Turbomachine including a vane and method of assembling such turbomachine

Patent metadata

Field	Value
Publication number	US-9995166-B2
Application number	US-201414550506-A
Country	US
Kind code	B2
Filing date	Nov 21, 2014
Priority date	Nov 21, 2014
Publication date	Jun 12, 2018
Grant date	Jun 12, 2018

Abstract

A vane for a turbomachine includes a pressure surface and a suction surface opposite the pressure surface. The pressure surface and the suction surface define a width therebetween. The vane also includes a first end. The first end includes a distal portion, a proximal portion, a pressure surface first portion, and a suction surface first portion. At least one of the pressure surface first portion and the suction surface first portion slope away from the other of the pressure surface first portion and the suction surface first portion such that the width increases from a first end minimum width at the proximal portion to a first end maximum width at the distal portion.

First claim

What is claimed is:

1. A vane for a turbomachine, said vane comprising:
a pressure surface;
a suction surface opposite said pressure surface, said pressure surface and said suction surface defining a width therebetween;
a first end comprising:
a distal portion including a distal surface extending from said pressure surface to said suction surface;
a proximal portion;
a pressure surface first portion; and
a suction surface first portion, at least one of said pressure surface first portion and said suction surface first portion sloping away from the other of said pressure surface first portion and said suction surface first portion such that said width increases from a first end minimum width at said proximal portion to a first end maximum width at said distal portion, wherein said at least one of said pressure surface first portion and said suction surface first portion is sloped along an extension from said proximal portion to said distal portion distal surface;
wherein the slope of said at least one of said pressure surface first portion and said suction surface first portion is constant from said proximal portion to said distal surface.

2. The vane in accordance with claim 1 , wherein said second end distal portion includes a second distal surface extending from said pressure surface to said suction surface,
at least one of said pressure surface second portion and said suction surface second portion sloping away from the other of said pressure surface second portion and said suction surface second portion such that said width increases from a second end minimum width at said second end proximal portion to a second end maximum width at said second end distal portion, wherein said at least one of said pressure surface second portion and said suction surface second portion is sloped along an extension from said second end proximal portion to said second distal surface.

3. The vane in accordance with claim 2 , wherein said pressure surface and said suction surface define a middle portion width that is substantially constant throughout said middle portion, said middle portion width equal to said first end minimum width and said second end minimum width.

4. The vane in accordance with claim 3 , wherein said first end maximum width equals said second end maximum width.

5. The vane in accordance with claim 2 , wherein said first end maximum width is greater than said second end maximum width.

6. The vane in accordance with claim 1 , wherein said pressure surface first portion makes an angle between about 140° and about 165° with said pressure surface middle portion.

7. The vane in accordance with claim 1 , wherein both said pressure surface first portion and said suction surface first portion are sloped.

8. The vane in accordance with claim 2 , wherein both said first end distal portion and said second end distal portion are pivotably coupled to the turbomachine.

9. The vane in accordance with claim 8 , wherein said distal surface is contoured to match an inner surface of the turbomachine such that a clearance space between said distal surface and said inner surface remains constant as said vane is pivoted.

10. The vane in accordance with claim 9 , wherein said second end distal portion comprises a second distal surface, said second distal surface contoured to match a second inner surface of the turbomachine such that a clearance space between said second distal surface and said second inner surface remains constant as said vane is pivoted.

11. A turbomachine comprising:
at least one rotatable element;
a casing extending at least partly circumferentially around said at least one rotatable element, said casing at least partially defining an airway; and
a vane extending across said airway, said vane comprising:
a pressure surface;
a suction surface opposite said pressure surface, said pressure surface and said suction surface defining a width therebetween; and
a first end comprising:
a distal portion coupled to said casing said distal portion including a distal surface extending from said pressure surface to said suction surface, wherein said distal surface and said casing define a clearance space therebetween;
a proximal portion;
a pressure surface first portion; and
a suction surface first portion, at least one of said pressure surface first portion and said suction surface first portion sloping away from the other of said pressure surface first portion and said suction surface first portion such that said width increases from a first end minimum width at said proximal portion to a first end maximum width at said distal portion, wherein said at least one of said pressure surface first portion and said suction surface first portion is sloped along an extension from said proximal portion to said distal surface;
wherein the slope of said at least one of said pressure surface first portion and said suction surface first portion is constant from said proximal portion to said distal surface.

12. The turbomachine in accordance with claim 11 , wherein said vane further comprises a second end comprising:
a distal portion coupled to said casing, said second end distal portion including a second distal surface extending from said pressure surface to said suction surface, wherein said second distal surface and said casing define a second clearance space therebetween; and
a proximal portion.

13. The turbomachine in accordance with claim 12 , wherein said vane further comprises a middle portion extending between said first end and said second end, said middle portion coupled to said first end proximal portion and to said second end proximal portion.

14. The turbomachine in accordance with claim 12 , wherein said second end further comprises:
a pressure surface second portion; and
a suction surface second portion, at least one of said pressure surface second portion and said suction surface second portion sloping away from the other of said pressure surface second portion and said suction surface second portion such that said width increases from a second end minimum width at said second end proximal portion to a second end maximum width at said second end distal portion, wherein said at least one of said pressure surface second portion and said suction surface second portion is sloped along an extension from said second end proximal portion to said second distal surface.

15. The turbomachine in accordance with claim 13 wherein said vane pivots about a pivot axis extending through said vane from said first end to said second end.

16. The turbomachine in accordance with claim 11 , wherein said vane has a height and said first end distal portion is spaced from said casing a distance between about 0.6% and about 1.3% of said height.

17. The turbomachine in accordance with claim 12 , wherein said vane has a height and said second end distal portion is spaced from said casing a distance between about 0.6% and about 1.3% of said height.

18. A method of assembling a turbomachine, said method comprising:
coupling a first casing member to a second casing member to at least partially enclose a rotatable element, the first casing member and second casing member at least partially defining an airway;
forming a flared vane including:
a pressure surface;
a suction surface opposite the pressure surface, the pressure surface and the suction surface defining a width therebetween; and
a first end including:
a distal portion having a first distal surface extending from the pressure surface to the suction surface;
a proximal portion;
a pressure surface first

Assignees

• Gen Electric

Inventors

• Vandeputte Thomas William

Classifications

• F01D17/162 Primary

  for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line (F01D17/167 takes precedence) · CPC title

• F04D29/563

  specially adapted for elastic fluid pumps · CPC title

• F01D5/145

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

• F05D2240/125

  related to the tip of a stator vane · CPC title

• F01D9/045

  for radial flow machines or engines · CPC title