Rolls-royce Corporation

Ian W Harrogate

Arthur B Griffin

David H Taylor

David W Tuson

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 turbine nozzle assembly includes an annular array of nozzle guide vanes located downstream of a combustor discharge casing. Each nozzle guide vane includes an aerofoil portion which is cast integrally with a radially inner platform and a radially outer platform. The radially outer platform of each nozzle guide vane has an extension to provide a smooth transition of the gases from the combustor discharge casing to the nozzle guide vanes. Two rows of cooling holes are provided in the extension to film cool the inner surface of the platform. A method is described to calculate the diameter of each of the cooling holes so that a uniform flow of cooling air passes over the inner surface of the each platform.

Cooled turbine nozzle assembly and a method of calculating the diameters

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.

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Derby, United Kingdom

Ian W Harrogate