Combustor sliding joint

Patent metadata

Field	Value
Publication number	US-10612403-B2
Application number	US-201414454366-A
Country	US
Kind code	B2
Filing date	Aug 7, 2014
Priority date	Aug 7, 2014
Publication date	Apr 7, 2020
Grant date	Apr 7, 2020

Abstract

A sliding joint in a gas turbine engine between a large exit duct of a combustor and a turbine vane assembly having a leading edge lug. The sliding joint has an elongated flexible arm extending between a first end joined to the outer surface of the large entry duct, and an opposed free second end disposed radially inward of the outer surface of the large entry duct. A spacer is joined to the second end of the arm and projects radially away therefrom toward the outer surface of the large entry duct. The spacer is spaced apart from the outer surface and defines a gap therebetween. The spacer, the arm, and the sliding joint axially displace with respect to the lug upon thermal expansion of the large entry duct.

First claim

The invention claimed is:

1. A sliding joint between a large exit duct of a combustor of a gas turbine engine and a turbine vane assembly having a leading edge lug, the large exit duct having a distal flange defining an inner surface and an outer surface, the sliding joint comprising:
an elongated flexible arm made from a resilient sheet metal and extending between a first end joined to the outer surface of the distal flange and an opposed free second end disposed radially inward of the distal flange, the flexible arm having a first surface and a second surface spaced radially inward from the first surface, the flexible arm being made from a material having a coefficient of thermal expansion being greater than a coefficient of thermal expansion of the distal flange; and
a spacer joined to the first surface of the second end of the flexible arm and projecting radially away therefrom toward the distal flange, the spacer made of an abradable material and spaced apart from the distal flange and defining a gap therebetween, the spacer axially displacing with respect to the lug upon thermal expansion of the large exit duct.

2. The sliding joint as defined in claim 1 , wherein the second end of the flexible arm is disposed radially inward of the lug of the turbine vane assembly and in opposed spaced relation therewith defining a second gap therebetween.

3. The sliding joint as defined in claim 2 , wherein the spacer projects radially away from the first surface of the second end within the second gap and toward the lug of the turbine vane assembly.

4. The sliding joint as defined in claim 1 , further comprising an elongated second flexible arm extending between a fixed end joined to the turbine vane assembly and an opposed unattached end disposed radially inward of the distal flange, the second flexible arm having a third surface and a fourth surface spaced radially inward of the third surface.

5. The sliding joint as defined in claim 4 , further comprising a second spacer joined to the fourth surface of the unattached end of the second flexible arm and projecting radially inward toward the spacer of the flexible arm, the second spacer spaced apart from the spacer and defining a spacer gap therebetween, the spacer axially displacing with respect to the second spacer upon thermal expansion of the large exit duct.

6. The sliding joint as defined in claim 1 , wherein the flexible arm is made from a sheet metal having a first gauge, and the spacer is made from a sheet metal having a second gauge, the second gauge being greater than the first gauge.

7. The sliding joint as defined in claim 1 , wherein the flexible arm has at least one cooling hole extending through the flexible arm between the first surface and the second surface.

8. A gas turbine engine, comprising:
a combustor defining a flowpath extending downstream from an upstream dome end towards a combustor exit, the upstream dome end being in fluid communication with a large exit duct and a small exit duct to define a combustion chamber therewithin, the large exit duct having a distal flange defining an inner surface facing the combustion chamber, and an outer surface, the distal flange being made from a material having a coefficient of thermal expansion;
a turbine vane assembly disposed downstream of the combustor and having at least one turbine vane and a leading edge lug, the leading edge lug is disposed radially inwardly of the distal flange and overlapped by the distal flange; and
a sliding joint disposed between the combustor and the turbine vane assembly, the sliding joint comprising:
an elongated flexible arm made from a resilient sheet metal and extending between a first end joined to the outer surface of the distal flange of the large exit duct, and an opposed free second end disposed radially inward of the distal flange, the flexible arm having a first surface and a second surface spaced radially inward from the first surface, the flexible arm being made from a material having a coefficient of thermal expansion being greater than the coefficient of thermal expansion of the distal flange; and
a spacer joined to the first surface of the second end of the flexible arm and projecting radially away therefrom toward the distal flange, the spacer spaced apart from the distal flange and defining a gap therebetween, the spacer axially displacing with respect to the leading edge lug upon thermal expansion of the large exit duct of the combustor.

9. The gas turbine engine as defined in claim 8 , wherein the leading edge lug of the turbine vane assembly is disposed in the gap between the second end of the flexible arm and the distal flange, the second end of the flexible arm disposed radially inward of the leading edge lug of the turbine vane assembly and in opposed spaced relation therewith defining a second gap therebetween.

10. The gas turbine engine as defined in claim 9 , wherein the spacer projects radially away from the first surface of the second end within the second gap and toward the leading edge lug of the turbine vane assembly.

11. The gas turbine engine as defined in claim 8 , further comprising an elongated second flexible arm extending between a fixed end joined to the turbine vane assembly and an opposed unattached end disposed radially inward of the distal flange, the second flexible arm having a third surface and a fourth surface spaced radially inward of the third surface.

12. The gas turbine engine as defined in claim 11 , further comprising a second spacer joined to the fourth surface of the unattached end of the second flexible arm and projecting radially inward toward the spacer of the flexible arm, the second spacer spaced apart from the spacer and defining a spacer gap therebetween, the spacer axially displacing with respect to the second spacer upon thermal expansion of the large exit duct.

13. The gas turbine engine as defined in claim 8 , wherein the flexible arm is made from a sheet metal having a first gauge, and the spacer is made from a sheet metal having a second gauge, the second gauge being greater than the first gauge.

Assignees

• Pratt & Whitney Canada

Inventors

• Stastny Honza
• Sze Robert

Classifications

• F23R3/60

  Support structures; Attaching or mounting means · CPC title

• F23R2900/00012

  Details of sealing devices · CPC title

• F23R2900/00005

  Preventing fatigue failures or reducing mechanical stress in gas turbine components · CPC title

• F01D9/023 Primary

  Transition ducts between combustor cans and first stage of the turbine in gas-turbine engines; their cooling or sealings · CPC title