Durable turbine vane

Patent metadata

Field	Value
Publication number	US-9506351-B2
Application number	US-201313852358-A
Country	US
Kind code	B2
Filing date	Mar 28, 2013
Priority date	Apr 27, 2012
Publication date	Nov 29, 2016
Grant date	Nov 29, 2016

Abstract

A durable nozzle vane includes a leading edge where hot combustion gas impinges on the vane, a pressure side extending from the leading edge to a trailing edge and a suction side extending from the leading edge to the trailing edge, a blunt region along the suction side between the leading edge and a high curvature region, the blunt region having small curvature in the length between the leading edge and the high curvature region allowing for at least two rows of cooling apertures.

First claim

We claim:

1. A durable gas turbine vane, comprising:
an inner band, an outer band, and at least one vane extending between the inner and outer bands;
the at least one vane further comprising a leading edge, a trailing edge, a suction side and a pressure side;
the suction side being disposed laterally opposite the pressure side;
wherein the suction side and the pressure side extend between the leading edge to the trailing edge thereby defining a chord-wise airfoil shape for the at least one vane;
the at least one vane being curved along an axial direction;
the suction side including a blunter region and a high curvature region;
the high curvature region spaced from said blunter region;
the blunter region having at least two rows of linear cooling apertures;
the cooling apertures being formed upon and extending into a surface of the blunter region; and,
the apertures extending at an angle θ, wherein θ is within a range of from zero to 40 degrees with respect to the surface of the blunter region.

2. The durable gas turbine vane of claim 1 , the blunter region being flatter than the high curvature region and being located between the leading edge and the high curvature region.

3. The durable gas turbine vane of claim 2 , said blunter region having a flattened distance of reduced curvature.

4. The durable gas turbine vane of claim 1 , said blunter region including three rows of said cooling apertures.

5. The durable gas turbine vane of claim 1 , said blunter region being between 8% and 17% of the surface length of said suction side.

6. The durable gas turbine vane of claim 1 , said blunter region having a minimum nondimensional curvature of 1/radius being 1.25.

7. The durable gas turbine vane of claim 6 , the blunter region between the leading edge and the high curvature region having a flattened distance in conjunction with a radiused high curvature region leading edge, thereby enhancing cooling air film attachment to the vane suction side.

8. A durable turbine nozzle vane, wherein the vane comprises:
a leading edge where hot combustion gas impinges on the nozzle vane;
a pressure side having a concave surface extending between the leading edge to a trailing edge;
a suction side having a convex surface extending between the leading edge to the trailing edge;
the suction side being disposed laterally opposite the pressure side;
the suction side and the pressure side extend between the leading edge to the trailing edge thereby defining a chord-wise airfoil shape for the vane;
a blunter region disposed along the suction side between the leading edge and a high curvature region having at least two rows of linear cooling apertures; and,
the blunter region having a curvature in the length between the leading edge and the high curvature region.

9. The durable gas turbine vane of claim 8 , the blunter region further comprising at least one row of cooling apertures.

10. The durable gas turbine vane of claim 9 wherein the cooling apertures are formed upon and extending into a surface of the blunter region and the apertures extend at an angle θ, wherein θ is within a range of from zero to 40 degrees with respect to the surface of the blunter region.

11. The durable gas turbine vane of claim 10 , the blunter region having a in the range of 8% of the suction side length to 17% of the suction side length.

12. The durable gas turbine vane of claim 11 wherein the minimum nondimensional curvature of the blunter region is less than 1.25.

13. The durable gas turbine vane of claim 12 , the blunter region between the leading edge and the high curvature region having a flattened distance in conjunction with a radiused high curvature region leading edge, thereby enhancing cooling air film attachment to the vane suction side.

Assignees

• Gen Electric

Inventors

• Bubnick Joseph Steven
• Bartz Robert Joseph
• Demers Daniel Edward
• Frederick Robert Alan
• Heffron Todd Stephen
• Molleson Sean Michael

Classifications

• F01D5/186 Primary

  Film cooling (F01D5/187 takes precedence) · CPC title

• Y02T50/673

  Cross-Sectional Technologies · mapped topic

• F05D2240/303

  related to the leading edge of a rotor blade · CPC title

• F05D2260/202

  by film cooling · CPC title

• F01D9/02

  Nozzles; Nozzle boxes; Stator blades; Guide conduits {, e.g. individual nozzles (nozzle boxes F01D9/047)} · CPC title