Cantilevered nozzle with crowned flange to improve outer band low cycle fatigue

1. A flange for supporting arcuate components comprising at least one arcuate rail, each arcuate rail having an inner radius, a first end, a second end located at a circumferential distance from the first end, a first taper location located at a first taper distance from the first end, a first taper region located between the first end and the first taper location, a second taper location located at a second taper distance from the second end, a second taper region located between the second end and the second taper location, wherein the thickness of at least a portion of the first taper region is tapered between the first taper location and the first end and wherein the thickness of at least a portion of the second taper region is tapered between the second taper location and the second end.

2. A flange according to claim 1 wherein the thickness of the flange between the first taper point and the second taper point is substantially constant.

3. A flange according to claim 1 wherein the first taper distance and the second taper distance are substantially equal.

4. A flange according to claim 3 wherein the first taper distance and the second taper distance are substantially equal to half of the circumferential distance between the first end and the second end.

5. An outer band for a turbine nozzle comprising:

a forward arcuate rail, an aft arcuate rail located axially aft from the forward arcuate rail, the forward arcuate rail having an inner radius, a first end, a second end located at a circumferential distance from the first end, a first taper location located at a first taper distance from the first end, a first taper region located between the first end and the first taper location, a second taper location located at a second taper distance from the second end, a second taper region located between the second end and the second taper location, wherein the thickness of at least a portion of the first taper region is tapered between the first taper location and the first end and wherein the thickness of at least a portion of the second taper region is tapered between the second taper location and the second end.

6. An outer band according to claim 5 wherein the thickness of the flange between the first taper point and the second taper point is substantially constant.

7. An outer band according to claim 5 wherein the first taper distance and the second taper distance are substantially equal.

8. An outer band according to claim 7 wherein the first taper distance and the second taper distance are substantially equal to half of the circumferential distance between the first end and the second end.

9. An outer band for a turbine nozzle comprising:

a forward arcuate rail, an aft arcuate rail located axially aft from the forward arcuate rail, the aft arcuate rail having an inner radius, a first end, a second end located at a circumferential distance from the first end, a first taper location located at a first taper distance from the first end, a first taper region located between the first end and the first taper location, a second taper location located at a second taper distance from the second end, a second taper region located between the second end and the second taper location, wherein the thickness of at least a portion of the first taper region is tapered between the first taper location and the first end and wherein the thickness of at least a portion of the second taper region is tapered between the second taper location and the second end.

10. An outer band according to claim 9 wherein the thickness of the flange between the first taper point and the second taper point is substantially constant.

11. An outer band according to claim 9 wherein the first taper distance and the second taper distance are substantially equal.

12. An outer band according to claim 11 wherein the first taper distance and the second taper distance are substantially equal to half of the circumferential distance between the first end and the second end.

13. A turbine nozzle segment comprising:

at least one airfoil extending radially between an outer band and an inner band, the outer band having a forward arcuate rail, an aft arcuate rail located axially aft from the forward arcuate rail, the forward arcuate rail having an inner radius, a first end, a second end located at a circumferential distance from the first end, a first taper location located at a first taper distance from the first end, a first taper region located between the first end and the first taper location, a second taper location located at a second taper distance from the second end, a second taper region located between the second end and the second taper location, wherein the thickness of at least a portion of the first taper region is tapered between the first taper location and the first end and wherein the thickness of at least a portion of the second taper region is tapered between the second taper location and the second end.

14. A turbine nozzle segment according to claim 13 wherein the thickness of the flange between the first taper point and the second taper point is substantially constant.

15. A turbine nozzle segment according to claim 13 wherein the first taper distance and the second taper distance are substantially equal.

16. A turbine nozzle segment according to claim 15 wherein the first taper distance and the second taper distance are substantially equal to half of the circumferential distance between the first end and the second end.

17. A turbine nozzle segment comprising:

at least one airfoil extending radially between an outer band and an inner band, the outer band having a forward arcuate rail, an aft arcuate rail located axially aft from the forward arcuate rail, the aft arcuate rail having an inner radius, a first end, a second end located at a circumferential distance from the first end, a first taper location located at a first taper distance from the first end, a first taper region located between the first end and the first taper location, a second taper location located at a second taper distance from the second end, a second taper region located between the second end and the second taper location, wherein the thickness of at least a portion of the first taper region is tapered between the first taper location and the first end and wherein the thickness of at least a portion of the second taper region is tapered between the second taper location and the second end.

18. A turbine nozzle segment according to claim 17 wherein the thickness of the flange between the first taper point and the second taper point is substantially constant.

19. A turbine nozzle segment according to claim 17 wherein the first taper distance and the second taper distance are substantially equal.

20. A turbine nozzle segment according to claim 19 wherein the first taper distance and the second taper distance are substantially equal to half of the circumferential distance between the first end and the second end.