Compressor end-wall treatment having a bent profile

Patent metadata

Field	Value
Publication number	US-10539154-B2
Application number	US-201415531992-A
Country	US
Kind code	B2
Filing date	Dec 10, 2014
Priority date	Dec 10, 2014
Publication date	Jan 21, 2020
Grant date	Jan 21, 2020

Abstract

A compressor is provided including a compressor end-wall having a casing and a hub. The compressor further includes at least one set of rotor blades, one set of stator blades, and a plurality of end-wall treatments spaced apart from each other, formed in an interior surface of at least one of the casing and hub, and facing a tip of the rotor blade or stator blade. Each end-wall treatment includes a forward recess portion extending along a first axis and an aft recess portion extending along a second axis different than the first axis. 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. The aft recess portion and/or the forward recess portion are bent from the intersection portion and inclined relative to an axial direction of the compressor.

First claim

The invention claimed is:

1. A 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 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.

2. The compressor of claim 1 , wherein the axial lean of the aft recess portion is in a range from about 0 degree to about 180 degrees relative to a surface of the compressor end-wall, and the axial lean of the forward recess portion is in a range from about 0 degree to about 150 degrees relative to the surface of the compressor end-wall.

3. The compressor of claim 1 , wherein the circumferential lean of the aft and forward recess portions are in a range from about 5 degrees to about 175 degrees relative to a surface of the compressor end-wall.

4. The compressor of claim 1 , wherein the aft and forward recess portions are inclined in a range from about −170 degrees to about 170 degrees.

5. The compressor of claim 1 , wherein the intersection portion is inclined in a range from about 30 degrees to about 150 degrees.

6. The compressor of claim 1 , wherein the plurality of end-wall treatments per each blade passage is in a range from about 0 to about 100.

7. The compressor of claim 1 , wherein the aft and forward recess portions are defined circumferentially about the compressor end-wall.

8. The compressor of claim 1 , wherein the aft and forward recess portions have a radial height in a range from about 5 percent to about 200 percent of an axial chord length of the tip of each blade among the plurality of rotor and stator blades.

9. The compressor of claim 1 , wherein the aft recess portion has an axial length in a range from about 0 percent to about 100 percent of an axial chord length of the tip of each blade among the plurality of rotor and stator blades.

10. The compressor of claim 1 , wherein the forward recess portion has an axial length in a range from about 0 percent to about 200 percent of an axial chord length of the tip of each blade among the plurality of rotor and stator blades.

11. The compressor of claim 1 , wherein the plurality of end-wall treatments has a solidity in a range from about 5 percent to about 95 percent of a pitch of each blade among the plurality of rotor and stator blades.

12. The compressor of claim 1 , wherein each end-wall treatment comprises a bend offset in front of each blade among the plurality of rotor and stator blades, wherein the bend offset is in a range from about −100 percent to about 300 percent of an axial chord length of the tip of each blade among the plurality of rotor and stator blades.

13. 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.

14. The method of claim 13 , further comprising distributing at least one of a sub-portion of the fluid flow from the aft recess portion into the forward recess portion, and the sub-portion of the fluid flow from the forward recess portion into the aft recess portion.

15. The method of claim 14 , further comprising recirculating the portion and the sub-portion of the fluid flow from the aft and forward recess portions into a gap formed between the tip of each blade among the plurality of rotor and stator blades, and each end-wall treatment.

16. 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 lea

Assignees

• Gen Electric

Inventors

• Mallina Ramakrishna Venkata
• Yoon Sungho
• Michelassi Vittorio
• Malcevic Ivan

Classifications

• F02C3/04

  having a turbine driving a compressor (power transmission arrangements F02C7/36; control of working fluid flow F02C9/16) · CPC title

• F04D29/685

  Inducing localised fluid recirculation in the stator-rotor interface · CPC title

• F04D29/526 Primary

  Details of the casing section radially opposing blade tips (ducts F04D29/545) · CPC title

• F01D5/145

  Means for influencing boundary layers or secondary circulations (for compressors F04D29/68) · CPC title

• F04D29/542

  Bladed diffusers (fixing blades to stators F01D9/042) · CPC title