Transition duct mounting system

A transition duct for a gas turbine engine comprising:

• a panel assembly having:
• a first panel formed from a single sheet of metal;
• a second panel formed from a single sheet of metal;
• said first panel fixed to said second panel along a plurality of axial seams by means such as welding, thereby forming a duct having an inner wall, an outer wall, and a first thickness therebetween said inner and outer walls, a generally cylindrical inlet end, and a generally rectangular exit end, said generally rectangular exit end defined by a pair of arcs of different diameters concentric about a center and connected by a pair of radial lines extending from said center;
• a generally cylindrical inlet sleeve having an inner diameter and outer diameter, said inlet sleeve fixed to said inlet end of said panel assembly;
• a generally rectangular aft frame having opposing sidewalls, said frame fixed to said exit end of said panel assembly;
• a plurality of retention lugs located on said aft frame proximate said arcs of said generally rectangular exit end;
• each of said retention lugs having a second thickness and containing a slot having a first circumferential length and a first radial width;
• the outermost retention lugs located proximate ends of said arcs which define said generally rectangular exit end;
• inner and outer bulkhead assemblies including:
• a first inner and first outer bulkhead having a plurality of first through holes;
• a second inner and second outer bulkhead having a plurality of second through holes;
• a plurality of bushings, each bushing having a second axial length, a second circumferential length, a second radial width, and a third through hole, each of said bushings is located within one of said slots of said outermost retention lugs;
• an aft mount assembly for fixturing a transition duct to the turbine inlet region of a gas turbine comprising:
• a plurality of mounting plates each having at least a fourth through hole and a spherical bearing located within a housing, said spherical bearing having a fifth through hole;
• a plurality of washers;
• a plurality of lock tabs;
• a first means for securing said mounting plates to a turbine inlet of a gas turbine engine wherein said first securing means passes through said fourth hole in said mounting plate;
• a second securing means for securing said aft mount assembly and said bulkhead assemblies to said aft frame such that said second securing means passes through at least one of said retention lugs of said aft frame, through at least one of said first and second through holes of said bulkheads, one of said spherical bearings of said aft mount assembly, and one of said lock tabs.