Abstract: A gas turbine includes a plurality of combustors and a turbine with a sealing arrangement between aft frames of the combustors and a first stage nozzle of the turbine. The sealing arrangement includes first and second circumferential outer seals with a radial side seal therebetween, the outer seals include circumferential extensions with an installation clearance, and the side seal includes a leaf that obstructs the installation clearance. The sealing arrangement also includes a notch on the side seal that forms a sliding joint with extensions of the first and second outer seals.

Abstract: A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. Each of the inner seals includes a wing extending radially inward at an oblique angle. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first wing extending radially outward at an oblique angle and a second wing extending radially outward at an oblique angle, the first wing of the side seal sealingly interfaces with the wing of the first inner seal and the second wing of the side seal sealingly interfaces with the wing of the second inner seal.

Abstract: A combustor assembly includes a combustion liner defining a first radial opening, an outer sleeve that at least partially surrounds the combustion liner. The outer sleeve defines a second radial opening. A mounting body having a jacket portion and a flange portion surrounds the first radial opening and extends radially outwardly from an outer surface of the combustion liner towards the outer sleeve. The flange portion is at least partially disposed within the second radial opening. An auxiliary component extends radially within the jacket portion and includes a flange portion. The flange portion of the auxiliary component is connected to the flange portion of the mounting body via a first fastener, and the flange portion of the auxiliary component is connected to the outer sleeve via a second fastener.

Abstract: The present application provides a gas turbine engine. The gas turbine engine may include a compressor discharge casing, a number of combustors configured in an annular array, and a number of aft mounting assemblies. An aft mounting assembly mounts a combustor to an inner diameter of the compressor discharge casing.

Abstract: A combustor assembly includes a combustion liner defining a first radial opening, an outer sleeve that at least partially surrounds the combustion liner. The outer sleeve defines a second radial opening. A mounting body having a jacket portion and a flange portion surrounds the first radial opening and extends radially outwardly from an outer surface of the combustion liner towards the outer sleeve. The flange portion is at least partially disposed within the second radial opening. An auxiliary component extends radially within the jacket portion and includes a flange portion. The flange portion of the auxiliary component is connected to the flange portion of the mounting body via a first fastener, and the flange portion of the auxiliary component is connected to the outer sleeve via a second fastener.

Abstract: A gas turbine includes a plurality of combustors and a turbine with a sealing arrangement between aft frames of the combustors and a first stage nozzle of the turbine. The sealing arrangement includes first and second circumferential outer seals with a radial side seal therebetween, the outer seals include circumferential extensions with an installation clearance, and the side seal includes a leaf that obstructs the installation clearance. The sealing arrangement also includes a notch on the side seal that forms a sliding joint with extensions of the first and second outer seals.

Abstract: A sealing arrangement for sealing between a first stage nozzle and a plurality of aft frames includes a first inner seal and a second inner seal which are circumferentially oriented and circumferentially aligned. Each of the inner seals includes a wing extending radially inward at an oblique angle. A side seal is radially disposed between the first inner seal and the second inner seal. The side seal includes a first wing extending radially outward at an oblique angle and a second wing extending radially outward at an oblique angle, the first wing of the side seal sealingly interfaces with the wing of the first inner seal and the second wing of the side seal sealingly interfaces with the wing of the second inner seal.

Abstract: The present application provides a gas turbine engine. The gas turbine engine may include a compressor discharge casing, a number of combustors configured in an annular array, and a number of aft mounting assemblies. An aft mounting assembly mounts a combustor to an inner diameter of the compressor discharge casing.