초록 ▼

A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane a

A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane and at least one of the inner and outer bands, wherein a leading edge of the at least one vane is downstream from the leading edges of the inner and outer bands, and coupling the turbine nozzle within the gas turbine engine such that the leading edge fillet is configured to facilitate minimizing vortex formation along the vane leading edge adjacent at least one of the inner and outer bands.

대표청구항 ▼

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising:providing a turbine nozzle including an inner band, an outer band, and a vane extending between the inner and outer bands, each of the inner and outer bands including a radial tab, a forward flange having a l

What is claimed is: 1. A method for assembling a gas turbine engine, said method comprising:providing a turbine nozzle including an inner band, an outer band, and a vane extending between the inner and outer bands, each of the inner and outer bands including a radial tab, a forward flange having a leading edge, and an upstream portion that extends downstream from the forward flange to the radial tab such that a retention channel is defined between the forward flange and the radial tab, the retention channel sized to receive a retainer, wherein a radially outer surface of the inner band upstream portion curves inwardly towards the inner band leading edge and wherein a radially inner surface of the outer band upstream portion curves outwardly towards the outer band leading edge; the turbine nozzle including; a first leading edge fillet between the vane and the outer band structured to substantially blend with the radially inner surface of the outer band upstream portion, a second leading edge fillet between the vane and the inner band structured to substantially blend with the radially outer surface of the inner band upstream portion, and an opening extending through each of the first and second leading edge fillets, wherein the opening is oriented to discharge cooling air towards a pitch-line of the vane; andcoupling the turbine nozzle within the gas turbine engine such that the first and second leading edge fillets facilitate minimizing vortex formation near the vane and adjacent the inner and outer bands, wherein coupling the turbine nozzle within the gas turbine engine includes positioning a retainer at least partially within the retention channel.