Circumferentially varying axial compressor endwall treatment for controlling leakage flow therein

Patent metadata

Field	Value
Publication number	US-2016169017-A1
Application number	US-201414572119-A
Country	US
Kind code	A1
Filing date	Dec 16, 2014
Priority date	Dec 16, 2014
Publication date	Jun 16, 2016
Grant date	—

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 one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub, the one or more endwall treatments 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 upstream of a point of removal of the flow, each of the one or more endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow.

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 2 , wherein the one or more endwall treatments comprise a plurality of discrete circumferentially varying slots defined circumferentially about at least one of the compressor hub or the compressor casing.

4 . The compressor as claimed in claim 3 , wherein the plurality of discrete circumferentially varying slots are circumferentially varied in placement relative to the immediately adjacent upstream bladerow.

5 . The compressor as claimed in claim 4 , wherein the plurality of discrete circumferentially varying slots include identical geometric parameters.

6 . The compressor as claimed in claim 4 , further comprising a blade passage defined between adjacent blades of the upstream blade row and wherein circumferentially varied in placement includes varying a number of the plurality of discrete circumferentially varying slots per blade passage.

7 . The compressor as claimed in claim 3 , wherein the plurality of discrete circumferentially varying slots include circumferentially varied geometric parameters.

8 . The compressor as claimed in claim 7 , wherein the circumferentially varied geometric parameters comprise one or more of axial lean angles, tangential lean angles, radial height, axial length, bend angles, slot width and planform area.

9 . The compressor as claimed in claim 3 , wherein the plurality of discrete circumferentially varying slots include radially varying widths.

10 . 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 one or more circumferentially varied end-wall treatments formed in at least one of the casing and the hub, wherein the one or more circumferentially varied end-wall treatments are formed in an interior surface of at least one of the casing or the hub, the one or more circumferentially varied endwall treatments 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 one or more circumferentially varied endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow; and flowing the portion of the fluid flow through the one or more circumferentially varied end-wall treatments to address circumferential flow non-uniformities introduced by an upstream blade-row.

11 . The method of claim 10 , wherein the immediately adjacent upstream bladerow comprises a plurality of stator blades.

12 . The method of claim 11 , wherein extracting a portion of the fluid flow into one or more circumferentially varied end-wall treatments includes extracting the fluid flow into a plurality of discrete circumferentially varying slots defined circumferentially about at least one of the compressor hub or the compressor casing.

13 . The method of claim 12 , wherein the plurality of discrete circumferentially varying slots are 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 discrete circumferentially varying slots.

14 . The method of claim 13 , wherein circumferentially varied in placement includes one of blade clocking relative to the immediately adjacent upstream bladerow or varying a number of discrete circumferentially varying slots in a blade passage defined between adjacent blades in the immediately adjacent upstream bladerow.

15 . The method of claim 13 , wherein the circumferentially varied geometric parameters comprise one or more of axial lean angles, tangential lean angles, radial height, axial length and planform area.

16 . An engine comprising:
a compressor; a combustor; a turbine, wherein the compressor, the combustor, and the turbine are configured in a downstream axial flow relationship, the compressor comprising:
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, the one or more endwall treatments 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 one or more endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow.

17 . The engine of claim 16 , wherein the immediately adjacent upstream bladerow comprises a plurality of stator blades and the one or more endwall treatments comprise a plurality of discrete circumferentially varying slots defined circumferentially about at least one of the compressor hub or the compressor casing.

18 . The engine of claim 16 , wherein the plurality of discrete circumferentially varying slots are 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 discrete circumferentially varying slots.

19 . The engine of claim 18 , wherein the circumferentially varied geometric parameters comprise one or more of axial lean angles, tangential lean angles, radial height, axial length, bend angles, slot width and planform area.

20 . The engine of claim 16 , wherein the core 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

• F01D11/001 Primary

  for sealing space between stator blade and rotor · CPC title

• F04D27/02

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

• F04D29/685

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

• F04D29/68

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