Methods and apparatus for assembling turbine engines

F - Mech Eng,Light,Heat,Weapons – 01 – D

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

Patent

CA 2570631

A turbine engine nozzle assembly (50) 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 (78) 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 (50) further includes a retention system to couple the nozzle to an engine combustor that includes a first annular ring (290) coupled between the outer band and the combustor, and a second annular ring (291) coupled between the inner band and the combustor.

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