Inboard cooled nozzle doublet

Details Inboard cooled nozzle doublet Inboard cooled nozzle doublet

F - Mech Eng,Light,Heat,Weapons

02

K

F02K 1/40 (2006.01) F01D 5/18 (2006.01) F01D 5/28 (2006.01) F01D 9/04 (2006.01)

Patent

CA 2489627

A turbine nozzle (16) includes outer and inner bands (18,20) integrally joined to a doublet of hollow vanes (22,24) extending radially therebetween. Each of the vanes includes opposite pressure and suction sidewalk (28-34) extending between opposite leading and trailing edges (36,38), and spaced apart to define an internal plenum (40) extending radially between the bands for receiving an air coolant (12). The vanes are spaced apart from each other to define a flow passage (42) for channeling hot combustion gases (14) which are bound by corresponding pressure and suction sidewalls (28,34) of the vanes facing inboard toward each other, with the remaining suction and pressure sidewalls (30,32) of the vanes facing outboard. The vanes include different cooling configurations to bias more of the coolant to the inboard sidewalls (28,34) than to the outboard sidewalls (30,32).

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