SEAL ASSEMBLY FOR A GUIDE VANE ASSEMBLY

• US 20160017739A1
• Filed: 07/07/2015
• Published: 01/21/2016
• Est. Priority Date: 07/21/2014
• Status: Active Grant

• Current Assignee: Rtx Corporation
• Original Assignee: United Technologies Corporation (Raytheon Technologies Corporation d/b/a RTX)
• Inventors: DiBenedetto, Enzo, Firnhaber, Michael C.
• Granted Patent: US 9,617,864 B2
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 11/003 by packing rings; Mechanical seals
• CPC Class Codes: F01D 17/162 for axial flow, i.e. the vanes turning around axes which are essentially perpendicular to the rotor centre line F01D17/167 takes precedence
• CPC Class Codes: F01D 9/041 using blades F01D5/148 takes precedence
• CPC Class Codes: F04D 29/563 specially adapted for elastic fluid pumps
• CPC Class Codes: F05D 2230/90 Coating; Surface treatment manufacture with deposition of material F05D2230/30
• CPC Class Codes: F05D 2240/121 related to the leading edge of a stator vane

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.

Claims

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.

2. The guide vane assembly of claim 1, wherein the seal assembly comprises:

a pressure mechanism; and

a seal, including a protruding side and a buried side,

wherein the pressure component is in contact with the buried side.

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

4. The guide vane assembly of claim 2, wherein the seal comprises a low-friction material.

5. The guide vane assembly of claim 2, wherein the seal comprises a coating disposed thereon.

6. The guide vane assembly of claim 2, wherein at least a portion of the protruding side is arcuate.

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

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

9. The guide vane assembly of claim 2, 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.

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

11. The guide vane assembly of claim 2, 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.

12. The guide vane assembly of claim 11, wherein the protruding side is in contact with 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 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.

14. The gas turbine engine of claim 13, wherein the seal assembly comprises:

a pressure mechanism; and

a seal, including a protruding side and a buried side,

wherein the pressure component is in contact with the buried side.

15. A gas turbine engine comprising:

a compressor section;

a plurality of guide vane assemblies, positioned within of 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.

16. The gas turbine engine of claim 15, wherein the seal assembly comprises:

a pressure mechanism; and

a seal, including a protruding side and a buried side,

wherein the pressure component is in contact with the buried side.