Compressor and a turbine engine with optimized efficiency

摘要

A turbine engine compressor including a casing having its inside wall defining an aerodynamic reference surface for a gas-passing passage and in which a rotor wheel having radial blades is mounted. A circumferential trench is formed in the inside wall of the casing. Its shape is defined from upstream to downstream by three surfaces, respectively an upstream surface, a middle surface, and a downstream surface, which surfaces are substantially conical. The upstream surface extends upstream from the leading edges of the blades. The middle surface is substantially parallel to the aerodynamic reference surface. The downstream surface extends downstream at least as far as the trailing edges of the blades. The junction between the middle and downstream surfaces is in a range of 30% to 80% or 50% to 65% of the axial length of the blades starting from their leading edges.

主权项

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.