Patent ID: 8647066
Filing Date: 2014-02-11
Classification: F01D,F05D,Y02T

Abstract:
1. A blade for a turbomachine impeller, comprising: an airfoil including a pressure surface, a suction surface, a trailing edge, and a leading edge; a platform extending at one of the ends of the airfoil in a direction globally perpendicular to a longitudinal direction of the airfoil; the blade being adapted to be arranged with a plurality of substantially identical blades to form a ring around a ring axis and define therealong upstream and downstream directions, with the ring having the airfoils arranged substantially radially therein; wherein a suction surface profile at the surface of the platform and along the suction surface has a first recessed part located axially in an upstream half of the airfoil, and a first boss-like part located axially downstream of the first recessed part.