Combustor sliding joint

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 distal flange and an opposed free second end disposed radially inward of the distal flange. The flexible arm has a first surface and a second surface spaced radially inward from the first surface. A spacer on the first surface of the flexible arm projects radially away toward the distal flange. The spacer defines a gap and axially displaces with respect to the lug upon thermal expansion of the large exit duct. The leading edge lug of the turbine vane assembly is disposed in the gap, and the second end of the flexible arm is disposed radially inward of the leading edge lug.

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 outer surface, the sliding joint comprising:
 an elongated flexible arm 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;   a spacer on 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 lug upon thermal expansion of the large exit duct; and   the leading edge lug of the turbine vane assembly disposed in the gap, and the second end of the flexible arm disposed radially inward of the leading edge lug.   
     
     
         2 . The sliding joint as defined in  claim 1 , wherein the second end of the flexible arm is disposed in opposed spaced relation with the leading edge lug and defines 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 spacer is made of an abradable material. 
     
     
         7 . 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. 
     
     
         8 . 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. 
     
     
         9 . The sliding joint as defined in  claim 1 , wherein the flexible arm is made from a material having a coefficient of thermal expansion being greater than a coefficient of thermal expansion of the distal flange. 
     
     
         10 . The sliding joint as defined in  claim 1 , wherein the spacer is separate from the first surface of the second end of the flexible arm and is joined thereto. 
     
     
         11 . The sliding joint as defined in  claim 1 , wherein the spacer is on an extremity of the first surface of the second end of the flexible arm that is axially downstream furthest from the first end of the flexible arm. 
     
     
         12 . 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 interconnecting a large exit duct and a small entry 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;   a turbine vane assembly disposed downstream of the combustor and having at least one turbine vane and a leading edge lug; and   a sliding joint disposed between the combustor and the turbine vane assembly, the sliding joint comprising:
 an elongated flexible arm 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; 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; 
   the leading edge lug of the turbine vane assembly 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.   
     
     
         13 . The gas turbine engine as defined in  claim 12 , wherein the distal flange overlaps the leading edge lug of the turbine vane assembly and is spaced radially outwardly therefrom. 
     
     
         14 . The gas turbine engine as defined in  claim 12 , wherein a first radial distance is defined between the leading edge lug and the distal flange, and a second radial distance is defined between the leading edge lug and the second end of the flexible arm, the first radial distance being greater than the second radial distance. 
     
     
         15 . The gas turbine engine as defined in  claim 12 , wherein the distal flange is made from a material having a coefficient of thermal expansion, and the flexible arm is made from a material having a coefficient of thermal expansion being greater than the coefficient of thermal expansion of the distal flange. 
     
     
         16 . The gas turbine engine as defined in  claim 12 , 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. 
     
     
         17 . The gas turbine engine as defined in  claim 12 , 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. 
     
     
         18 . 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 interconnecting a large exit duct and a small entry 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;   a turbine vane assembly disposed downstream of the combustor and having at least one turbine vane and a leading edge lug; and   a sliding joint disposed between the combustor and the turbine vane assembly, the sliding joint comprising:
 an elongated flexible arm 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; 
 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; 
 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; and 
 a second spacer joined to the unattached end of the second flexible arm and spaced apart from the spacer of the flexible arm to be displaceable relative thereto. 
   
     
     
         19 . The gas turbine engine as defined in  claim 18 , wherein the second flexible arm has a third surface and a fourth surface spaced radially inward of the third surface, the second spacer joined to the fourth surface 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. 
     
     
         20 . The gas turbine engine as defined in  claim 18 , wherein one or both of the spacer and the second spacer is made of an abradable material.