Claims
- 1. A turbine nozzle comprising:an outer band; an inner band; a plurality of vanes extending between said outer and inner bands; each of said vanes including leading and trailing edges, and pressure and suction sides extending therebetween, and also including a bow along said trailing edge; and each of said vanes also including a thermal barrier coating selectively disposed along at least a portion of said suction side with said pressure side being devoid of said coating.
- 2. A nozzle according to claim 1 wherein:adjacent ones of said vanes are spaced apart circumferentially to define a throat of minimal flow area therebetween having a first boundary along said pressure side at said trailing edge of one of said vanes, and a second boundary along said suction side adjacent said leading edge of a second one of said vanes; and both said first and second throat boundaries are devoid of said coating.
- 3. A nozzle according to claim 2 wherein:said vanes are hollow and include impingement baffles therein for channelling cooling air in impingement inside said vanes for impingement cooling both said pressure and suction sides thereof; and said coating is sized in thickness along said suction side to reduce differential thermal movement between said pressure and suction sides adjacent said vane bow.
- 4. A nozzle according to claim 3 wherein said vane bow is radially convex between said outer and inner bands along said pressure side, and radially concave along said suction side having said coating thereon.
- 5. A nozzle according to claim 4 wherein:said vane has maximum curvature at said trailing edge, and decreases in curvature toward said leading edge; and said coating decreases in thickness from said trailing edge toward said second throat boundary.
- 6. A nozzle according to claim 5 wherein said vane bow is disposed nearer said inner band than said outer band.
- 7. A nozzle according to claim 5 wherein each of said vanes twists about said leading edge from said inner band to said outer band to define said bow.
- 8. A nozzle according to claim 5 wherein each of said vanes leans along said trailing edge to define said bow.
- 9. A nozzle according to claim 5 wherein each of said vanes twists about said leading edge from said inner band to said outer band, and leans along said trailing edge to define said bow.
- 10. A nozzle according to claim 9 wherein said bow is configured to increase momentum of said combustion gases adjacent said inner band.
Parent Case Info
This application is a division of Ser. No. 09/136,834 filed Aug. 20, 1998 now U.S. Pat. No. 6,077,036.
US Referenced Citations (7)
Foreign Referenced Citations (3)
Number |
Date |
Country |
63295803 |
Dec 1988 |
JP |
7127401 |
May 1995 |
JP |
7278780 |
Oct 1995 |
JP |