Rolls-royce Corporation

David H Taylor

Arthur B Griffin

David W Tuson

Ian W Harrogate

Michael R Lyons

A cooling and sealing arrangement in a gas turbine engine comprises a seal assembly extending between nozzle guide vanes and combustion chamber discharge nozzles. The nozzle guide vanes have platforms having extensions which in one embodiment overlap the downstream ends of the discharge nozzles. Cooling air is supplied to the upstream edge portions of the platforms through holes in flanges on the discharge nozzles. The seal assembly defines a chamber adjacent the platform extensions which is supplied with cooling air through metering holes in the seal assembly which provides part of a boundary for a cooling air chamber, the boundary of the chamber having cooling air holes for metering cooling air into the chamber to cool the upstream portion of the nozzle guide vane outer platforms. Cooling air exits the chamber through holes in the platform extensions to film cool them.

Sealing structures for gas turbine engines

A cooling and sealing arrangement in a gas turbine engine comprises a seal assembly (42,30) extending between nozzle guide vanes (20) and combustion chamber discharge nozzles (22). The nozzle guide vanes (20) have platforms (34,36) having extensions (34A,36A) which in one embodiment overlap the downstream ends of the discharge nozzles (22). Cooling air is supplied to the upstream edge portions of the platforms through holes (26,28C) in flanges (24,28) on the discharge nozzles (22). The seal assembly (42,30) defines a chamber (58,70) adjacent the platform extensions which is supplied with cooling air through metering holes (56,68) in the seal assembly. Cooling air exits the chamber (58,70) through holes (34B,36B) in the platform extensions to film cool them.

A gas turbine engine component support assembly (30) comprises a pair of ring members (64) and (74) defining a slot in which a cranked flange (28) extending from the inner surfaces of an array of combustion chamber discharge nozzles (22) is located. One part (28B) of the cranked flange has projections (28C) which engage with radial slots (76) formed in one of the ring members (74) to provide cross-key location of the discharge nozzles. The support assembly (30) is located adjacent the radially inner platform of an array of nozzle guide vanes (20), and also provides support and location for the vanes.

Gas turbine engines

Combustion chamber assembly with hollow support strut for carrying

A gas turbine engine fuel system comprises a main fuel manifold and starter fuel manifold which direct fuel into the combustion apparatus of a gas turbine engine. During normal engine operation, fuel flow to the starter manifold is prevented by a solenoid valve. Air from within the combustion apparatus then flows back through the starter manifold and into a fuel drains system of the engine to purge the starter manifold of fuel. This purging of fuel in the starter manifold engine operation prevents the undesirable leakage of fuel into the combustion apparatus from the starter manifold.

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Warwickshire, United Kingdom

David H Taylor