Abstract: A combustion chamber assembly includes a combustion chamber casing, a combustion chamber, a plurality of fuel injectors and respective seals. The axis of each fuel injector head is arranged at an angle to the axis of the combustion chamber casing and parallel to the center line of the combustion chamber. Each seal is positioned between a fuel injector head and an aperture in an upstream wall of the combustion chamber. Each seal has an aperture extending through the seal which is arranged parallel to the axis of the combustion chamber casing or the flange of the fuel injector. Each fuel injector head has a part spherical surface located in a seal. The assembly provides a clearance required to engage, or disengage, a fuel injector head while minimizing the amount of material removed from the between the apertures in the upstream wall of the combustion chamber.

Abstract: A gas turbine engine comprises a compressor, a combustion chamber, an outer casing, an inner casing and a cooling arrangement. The outer casing surrounds the compressor and the combustion chamber and the combustion chamber has turbine nozzle guide vanes. The compressor has load carrying outlet guide vanes connected to the outer casing and the inner casing. The turbine nozzle guide vanes connect the outer casing and the inner casing. The cooling arrangement comprises a cooling air duct located between the compressor and the combustion chamber. The compressor outlet guide vanes carry at least one aerodynamic fairing. A support structure supports the cooling air duct from the inner casing at two spaced positions and the support structure forms a chamber with the inner casing. The support structure comprises at least one hollow duct and each hollow duct locates behind a respective one of the aerodynamic fairings.

Abstract: A combustion chamber assembly includes a combustion chamber casing, a combustion chamber, a plurality of fuel injectors and respective seals. The axis of each fuel injector head is arranged at an angle to the axis of the combustion chamber casing and parallel to the centre line of the combustion chamber. Each seal is positioned between a fuel injector head and an aperture in an upstream wall of the combustion chamber. Each seal has an aperture extending through the seal which is arranged parallel to the axis of the combustion chamber casing or the flange of the fuel injector. Each fuel injector head has a part spherical surface located in a seal. The assembly provides a clearance required to engage, or disengage, a fuel injector head whilst minimising the amount of material removed from the between the apertures in the upstream wall of the combustion chamber.

Abstract: A gas turbine engine comprises a compressor, a combustion chamber, an outer casing, an inner casing and a cooling arrangement. The outer casing surrounds the compressor and the combustion chamber and the combustion chamber has turbine nozzle guide vanes. The compressor has load carrying outlet guide vanes connected to the outer casing and the inner casing. The turbine nozzle guide vanes connect the outer casing and the inner casing. The cooling arrangement comprises a cooling air duct located between the compressor and the combustion chamber. The compressor outlet guide vanes carry at least one aerodynamic fairing. A support structure supports the cooling air duct from the inner casing at two spaced positions and the support structure forms a chamber with the inner casing. The support structure comprises at least one hollow duct and each hollow duct locates behind a respective one of the aerodynamic fairings.

Abstract: Within such machines as gas turbine engines it is desirable to provide close association between rotating assemblies and a rotor path arrangement to reduce leakage. However, such arrangements of rotor assemblies and rotor path arrangements are subject to thermal cycling and differentials between the respective parts can lead to rub associations. In order to allow closer thermal responses between the respective rotor path arrangement and rotor assembly, a flexible assembly is provided for a liner. A face surface is presented upon a backer plate or floating ring such that the thermal response can be tuned to the reciprocal similar effects under the same conditions of the rotor assembly. In such circumstances, closer gap control can be achieved. Furthermore, rather than requiring an entire integral casing to be overhauled, generally only the face surfaces and/or the flexible assembly will require remedial action.

Abstract: Within such machines as gas turbine engines it is desirable to provide close association between rotating assemblies and a rotor path arrangement to reduce leakage. However, such arrangements of rotor assemblies and rotor path arrangements are subject to thermal cycling and differentials between the respective parts can lead to rub associations. In order to allow closer thermal responses between the respective rotor path arrangement and rotor assembly, a flexible assembly (8, 9, 10, 100) is provided for a liner (6). A face surface (5, 103) is presented upon a backer plate (10) or floating ring (101) such that the thermal response can be tuned to the reciprocal similar effects under the same conditions of the rotor assembly. In such circumstances, closer gap (111) control can be achieved. Furthermore, rather than requiring an entire integral casing to be overhauled, generally only the face surfaces (5, 108) and/or the flexible assembly will require remedial action.