Abstract: An exhaust nozzle for a gas turbine engine includes a nozzle casing having top and bottom walls and side walls. A liner is provided within the nozzle casing to define a cooling passage. The top and bottom walls each include mutually inclined planar wall portions which meet at respective creases. The creases increase the rigidity of the top and bottom walls. In addition, the inclined wall portions cause the cooling passage to taper in the direction outwardly from the creases, so assisting in the cooling air distribution over the liner.

Abstract: A duct installation, for example a casing 4 and an exhaust duct 8 of a gas turbine engine, comprises a main body 12 and an end section 14 of the casing 4 which are separable at a coupling including end flanges 18, 20. The end section 14 is axially slidable over the exhaust duct 8, taking with it a liner section 36, so as to provide access to the engine or to permit removal of the engine without disturbing the exhaust duct 8.

Abstract: A gas turbine engine annular combustor has a bulkhead at its upstream end which is protected by an annular array of heatshield segments. The segments are spaced apart from the bulkhead by means of a plurality of flanges. Cooling air apertures provided in the bulkhead direct cooling air into the space between the heatshield and the bulkhead. A portion of the cooling air is directed on to the downstream face of heatshield by means of a plurality of radially extending slots disposed around a fuel nozzle aperture in the centre of each heatshield segment. The slots provide for unrestrained thermal expansion of the heatshield region immediately surrounding the fuel nozzle aperture, thereby to prevent excessive thermal hoop stresses developing in the heatshield during engine operation.