Compressor end-wall treatment having a bent profile

A method comprising:

• introducing a fluid flow along a flow passage defined by a compressor end-wall of the compressor, wherein the compressor end-wall comprising a casing and a hub disposed concentrically about and coaxially along a longitudinal axis,
• wherein the compressor comprises at least one of a rotor blade and a stator blade, wherein the rotor blade is coupled to the hub, extends between the hub and the casing, and defines a blade passage there between an adjacent rotor blade, wherein the stator blade is coupled to the casing, extends between the casing and the hub, and defines a blade passage there between an adjacent stator blade;
• extracting a portion of the fluid flow into an end-wall treatment among the plurality of end-wall treatments spaced apart from each other and formed in an interior surface of at least one of the casing and the hub,
• wherein each end-wall treatment faces a tip of the rotor blade or the stator blade, wherein each end-wall treatment comprises a forward recess portion extending along a first axis and an aft recess portion extending along a second axis different than the first axis, wherein the aft recess portion is joined to the corresponding forward recess portion via an intersection portion which is inclined relative to at least one of the first axis, and the second axis, wherein at least one of the aft recess portion and the forward recess portion is bent from the intersection portion and inclined relative to an axial direction of the compressor, and wherein the aft and forward recess portions comprise an axial lean inclined relative to at least one of the axial direction of the compressor, the first axis, and the second axis, and a circumferential lean inclined relative to a circumferential direction of the compressor;
• and
• flowing the portion of the fluid flow along the first axis to maintain a fluid flow substantially straight through the forward recess portion, and along the second axis to maintain the fluid flow substantially straight through the aft recess portion.

An engine comprising:

• a compressor;
• a combustor;
• and
• a turbine, wherein the compressor, the combustor, and the turbine are configured in a downstream axial flow relationship, the compressor comprising:
• a compressor end-wall defining a flow passage, the compressor end-wall comprising a casing and a hub disposed concentrically about and coaxially along a longitudinal axis;
• at least one of a rotor blade and a stator blade, wherein the rotor blade is coupled to the hub, extends between the hub and the casing, and defines a blade passage there between an adjacent rotor blade, wherein of the stator blade is coupled to the casing, extends between the casing and the hub, and defines a blade passage there between an adjacent stator blade;
• and
• a plurality of end-wall treatments spaced apart from each other and formed in an interior surface of at least one of the casing and the hub, wherein each end-wall treatment faces a tip of the rotor blade or the stator blade,
• wherein each end-wall treatment comprises a forward recess portion extending along a first axis to maintain a fluid flow substantially straight through the forward recess portion, and an aft recess portion extending along a second axis different than the first axis to maintain the fluid flow substantially straight through the aft recess portion, wherein the aft recess portion is joined to the corresponding forward recess portion via an intersection portion which is inclined relative to at least one of the first axis, and the second axis, wherein at least one of the aft recess portion and the forward recess portion is bent from the intersection portion and inclined relative to an axial direction of the compressor, and wherein the aft and forward recess portions comprise an axial lean inclined relative to at least one of the axial direction of the compressor, the first axis, and the second axis, and a circumferential lean inclined relative to a circumferential direction of the compressor.