F - Mech Eng,Light,Heat,Weapons – 02 – C
Patent
F - Mech Eng,Light,Heat,Weapons
02
C
F02C 9/16 (2006.01) F01D 5/18 (2006.01) F01D 9/02 (2006.01)
Patent
CA 2118557
A turbine nozzle assembly comprises an annular array of nozzle guide vanes (24) located downstream of a combustor discharge casing (40). Each nozzle guide vane (24) comprises an aerofoil portion (25) which is cast integrally with a radially inner platform (26) and a radially outer platform (30). The radially outer platform (30) of each nozzle guide vane (24) has an extension (34) to provide a smooth transition of the gases from the combustor discharge casing (40) to the nozzle guide vanes (24). Two rows of cooling holes (38) are provided in the extension (34) to film cool inner surface (31) of the platform (30). A method is described to calculate the diameter of each of the cooling holes (38) so that a uniform flow of cooling air passes over the inner surface (31) of the platform (30).
Gowling Lafleur Henderson Llp
Rolls-Royce Plc
LandOfFree
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