A turbofan engine comprising: a fan driven by a low pressure turbine, and a compressor following said fan and driven by a high pressure turbine preceding said low pressure turbine in counter rotation therewith; said low pressure turbine including a turbine stator nozzle (58,82) comprising: a row of vanes joined at opposite ends to outer and inner bands (62,64); each of said vanes having a concave pressure side and circumferentially opposite, convex suction side extending radially in span between said bands (62,64) and axially in chord between opposite leading and trailing edges (78,80); said inner band being inclined radially outwardly in a downstream direction between said leading and trailing edges (78,80) and said outer band being correspondingly inclined radially outwardly in the downstream direction more than said inner band, with said vanes having camber for turning combustion gases between said leading and trailing edges, and also having an acute exit angle relative to an axial centerline axis of said engine for imparting swirl in said combustion gases discharged at said trailing edges; and characterized in that said trailing edges are tilted axially forwardly from said inner band to correspondingly effect oblique lean at a junction of said titled trailing edge with said outer band, wherein an axial width of said vanes at said outer band is equal to an axial width of said vanes at said inner band. a fan driven by a low pressure turbine, and a compressor following said fan and driven by a high pressure turbine preceding said low pressure turbine in counter rotation therewith; said low pressure turbine including a turbine stator nozzle (58,82) comprising: a row of vanes joined at opposite ends to outer and inner bands (62,64); each of said vanes having a concave pressure side and circumferentially opposite, convex suction side extending radially in span between said bands (62,64) and axially in chord between opposite leading and trailing edges (78,80); said inner band being inclined radially outwardly in a downstream direction between said leading and trailing edges (78,80) and said outer band being correspondingly inclined radially outwardly in the downstream direction more than said inner band, with said vanes having camber for turning combustion gases between said leading and trailing edges, and also having an acute exit angle relative to an axial centerline axis of said engine for imparting swirl in said combustion gases discharged at said trailing edges; and characterized in that said trailing edges are tilted axially forwardly from said inner band to correspondingly effect oblique lean at a junction of said titled trailing edge with said outer band, wherein an axial width of said vanes at said outer band is equal to an axial width of said vanes at said inner band. a row of vanes joined at opposite ends to outer and inner bands (62,64); each of said vanes having a concave pressure side and circumferentially opposite, convex suction side extending radially in span between said bands (62,64) and axially in chord between opposite leading and trailing edges (78,80); said inner band being inclined radially outwardly in a downstream direction between said leading and trailing edges (78,80) and said outer band being correspondingly inclined radially outwardly in the downstream direction more than said inner band, with said vanes having camber for turning combustion gases between said leading and trailing edges, and also having an acute exit angle relative to an axial centerline axis of said engine for imparting swirl in said combustion gases discharged at said trailing edges; and characterized in that said trailing edges are tilted axially forwardly from said inner band to correspondingly effect oblique lean at a junction of said titled trailing edge with said outer band, wherein an axial width of said vanes at said outer band is equal to an axial width of said vanes at said inner band.