A turbine engine nozzle assembly comprising: an outer band comprising a leading edge, a trailing edge, and a body extending therebetween; the outer band further comprising a plurality of circumferentially spaced outer band radial tabs extending radially outwardly from the outer band and an outer band forward flange extending radially outwardly from the outer band, the outer band forward flange having an upstream side, the outer band radial tabs spaced downstream from the outer band forward flange such that an outer band retention channel is defined between each outer band radial tab and the outer band forward flange, each of the outer band retention channels sized to receive an outer-band retainer for coupling the nozzle assembly to an aft end of a combustor; an inner band comprising a leading edge, a trailing edge, and a body extending therebetween; the inner band further comprising a plurality of circumferentially-spaced inner band radial tabs extending radially inwardly from the inner band and an inner band forward flange extending radially inwardly from the inner band, the inner band forward flange having an upstream side, the inner band radial tabs spaced downstream from the inner band forward flange such that an inner band retention channel is defined between each inner band radial tab and the inner band forward flange, each of the inner band retention channels sized to receive an inner-band retainer for coupling the nozzle assembly to an aft end of the combustor; at least one vane extending between said outer and inner bands, said at least one vane comprising a first sidewall and a second sidewall connected together at a leading edge and a trailing edge, said at least one vane leading edge positioned downstream from said inner and outer band leading edges; and a first leading edge fillet extending between said at least one vane and said outer band in a tip area of said vane leading edge, wherein said first leading edge fillet is blended from said vane leading edge across a radially inner surface of said outer band towards said outer band leading edge; a second leading edge fillet extending between said at least one vane and said inner band in a hub area of said vane leading edge, wherein said second leading edge fillet is blended from said vane leading edge across a radially outer surface of said inner band towards said inner band leading edge; wherein each of the first and second leading edge fillets comprise a cooling opening extending through the fillet and oriented towards a pitch-line of said vane to thereby, in use, discharge cooling air into a boundary flow flowing over the vane and thereby energise flow momentum in the boundary layer. an outer band comprising a leading edge, a trailing edge, and a body extending therebetween; the outer band further comprising a plurality of circumferentially spaced outer band radial tabs extending radially outwardly from the outer band and an outer band forward flange extending radially outwardly from the outer band, the outer band forward flange having an upstream side, the outer band radial tabs spaced downstream from the outer band forward flange such that an outer band retention channel is defined between each outer band radial tab and the outer band forward flange, each of the outer band retention channels sized to receive an outer-band retainer for coupling the nozzle assembly to an aft end of a combustor; an inner band comprising a leading edge, a trailing edge, and a body extending therebetween; the inner band further comprising a plurality of circumferentially-spaced inner band radial tabs extending radially inwardly from the inner band and an inner band forward flange extending radially inwardly from the inner band, the inner band forward flange having an upstream side, the inner band radial tabs spaced downstream from the inner band forward flange such that an inner band retention channel is defined between each inner band radial tab and the inner band forward flange, each of the inner band retention channels sized to receive an inner-band retainer for coupling the nozzle assembly to an aft end of the combustor; at least one vane extending between said outer and inner bands, said at least one vane comprising a first sidewall and a second sidewall connected together at a leading edge and a trailing edge, said at least one vane leading edge positioned downstream from said inner and outer band leading edges; and a first leading edge fillet extending between said at least one vane and said outer band in a tip area of said vane leading edge, wherein said first leading edge fillet is blended from said vane leading edge across a radially inner surface of said outer band towards said outer band leading edge; a second leading edge fillet extending between said at least one vane and said inner band in a hub area of said vane leading edge, wherein said second leading edge fillet is blended from said vane leading edge across a radially outer surface of said inner band towards said inner band leading edge; wherein each of the first and second leading edge fillets comprise a cooling opening extending through the fillet and oriented towards a pitch-line of said vane to thereby, in use, discharge cooling air into a boundary flow flowing over the vane and thereby energise flow momentum in the boundary layer.