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A turbine apparatus includes: A first nozzle comprising an array of first vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; A rotor downstream from the first nozzle comprising a plurality of blades carried by a rotatable disk; and a second nozzle di

A turbine apparatus includes: A first nozzle comprising an array of first vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; A rotor downstream from the first nozzle comprising a plurality of blades carried by a rotatable disk; and a second nozzle disposed downstream from the rotor comprising an array of second vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; wherein the first and second vanes of the first and second nozzles are circumferentially clocked relative to each other such that, in a predetermined operating condition, wakes discharged from the first vanes are aligned in a circumferential direction with the leading edges of the second vanes, wherein a stacking axis of the first vanes is nonlinear. An inner band of the first nozzle is contoured in a non-axisymmetric shape.

대표청구항 ▼

1. A turbine apparatus, comprising: a first nozzle comprising an array of first vanes disposed between an annular inner band and an annular outer band, each of the first vanes including: a root, a tip, a concave pressure side and a laterally opposite convex suction side extending in chord between op

1. A turbine apparatus, comprising: a first nozzle comprising an array of first vanes disposed between an annular inner band and an annular outer band, each of the first vanes including: a root, a tip, a concave pressure side and a laterally opposite convex suction side extending in chord between opposite leading and trailing edges, the first vanes arranged so as to define a plurality of first flow passages therebetween bounded in part by the inner band, wherein a surface of the inner band is contoured in a non-axisymmetric shape;a rotor disposed downstream from the first nozzle and comprising a plurality of blades carried by a rotatable disk, each blade including an airfoil having a root, a tip, a concave pressure side, and a laterally opposite convex suction side, the pressure side and the suction side extending in chord between opposite leading and trailing edges; anda second nozzle disposed downstream from the rotor comprising an array of second vanes disposed between an annular inner band and an annular outer band, each of the second vanes including a concave pressure side and a laterally opposite convex suction side extending in chord between opposite leading and trailing edges, the second vanes arranged so as to define a plurality of second flow passages therebetween;wherein the first vanes of the first nozzle and the second vanes of the second nozzle are circumferentially clocked relative to each other such that, in a predetermined operating condition, wakes discharged from the first vanes are aligned in a circumferential direction with the leading edges of the second vanes, wherein a stacking axis of the first vanes is nonlinear such that a plurality of cross-sectional stations spaced-apart along the stacking axis are progressively shifted in a tangential direction to a greater degree from the root of the first vanes to the tip of the first vanes. 2. The turbine apparatus of claim 1 wherein the first nozzle and the second nozzle include an equal number of vanes. 3. The turbine apparatus of claim 1 wherein the plurality of cross-sectional stations spaced-apart along the stacking axis of the first vanes are each positioned such that, in a predetermined operating condition, wakes discharged therefrom are circumferentially aligned with the leading edges of corresponding cross-sectional stations spaced-apart along the second vanes. 4. The turbine assembly of claim 1 wherein each of the turbine blades comprises: an outer platform disposed at the tip of the airfoil, and an inner platform disposed at the root of the airfoil, the inner platform having a hot side facing the airfoil which is contoured in a non-axisymmetric shape. 5. The turbine assembly of claim 4 wherein the hot side sides of each of the inner platforms is contoured in a non-axisymmetric shape including a peak of relatively higher radial height adjoining the pressure side of one of the airfoils adjacent its leading edge, and a trough of relatively lower radial height is disposed parallel to and spaced-away from the suction side of an adjacent airfoil aft of the leading edge of one of the airfoils; and wherein the peak and the trough define cooperatively define an arcuate channel extending axially along the inner platform. 6. The turbine assembly of claim 5 wherein the peak decreases in height around the leading edge of the one of the airfoils to join the trough along the suction side of the adjacent airfoil; and the trough extends along the suction side of the adjacent airfoil to the trailing edge of the adjacent airfoil. 7. The turbine assembly of claim 5 wherein the hot side of each inner platform includes a trailing edge ridge of relatively higher radial height extending aft of the trailing edge of the airfoil. 8. The turbine blade assembly of claim 5 wherein the peak is centered at the pressure side of each airfoil between the leading edge and a mid-chord position, and decreases in height forward, aft, and laterally therefrom; and the trough is centered at the suction side near the maximum thickness of the airfoil, and decreases in depth forward, aft, and laterally therefrom. 9. The turbine blade assembly of claim 1 wherein a surface of the inner band in each of the first passages is contoured in a non-axisymmetric shape including a peak of relatively higher radial height adjoining the pressure side of one of the first vanes adjacent its leading edge, and a trough of relatively lower radial height disposed parallel to and spaced-away from the suction side of an adjacent first vane aft of its leading edge; and wherein the peak and trough define cooperatively define an arcuate channel extending axially along the inner band between the adjacent first vanes. 10. The turbine blade assembly of claim 9 wherein the peak disposed in each first passage decreases in height around each the leading edge of one of the first vanes to join the trough along the suction side of the adjacent first vane; and the trough extends along the suction sides of the adjacent first vane to its trailing edge. 11. The turbine assembly of claim 1 wherein the peak is centered at the pressure side of each first vane between the leading edge and a mid-chord position, and decreases in height forward, aft, and laterally therefrom; and the trough is centered at the suction side near the maximum thickness of the airfoils, and decreases in depth forward, aft, and laterally therefrom. 12. The turbine apparatus of claim 1 further including at least one additional stage positioned upstream or downstream therefrom, the additional stage including: an additional nozzle comprising an array of vanes disposed between an annular inner band and an annular outer band, each of the vanes including a concave pressure side and a laterally opposite convex suction side extending in chord between opposite leading and trailing edges, the vanes arranged so as to define a plurality of flow passages therebetween; andan additional rotor disposed downstream from the additional nozzle and comprising a plurality of blades carried by a rotatable disk, each blade including an airfoil having a root, a tip, a concave pressure side, and a laterally opposite convex suction side, the pressure and suction sides extending in chord between opposite leading and trailing edges.