Airfoil assembly with paired endwall contouring
An airfoil assembly is disclosed. The airfoil assembly may comprise a series of airfoils such as vanes radially extending between an ID endwall and a substantially concentric OD endwall. The airfoils are circumferentially spaced apart and define a plurality of fluid flow passages between adjacent airfoils. The ID endwall and the OD endwall define contoured regions to optimize fluid flow through the passages. A geometric relationship between the ID endwall contoured regions and the OD endwall contoured regions assures that the throat area generally increases or decreases in the direction of fluid flow.
1. An airfoil assembly comprising:
an ID endwall having a surface;
an OD endwall having a surface, the ID endwall and the OD endwall being concentric about a center line; and
a pair of airfoils projecting radially outward from the ID endwall and terminating at the OD endwall, each airfoil having a leading edge, a trailing edge and a first side and an opposite second side extending substantially axially between the leading edge and the trailing edge, the airfoils being circumferentially spaced apart;
wherein the ID endwall, the OD endwall and the airfoils define a fluid flow passage; and
wherein the surfaces of the ID endwall and the OD endwall define at least one of a contoured region, the contoured region having more than two profiled regions.
2. The airfoil assembly of claim 1 wherein:
the ID endwall surface defines at least one of a convex profiled region and a concave profiled region.
3. The airfoil assembly of claim 1 wherein:
the OD endwall surface defines at least one of a convex profiled region and a concave profiled region.
4. The airfoil assembly of claim 1 wherein:
the ID endwall surface defines at least one of a convex profiled region and a concave profiled region; and
the OD endwall surface defines at least one of a convex profiled region and a concave profiled region.
5. The airfoil assembly of claim 1 wherein:
the ID endwall surface defines a convex profiled region and a concave profiled region; and
the OD endwall surface defines a convex profiled region and a concave profiled region.
6. The airfoil assembly of claim 5 wherein:
the convex profiled region on the ID endwall is adjacent to the first side and the concave profiled region on the ID endwall is adjacent to the second side; and
the convex profiled region on the OD endwall is adjacent to the first side and the concave profiled region on the OD endwall is adjacent to the second side.
7. The airfoil assembly of claim 6 wherein:
the first side of each airfoil is a pressure side; and
the second side of each airfoil is a suction side.
8. The airfoil assembly of claim 1 wherein:
each fluid flow passage defines a throat area; and
the throat area varies in an axial direction.
9. The airfoil assembly of claim 8 wherein:
the airfoil assembly is part of a turbine vane assembly or a mid-turbine frame assembly;
fluid may flow through the fluid flow passage in a direction of fluid flow defined generally as the direction from the leading edges to the trailing edges; and
the throat area does not decrease in the direction of fluid flow.
10. The airfoil assembly of claim 8 wherein:
the airfoil assembly is part of a compressor vane assembly;
fluid may flow through the fluid flow passage in a direction of fluid flow defined generally as the direction from the leading edges to the trailing edges; and
the throat area does not increase in the direction of fluid flow.
11. The airfoil assembly of claim 1 wherein the airfoils are turbine vanes.
12. The airfoil assembly of claim 1 wherein the airfoils are compressor stator vanes.
13. The airfoil assembly of claim 1 wherein the airfoils are MTF vanes.
14. The airfoil assembly of claim 1 wherein the airfoils are fan exit guide vanes.
15. A vane assembly comprising:
an ID endwall having a radially outward facing surface, the radially outward facing surface defining a first contoured region;
an OD endwall substantially concentric with the ID endwall and having a radially inward facing surface, the radially inward facing surface defining a second contoured region;
a pair of vanes extending between the ID endwall and the OD endwall, each vane being generally airfoil shaped and having a first side and an opposite second side extending axially between a leading edge and a trailing edge, the vanes being circumferentially spaced apart between the ID endwall and the OD endwall, the vanes and endwalls defining an air flow passage; and
the first contoured region on the ID endwall having more than two profiled regions; and
the second contoured region of the OD endwall having more than two profiled regions.
16. The vane assembly of claim 15 wherein:
there is a geometric relationship between the first contoured region and the second contoured region.
17. The vane assembly of claim 15 wherein:
the ID endwall has an upstream edge;
the OD endwall has an upstream edge;
the contoured region defined by the ID endwall is located downstream of the upstream edge of the ID endwall; and
the contoured region defined by the OD endwall is located downstream of the upstream edge of the OD endwall.
18. A method of improving fluid dynamics within a gas turbine engine, the method comprising the steps of:
providing an airfoil assembly comprising a pair of airfoils extending between opposing endwalls, the airfoils and endwalls defining a fluid flow passage;
moving fluid through a fluid flow passage;
influencing the general flow of the fluid through the fluid flow passage by providing at least one of a contoured region on both endwalls; and
the contoured region on both endwalls defining more than two profiled regions.
19. The method of claim 18 wherein:
at least one of the contoured regions comprises a convex profiled region.
20. The method of claim 18 wherein:
at least one of the contoured regions comprises a concave profiled region.
21. The method of claim 18 wherein:
each contoured region comprises a convex profiled region and a concave profiled region.