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US 5,509,270 AGranted
Gas turbine engine combustor heatshield
AssigneeROLLS-ROYCE plc
InventorsDonald E. Pearce, Michael J. Westlake
Life of this patent
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AssigneeROLLS-ROYCE plc
InventorsDonald E. Pearce, Michael J. Westlake
Estimating the term…
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.
A combustor for a gas turbine engine comprising a cylindrical radial inner wall, a cylindrical radial outer wall, an upstream bulkhead wall extending between said inner and outer walls, and an internal heatshield located on a downstream face of said upstream bulkhead wall and spaced therefrom to create a passageway for cooling air, each of the internal heatshield and the upstream bulkhead wall being formed with a fuel nozzle aperture therethrough,
A heatshield for a combustor for a gas turbine engine comprising a cylindrical radial inner wall, a cylindrical radial outer wall, an upstream bulkhead wall extending between said inner and outer walls, and an internal heatshield located on a downstream face of said upstream bulkhead wall, said internal heatshield being spaced from the upstream bulkhead wall to create a passageway for cooling air,
Dependencies are inferred from the claim text.