Gas turbine engine vane end devices

Patent metadata

Field	Value
Publication number	US-11326464-B2
Application number	US-201916453438-A
Country	US
Kind code	B2
Filing date	Jun 26, 2019
Priority date	Feb 26, 2013
Publication date	May 10, 2022
Grant date	May 10, 2022

Abstract

A turbomachinery component of a gas turbine engine is disclosed having a number of techniques of reducing the effects of a gap flow between an airfoil member of the gas turbine engine and a wall of the gas turbine engine. The airfoil member can be variable and in one form is a variable turbine vane. In one embodiment a brush seal is included between the vane and the wall. In another form a wear surface is disposed between the vane and the wall. In yet another form a moveable member capable of being actuated to change position can be disposed between the vane and the wall to alter the size of a gap between the two.

First claim

What is claimed is:

1. An apparatus comprising:
a rotatable airfoil member for a gas turbine engine having an end structured to contact a wall of the gas turbine engine, the end having an abradable coating configured to wear according to a contact between the abradable coating and the wall of the gas turbine engine,
wherein the rotatable airfoil member is disposed adjacent a rotatable blade and the rotatable airfoil member is configured to turn a working fluid, the rotatable blade configured to rotate around a central axis of the gas turbine engine, and the rotatable airfoil member is rotatable about a rotation axis that extends perpendicularly from the central axis,
wherein the end of the rotatable airfoil member defines two squealer tips integrally formed with the rotatable airfoil member such that the two squealer tips are blocked from moving radially relative to the rotatable airfoil member, the two squealer tips spaced apart from each other, wherein the abradable coating is applied to a radial outer tip of each of the two squealer tips, and the two squealer tips engage the wall of the gas turbine engine, and
wherein the rotatable airfoil member is a turbine vane, and the turbine vane includes a cooling hole disposed between the two squealer tips.

2. The apparatus of claim 1 , wherein one of the two squealer tips is disposed toward a relatively low pressure side of the vane and the other of the two squealer tips is disposed toward a relatively high pressure side of the vane.

3. The apparatus of claim 1 , wherein the abradable coating is made of a first material and the end of the vane is made of a second material.

4. The apparatus of claim 3 , wherein the first material is different than the second material.

5. The apparatus of claim 3 , wherein a density of the first material is different than a density of the second material.

6. An apparatus comprising:
a rotatable airfoil member for a gas turbine engine, the rotatable airfoil member having a first end and a second end spaced apart radially from the first end relative to a central axis of the gas turbine engine such that the rotatable airfoil member extends radially relative to the central axis, the first end of the rotatable airfoil member formed to include a first squealer member that is integrally formed with the first end so that the first squealer member is blocked from moving radially relative to the first end, and wherein the first squealer member extends radially outward away from the first end relative to the central axis, the rotatable airfoil member configured to rotate about a rotation axis that extends radially through the rotatable airfoil member, and the rotation axis is perpendicular to the central axis; and
a wall arranged circumferentially around the first end of the rotatable airfoil member relative to the central axis;
wherein the rotatable airfoil member further includes a first wear surface disposed on a radial terminating tip of the first squealer member, the first wear surface configured to engage the wall in response to the rotatable airfoil member rotating about the rotation axis, and the first wear surface is configured to be abraded when relative movement between the rotatable airfoil member and the wall causes the rotatable airfoil member and the wall to contact each other.

7. The apparatus of claim 6 , wherein the rotatable airfoil member includes a leading edge and a trailing edge spaced apart axially from the leading edge relative to the central axis and the first squealer member is located at the leading edge of the rotatable airfoil member.

8. The apparatus of claim 7 , wherein the rotatable airfoil member is formed to include a cooling hole formed in the first end of the rotatable airfoil member.

9. The apparatus of claim 8 , wherein the rotatable airfoil member includes a second squealer member and a second wear surface disposed on the second squealer member and the second squealer member is spaced apart from the first squealer member to locate the cooling hole between the first squealer member and the second squealer member.

10. The apparatus of claim 9 , wherein the first wear surface has a first radial thickness and the second wear surface has a second radial thickness that is different than the first radial thickness.

11. The apparatus of claim 6 , wherein the rotatable airfoil member includes a leading edge and a trailing edge spaced apart axially from the leading edge relative to the central axis and the first squealer member is located at the trailing edge of the rotatable airfoil member.

12. The apparatus of claim 6 , wherein the rotatable airfoil member includes a leading edge and a trailing edge spaced apart axially from the leading edge relative to the central axis and a radial thickness of the first wear surface varies as a function of axial location of the first wear surface relative to the central axis.

13. The apparatus of claim 12 , wherein the first wear surface is thicker near the trailing edge than that near the leading edge of the rotatable airfoil member.

14. The apparatus of claim 6 , wherein the first squealer member is airfoil shaped and extends continuously around the first end of the rotatable airfoil member.

15. The apparatus of claim 6 , wherein the rotatable airfoil member is made of a first material and the first wear layer is made of a second material that is different than the first material.

16. The apparatus of claim 6 , wherein the first wear surface is formed from a material and an entirety of the first squealer member is formed from the material.

17. The apparatus of claim 6 , wherein the rotatable airfoil member includes a second squealer member and a second wear surface disposed on the second squealer member, the first wear surface has a first radial thickness, and the second wear surface has a second radial thickness that is different than the first radial thickness.

18. The apparatus of claim 6 , wherein the rotatable airfoil member includes a second squealer member spaced apart from the first squealer member, the rotatable airfoil member is a turbine vane, the turbine vane includes a cooling hole disposed between the first and second squealer members, and wherein the first squealer member is disposed toward a relatively low pressure side of the turbine vane and the second squealer member is disposed toward a relatively high pressure side of the turbine vane.

Assignees

• Rolls Royce Nam Tech Inc
• Rolls Royce Corp

Inventors

• Taketa Linnea
• Munson John
• Freeman Ted J

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

• F05D2240/56

  Brush seals · CPC title

• F04D19/02

  Multi-stage pumps · CPC title

• F04D27/0246

  by varying geometry within the pumps, e.g. by adjusting vanes · CPC title

• F01D11/122

  with erodable or abradable material (blades having cutting or grinding tips F01D5/20) · CPC title