Seal assembly for a guide vane assembly

Patent metadata

Field	Value
Publication number	US-9617864-B2
Application number	US-201514793362-A
Country	US
Kind code	B2
Filing date	Jul 7, 2015
Priority date	Jul 21, 2014
Publication date	Apr 11, 2017
Grant date	Apr 11, 2017

Abstract

The present disclosure relates generally to a guide vane assembly including a first airfoil, including a first airfoil trailing edge, a second airfoil, including a second airfoil leading edge, positioned aft the first airfoil to create a gap therebetween, and a seal assembly disposed within the gap to engage the first airfoil trailing edge and the second airfoil leading edge.

First claim

What is claimed is:

1. A guide vane assembly for a gas turbine engine comprising:
a first airfoil, including a first airfoil trailing edge;
a second airfoil, including a second airfoil leading edge, positioned aft the first airfoil to create a gap therebetween; and
a seal assembly disposed within the gap to engage the first airfoil trailing edge and the second airfoil leading edge, wherein the seal assembly comprises:
a pressure component; and
a seal, including a protruding side and a buried side, wherein the pressure component is in contact with the buried side and the pressure component is configured to maintain contact between the protruding side and at least one of the first airfoil trailing edge and the second airfoil leading edge.

2. The guide vane assembly of claim 1 , wherein the pressure component comprises a spring.

3. The guide vane assembly of claim 1 , wherein the seal comprises a low-friction material.

4. The guide vane assembly of claim 1 , wherein the seal comprises a coating disposed thereon.

5. The guide vane assembly of claim 1 , wherein at least a portion of the protruding side is arcuate.

6. The guide vane assembly of claim 1 , wherein the first airfoil comprises an airfoil selected from the group consisting of variable incidence and fixed.

7. The guide vane assembly of claim 1 , wherein the second airfoil comprises an airfoil selected from the group consisting of variable incidence and fixed.

8. The guide vane assembly of claim 1 , wherein the first airfoil trailing edge includes a slot, disposed within the first airfoil trailing edge, wherein the slot is positioned substantially parallel to a first airfoil trailing edge longitudinal axis, and wherein the seal assembly is disposed within the slot.

9. The guide vane assembly of claim 8 , wherein the protruding side of the seal is in contact with the second airfoil leading edge.

10. The guide vane assembly of claim 1 , wherein the second airfoil leading edge includes a slot, disposed within the second airfoil leading edge, wherein the slot is positioned substantially parallel to a second airfoil leading edge longitudinal axis, and wherein the seal assembly is disposed within the slot.

11. The guide vane assembly of claim 10 , wherein the protruding side of the seal is in contact with the first airfoil trailing edge.

12. A gas turbine engine comprising:
a compressor section;
a plurality of guide vane assemblies, positioned within the compressor section, wherein each guide vane assembly comprising:
a first airfoil, including a first airfoil trailing edge, and a first airfoil trailing edge longitudinal axis;
a second airfoil, including a second airfoil leading edge, and a second airfoil leading edge longitudinal axis, wherein the second airfoil leading edge is positioned aft the first airfoil trailing edge to create a gap therebetween;
a slot disposed within the first airfoil trailing edge positioned substantially parallel to the first airfoil trailing edge longitudinal axis; and
a seal assembly disposed within the slot to engage the second airfoil leading edge, wherein the seal assembly comprises:
a pressure component; and
a seal, including a protruding side and a buried side, wherein the pressure component is in contact with the buried side and the pressure component is configured to maintain contact between the protruding side and the first airfoil trailing edge.

13. A gas turbine engine comprising:
a compressor section;
a plurality of guide vane assemblies, positioned within the compressor section, wherein each guide vane assembly comprising:
a first airfoil, including a first airfoil trailing edge, and a first airfoil trailing edge longitudinal axis;
a second airfoil, including a second airfoil leading edge, and a second airfoil leading edge longitudinal axis, wherein the second airfoil leading edge is positioned aft the first airfoil trailing edge to create a gap therebetween;
a slot disposed within the second airfoil leading edge positioned substantially parallel to the second airfoil leading edge longitudinal axis; and
a seal assembly disposed within the slot to engage the first airfoil trailing edge, wherein
the seal assembly comprises:
a pressure component; and
a seal, including a protruding side and a buried side, wherein the pressure component is in contact with the buried side and the pressure component is configured to maintain contact between the protruding side and the second airfoil leading edge.

Assignees

• United Technologies Corp

Inventors

• Firnhaber Michael C
• Dibenedetto Enzo

Classifications

• F01D5/146

  of blades with tandem configuration, split blades or slotted blades · CPC title

• F01D11/003

  by packing rings; Mechanical seals · CPC title

• F05D2240/121

  related to the leading edge of a stator vane · CPC title

• F01D9/041 Primary

  using blades (F01D5/148 takes precedence) · CPC title

• 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