Combustor apparatus
AssigneeROLLS-ROYCE plc
InventorStephen C. HARDING
Life of this patent
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Abstract
An integral guide vane combustor assembly for a gas turbine engine comprises an annular array of radially extending guide vane combustors. The gas turbine engine comprises, in axial flow sequence, a compressor assembly, the integral guide vane combustor assembly, a turbine assembly, and an exhaust assembly. Each of the guide vane combustors comprises, in axial flow sequence, a guide vane portion, and a combustor body portion. The guide vane portion is formed integrally with the combustor body portion, and the guide vane portion is configured to direct a gas flow exiting the compressor assembly into the combustor body portion.
Claims10
An integral guide vane combustor assembly for a gas turbine engine, the gas turbine engine comprising, in axial flow sequence, a compressor assembly, the integral guide vane combustor assembly, a turbine assembly, and an exhaust assembly, the integral guide vane combustor assembly comprising an annular array of radially extending guide vane combustors;
- wherein each guide vane combustor comprises, in axial flow sequence, a guide vane portion, and a combustor body portion, the guide vane portion being formed integrally with the combustor body portion, and the guide vane portion being configured to direct a gas flow exiting the compressor assembly into the combustor body portion.
Dependencies are inferred from the claim text.