Rolls-royce Corporation

Michael J Westlake

Samuel M Sampson

Donald E Pearce

Ian A Mitchell

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.

Exhaust nozzle for a gas turbine engine

A combustor for a gas turbine engine comprising a combustion chamber wall having formed therein at least one hole for admitting air into the combustion chamber and at least one air intake chute aligned with said hole. The air intake chutes are attached to the combustor wall in regions which, during operation, will be regions of low stress concentration.

Gas turbine engine combustor

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.

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Gloucestershire, United Kingdom

Michael J Westlake