Compressor apparatus with bleed slot and supplemental flange

Patent metadata

Field	Value
Publication number	US-2022018293-A1
Application number	US-202117188780-A
Country	US
Kind code	A1
Filing date	Mar 1, 2021
Priority date	Apr 27, 2017
Publication date	Jan 20, 2022
Grant date	—

Abstract

An example compressor bleed slot apparatus includes an annular compressor casing, a blade row mounted for rotation about a centerline axis inside the compressor casing, a bleed slot passing through the forward section of the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row, an array of struts interconnecting the inboard and outboard walls, and an annular supplemental flange extending radially outward from the forward section of the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot, wherein the supplemental flange includes a necked-down portion adjacent the forward section of the compressor casing, the necked-down portion positioned axially between an inlet of the bleed slot and an outlet of the bleed slot.

First claim

What is claimed is:

1 . A compressor bleed slot apparatus, comprising:
an annular compressor casing; a blade row mounted for rotation about a centerline axis inside the compressor casing; a bleed slot passing through a forward section of the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the compressor casing, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row; an array of struts interconnecting the inboard and outboard walls; and an annular supplemental flange extending radially outward from the forward section of the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot, wherein the supplemental flange includes a necked-down portion adjacent the forward section of the compressor casing, the necked-down portion positioned axially between an inlet of the bleed slot and an outlet of the bleed slot.

2 . The apparatus of claim 1 wherein the supplemental flange includes a pair of spaced-apart faces defining a V-shape therebetween.

3 . The apparatus of claim 1 wherein the slot axis is disposed at an angle of 65° or less relative to the centerline axis.

4 . The apparatus of claim 1 wherein the slot axis is disposed at an angle of 30° to 65° relative to the centerline axis.

5 . The apparatus of claim 1 wherein the slot has an outlet positioned within the axial extent of the blade row.

6 . The apparatus of claim 1 wherein the inboard and outboard walls diverge from each other in a downstream direction relative to the bleed slot.

7 . The apparatus of claim 1 , wherein an enlarged portion of the supplemental flange is radially spaced apart from an annular outer wall of the compressor casing.

8 . The apparatus of claim 1 , wherein the supplemental flange is positioned at an angle with respect to the bleed slot axis.

9 . The apparatus of claim 1 further comprising an extended diffuser having divergent walls positioned downstream of the bleed slot.

10 . The apparatus of claim 9 , wherein the diffuser extends beyond the struts a distance of at least 50% of a chord length of the struts.

11 . The apparatus of claim 1 , wherein the struts are to control a throat area of the bleed slot, the struts to improve a structural stiffness of the bleed slot.

12 . The apparatus of claim 1 , wherein the supplemental flanges are incorporated to control a thermal response of the compressor casing.

13 . The apparatus of claim 1 , wherein at least one of the struts includes a concave sidewall joined to a convex sidewall at a leading edge and a trailing edge.

14 . A gas turbine engine apparatus, comprising:
a compressor, a combustor, and a turbine arranged in serial flow relationship, wherein the compressor includes: an annular compressor casing; a stator row disposed inside the compressor casing; a blade row mounted for rotation about a centerline axis inside the compressor casing; a bleed slot passing through a forward section of the compressor casing, wherein the bleed slot is bounded by inboard and outboard walls defined within the forward section of the compressor casing, the bleed slot having an inlet positioned axially between the stator row and the blade row, the bleed slot extending along a slot axis, at least a portion of the bleed slot lying within an axial extent of the blade row; and an annular supplemental flange extending radially outward from the forward section of the compressor casing, wherein at least a portion of the supplemental flange is axially positioned within an axial extent of the bleed slot, wherein the supplemental flange is cantilevered and has a freestanding end, and wherein the supplemental flange includes an enlarged portion at an outer periphery thereof, and a necked-down portion adjacent the forward section of the compressor casing, wherein the necked-down portion is positioned axially between the inlet of the bleed slot and an outlet of the bleed slot.

15 . The apparatus of claim 14 wherein the supplemental flange includes a pair of spaced-apart faces defining a V-shape therebetween.

16 . The apparatus of claim 14 wherein the slot axis is disposed at an angle of 65° or less relative to the centerline axis.

17 . The apparatus of claim 14 wherein the slot axis is disposed at an angle of 30° to 65° relative to the centerline axis.

18 . The apparatus of claim 14 wherein the slot has an outlet positioned within the axial extent of the blade row.

19 . The apparatus of claim 14 wherein the inboard and outboard walls diverge from each other in a downstream direction relative to the bleed slot.

20 . The apparatus of claim 14 further comprising an extended diffuser having divergent walls positioned downstream of the bleed slot.

Assignees

• Gen Electric

Inventors

• Taylor Steven Mitchell
• K Vishnu Das
• Singhal Manish
• Saha Atanu
• Thomas Michael Anthony

Classifications

• F04D29/522 Primary

  especially adapted for elastic fluid pumps · CPC title

• F02C9/18 Primary

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F05D2240/12

  Fluid guiding means, e.g. vanes · CPC title

• F04D29/601

  specially adapted for elastic fluid pumps · CPC title

• F05D2220/32

  in gas turbines · CPC title