Non axis-symmetric stator vane endwall contour
AssigneeUnited Technologies Corporation
InventorsBrian Green, Sean Nolan
Life of this patent
Estimating the term…
Abstract
An airfoil comprises pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, defining a mean span therebetween. An inner endwall defines an inner endwall contour extending axially and circumferentially from the root section, and an outer endwall defines an outer endwall contour extending axially and circumferentially from the tip section. The inner and outer endwall contours are defined by varying radial deviations from circumferentially uniform nominal inner and outer radii, where one of the radial deviations varies axially and circumferentially by at least three percent of a mean span of the airfoil.
Claims25
An airfoil comprising:
- pressure and suction surfaces extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, the root and tip sections defining a mean span therebetween;
- an inner platform defining an inner endwall contour extending circumferentially from the root section, the inner endwall contour defined by varying radial deviations from a circumferentially uniform inner radius;
- and
- an outer platform defining an outer endwall contour extending axially and circumferentially from the tip section, the outer endwall contour defined by varying radial deviations from a circumferentially uniform outer radius;
- wherein the radial deviations of at least one of the inner and outer endwall contours vary axially and circumferentially by at least three percent of a mean span of the airfoil.
A vane comprising:
- an airfoil portion having pressure and suction surfaces extending in an axial direction from a leading edge to a trailing edge, the leading and trailing edges extending in a radial direction from a root section to a tip section and defining a mean span therebetween;
- an inner endwall extending in axial and circumferential directions adjacent the root section of the airfoil portion, the inner endwall having a non axis-symmetric contour defined by varying radial deviations from a circumferentially uniform nominal inner radius;
- and
- an outer endwall extending in axial and circumferential directions adjacent the tip section of the airfoil portion, the outer endwall having a non axis-symmetric contour defined by varying radial deviations from a circumferentially uniform nominal outer radius;
- wherein the radial deviations of the inner endwall and the outer endwall vary by at least three percent of the mean span along the axial and circumferential directions.
A stator row comprising:
- a plurality of airfoils disposed circumferentially about an axis, each of the airfoils having a pressure surface and a suction surface extending axially from a leading edge to a trailing edge and radially from a root section to a tip section, the root section and the tip section defining a mean span therebetween;
- an inner endwall extending axially and circumferentially between the airfoils adjacent the root sections, the inner endwall having a non axis-symmetric contour defined by a varying radial deviation from a circumferentially uniform nominal inner radius;
- and
- an outer endwall extending axially and circumferentially between the airfoils adjacent the tip section, the outer endwall having a non axis-symmetric contour defined by a varying radial deviation from a circumferentially uniform nominal outer radius;
- wherein the radial deviations of the inner endwall and the outer endwall each vary both axially and radially by at least three percent of the mean span.
Dependencies are inferred from the claim text.