and prediction. The work presented was closely linked to the development of the BR710 engin e on which the advanced ESS is in service today.