Methods and apparatus for assembling turbine engines

Details Methods and apparatus for assembling turbine engines Methods and apparatus for assembling turbine engines

F - Mech Eng,Light,Heat,Weapons

01

D

F01D 9/02 (2006.01) F23R 3/02 (2006.01)

Patent

CA 2570633

A turbine engine nozzle assembly includes an outer band (54) including a leading edge (70), a trailing edge (74), and a body (78) extending therebetween; an inner band (56) including a leading edge (72), a trailing edge (76), and a body (80) extending therebetween; and at least one vane (52) extending between the outer and inner bands including a first sidewall (60) and a second sidewall (62) connected together at a leading edge (64) and a trailing edge (66), the at least one vane leading edge (64) being positioned downstream from the inner and outer band leading edges. The turbine engine nozzle assembly further includes a leading edge fillet (170) extending between the at least one vane and at least one of the inner band and the outer band configured to minimizing vortex formation along the vane leading edge adjacent at least one of the inner and outer bands.

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