Circumferentially varying axial compressor endwall treatment for controlling leakage flow therein

Patent metadata

Field	Value
Publication number	US-10047620-B2
Application number	US-201414572119-A
Country	US
Kind code	B2
Filing date	Dec 16, 2014
Priority date	Dec 16, 2014
Publication date	Aug 14, 2018
Grant date	Aug 14, 2018

Abstract

A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.

First claim

What is claimed is:

1. A compressor comprising:
a casing;
a hub;
a cylindrical flow passage formed between the casing and the hub and defining a flow path;
a plurality of blades positioned in the flow path; and
a plurality of discrete axial slots formed in a single row, relative to each of the plurality of blades, and along a circumferential direction about an interior surface of at least one of the casing or the hub, the plurality of discrete axial slots configured to return a flow adjacent one of a plurality of rotor blade tips or a plurality of stator blade tips to the cylindrical flow passage and upstream of a point of removal of the flow, wherein each of the plurality of discrete axial slots has a radial height based on their position circumferentially about the interior surface of the at least one of the casing or hub and relative to an immediately adjacent upstream bladerow and wherein the radial height varies between the plurality of discrete axial slots.

2. The compressor as claimed in claim 1 , wherein the immediately adjacent upstream bladerow comprises a plurality of stator blades.

3. The compressor as claimed in claim 1 , wherein each of the plurality of discrete axial slots is aligned substantially along a principal axis that is perpendicular to a direction of rotation of the plurality of blades.

4. The compressor as claimed in claim 1 , wherein the plurality of discrete axial slots include geometric parameters that vary between the plurality of discrete axial slots.

5. The compressor as claimed in claim 4 , wherein the geometric parameters comprise one or more of axial lean angles, tangential lean angles, radial height, axial length, bend angles, slot width and planform area.

6. The compressor as claimed in claim 1 ,
wherein the plurality of discrete axial slots include radially varying widths.

7. A method comprising:
introducing a fluid flow along a cylindrical flow passage formed between a casing and a hub of a compressor, the cylindrical flow passage defining a flow path, wherein the compressor further comprises a plurality of blades positioned in the flow path;
extracting a portion of the fluid flow into a plurality of discrete axial slots formed in a single row relative to each of the plurality of blades and along a circumferential direction about an interior surface of at least one of the casing and the hub, the plurality of discrete axial slots configured to return a flow adjacent one of the plurality of rotor blade tips or the plurality of stator blade tips to the cylindrical flow passage upstream of a point of removal of the flow, each of the plurality of discrete axial slots having a radial height based on their position circumferentially about the at least one of the casing or hub and relative to an immediately adjacent upstream bladerow and wherein the radial height varies between the plurality of discrete axial slots; and
flowing the portion of the fluid flow through the plurality of discrete axial slots to address circumferential flow non-uniformities introduced by an upstream bladerow.

8. The method of claim 7 , wherein the immediately adjacent upstream bladerow comprises a plurality of stator blades.

9. The method of claim 7 , wherein each of the plurality of discrete axial slots includes geometric parameters that vary between the plurality of discrete axial slots.

10. The method of claim 9 , wherein the geometric parameters comprise one or more of axial lean angles, tangential lean angles, radial height, axial length and planfbrm area.

11. An engine comprising:
a compressor according to claim 1 ;
a combustor;
a turbine, wherein the compressor, the combustor, and the turbine are configured in a downstream axial flow relationship.

12. The engine of claim 11 , wherein the immediately adjacent upstream bladerow comprises a plurality of stator blades.

13. The engine of claim 1 , wherein each of the plurality of discrete axial slots includes geometric parameters that vary between the plurality of discrete axial slots.

14. The engine of claim 13 , wherein the geometric parameters comprise one or more of axial lean angles, tangential lean angles, radial height, axial length, bend angles, slot width and planform area.

15. The engine of claim 11 , wherein the engine is configured for use in an aircraft engine.

Assignees

• Gen Electric

Inventors

• Giacché Davide
• Stampfli John David
• Mallina Ramakrishna Venkata
• Michelassi Vittorio
• Jothiprasad Giridhar
• Rao Ajay Keshava
• Selmeier Rudolf Konrad
• Yoon Sungho
• Malcevic Ivan

Classifications

• F04D29/681

  especially adapted for elastic fluid pumps · CPC title

• F04D29/526

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

• F01D11/001 Primary

  for sealing space between stator blade and rotor · CPC title

• F04D29/68

  by influencing boundary layers {(by bleeding elastic fluid F04D27/0215)} · CPC title

• F04D27/02

  Surge control {(surge detection F04D27/001)} · CPC title