Patent ID: 9488179
Filing Date: 2016-11-08
CPC Classification: F01D,F04D,F05D

Claim Text:
1. An axial flow turbine engine compressor comprising: a casing presenting an inside wall of general shape that defines an aerodynamic reference surface defining a gas-passing passage; a rotor wheel mounted to rotate relative to the casing in the passage; the rotor wheel carrying a plurality of radial blades, each having a tip, a leading edge, and a trailing edge; a circumferential trench being formed in the inside wall of the casing; a shape of the trench being defined by three substantially conical surfaces, of an upstream surface, a middle surface, and a downstream surface, the surfaces following one after another from upstream to downstream; the middle surface being substantially parallel to the aerodynamic reference surface; the downstream surface extending downstream at least as far as the trailing edges of the blades; the upstream surface being located entirely upstream from the leading edges of the blades; and a junction between the middle and downstream surfaces is situated in a range of 30% to 80% of an axial length of the blades starting from the leading edge.