Gas turbine engine ducting arrangement having discrete insert

Abstract

A ducting arrangement ( 10 ), including: a plurality of discrete ducts ( 18 ), each defining a flow path and configured to receive a flow of combustion gases from a respective combustor can, where the plurality of discrete ducts merge to form a common duct structure; and a throat insert ( 50 ) configured to define at least part of a junction of one of the discrete ducts and the common duct structure.

The invention claimed is: 
     
         1 . A ducting arrangement, comprising:
 a plurality of discrete ducts, each defining a flow path and configured to receive a flow of combustion gases from a respective combustor can, wherein the plurality of discrete ducts merge to form a common duct structure; and   a throat insert configured to define at least part of a junction of one of the discrete ducts and the common duct structure.   
     
     
         2 . The ducting arrangement of  claim 1 , wherein the ducting arrangement is formed by bicasting ducting material around the throat insert. 
     
     
         3 . The ducting arrangement of  claim 1 , wherein the throat insert is configured to define part of a flow path associated with the one discrete duct. 
     
     
         4 . The ducting arrangement of  claim 1 , wherein the throat insert comprises an intersection of a corner of the one discrete duct and a corner of the common duct structure. 
     
     
         5 . The ducting arrangement of  claim 1 , wherein a throat material of the throat insert comprises a different mechanical property than a ducting material immediately surrounding the throat insert. 
     
     
         6 . The ducting arrangement of  claim 1 , further comprising an expansion gap between the throat insert and ducting material surrounding the throat insert effective to prevent internal stress in the throat insert from exceeding a yield strength of a material of the throat insert. 
     
     
         7 . The ducting arrangement of  claim 1 , wherein an interface between the throat insert and a remainder of the ducting arrangement forms a tortuous path. 
     
     
         8 . The ducting arrangement of  claim 1 , wherein an interface between the throat insert and a remainder of the ducting arrangement forms a geometric interlock effective to secure the throat insert in place. 
     
     
         9 . A ducting arrangement, comprising:
 a plurality of discrete ducts, each defining a flow path configured to receive a flow of combustion gases from a respective combustor can;   a common duct structure into which the plurality of discrete ducts merge; and   a plurality of discrete throat inserts, each configured to define at least part of a junction between one of the discrete ducts and the common duct structure,   wherein the ducting arrangement is configured to structurally compensate for a non-metallurgical bond at an interface of the discrete throat inserts with a remainder of the ducting arrangement.   
     
     
         10 . The ducting arrangement of  claim 9 , wherein the ducting arrangement is formed by bi-casting ducting material around the plurality of discrete throat inserts. 
     
     
         11 . The ducting arrangement of  claim 9 , wherein the ducting arrangement is configured to flex in order to structurally compensate for the non-metallurgical bond. 
     
     
         12 . The ducting arrangement of  claim 9 , wherein a portion of the ducting arrangement immediately surrounding the throat inserts is thickened with respect to a remainder of the ducting arrangement to structurally compensate for the non-metallurgical bond. 
     
     
         13 . The ducting arrangement of  claim 9 , wherein a throat material of the throat inserts comprises a greater high-temperature stability than a ducting material in which the throat inserts reside. 
     
     
         14 . The ducting arrangement of  claim 9 , wherein ducting material defines a plurality of openings in each of which a respective throat insert resides, and wherein each opening is sized to permit thermal growth interference between the throat insert and the ducting material without exceeding a yield strength of a material of the throat insert. 
     
     
         15 . The ducting arrangement of  claim 9 , wherein each throat insert defines a portion of a flow path associated with a respective discrete duct. 
     
     
         16 . A ducting arrangement, comprising:
 a ducting arrangement subcomponent comprising a discrete duct and a downstream end, the discrete duct defining a flow path and configured to receive a flow of combustion gases from a respective combustor can, wherein the downstream end constitutes part of a common duct structure configured to deliver combustion gases to a turbine inlet annulus when assembled to other ducting arrangement subcomponents; and   a throat insert disposed configured to define at least part of a junction of the discrete duct and the downstream end,   wherein the junction is formed by bi-casting a ducting material around the throat insert.   
     
     
         17 . The ducting arrangement of  claim 16 , wherein a throat material of the throat insert comprises a reduced yield strength relative to the ducting material. 
     
     
         18 . The ducting arrangement of  claim 16 , wherein a throat material comprises an increased high-temperature stability relative to a remainder of the junction. 
     
     
         19 . The ducting arrangement of  claim 16 , wherein the throat insert and a remainder of the ducting arrangement are free to thermally grow relative to each other. 
     
     
         20 . The ducting arrangement of  claim 16 , wherein the throat insert and the ducting material around the throat insert are configured to accommodate thermal growth interference there between without exceeding a yield strength of the throat insert.