Stator vane assembly and method therefor
A stator vane assembly includes a plurality of distinct vane segments that each respectively include a first platform, a second platform and at least one vane airfoil connected at opposed ends thereof to the first platform and the second platform. The first platforms meet at distinct first joints with each other, and the second platforms meet at distinct second joints with each other such that the plurality of vane segments forms an annular structure.
1. A stator vane assembly comprising:
a plurality of distinct vane segments each respectively including a first platform, a second platform and at least one vane airfoil connected at opposed ends thereof to the first platform and the second platform, the first platforms meeting at distinct first joints with each other and the second platforms meeting at distinct second joints with each other such that the plurality of vane segments form an annular structure, wherein at least the distinct first joints run parallel to a line that is tangent to a leading edge fillet and a trailing edge fillet on a pressure side of the at least one vane airfoil.
2. The assembly as recited in claim 1 , wherein the distinct first joints and the distinct second joints include surface discontinuities.
3. The assembly as recited in claim 1 , wherein the distinct first joints and the distinct second joints are bonded joints.
4. The assembly as recited in claim 1 , wherein each of the distinct first joints extends between neighboring vane airfoils, and at two points that are respectively nearest to the neighboring vane airfoils, the distinct first joint is closer to a pressure side of one of the neighboring vane airfoils than to a suction side of another of the neighboring vane airfoils.
5. The assembly as recited in claim 1 , wherein the first platform has a first circumferential side and the second platform has a second circumferential side that is coplanar with the first circumferential side.
6. The assembly as recited in claim 1 , wherein between neighboring vane airfoils there is a boundary where a first flow field defined around one of the neighboring vane airfoils meets a second flow field defined around another of the neighboring vane airfoils, and one of the distinct first joints is located between neighboring vane airfoils such that the distinct fist joint does not breach the boundary.
7. The assembly as recited in claim 1 , wherein the distinct first joints are straight.
8. The assembly as recited in claim 1 , wherein each of the distinct first joints is situated in a linear band between neighboring vane airfoils.
9. The assembly as recited in claim 1 , wherein the distinct first joints and the distinct second joints are metallurgical joints.
10. The assembly as recited in claim 1 , wherein the distinct first joints and the distinct second joints are bonded joints, each of the distinct first joints extends between neighboring vane airfoils, and at two points that are respectively nearest to the neighboring vane airfoils, the distinct first joint is closer to a pressure side of one of the neighboring vane airfoils than to a suction side of another of the neighboring vane airfoils.
11. The assembly as recited in claim 10 , wherein the first platform has a first circumferential side and the second platform has a second circumferential side that is coplanar with the first circumferential side, and between neighboring vane airfoils there is a boundary where a first flow field defined around one of the neighboring vane airfoils meets a second flow field defined around another of the neighboring vane airfoils, and one of the distinct first joints is located between neighboring vane airfoils such that the distinct first joint does not breach the boundary.
12. The assembly as recited in claim 11 , wherein the distinct first joints are straight.
13. A gas turbine engine comprising:
a fan;
a compressor section;
a combustor in fluid communication with the compressor section; and
a turbine section in fluid communication with the combustor, the turbine section, the compressor section or both including a stator vane assembly having a plurality of distinct vane segments each respectively including a first platform, a second platform and at least one vane airfoil connected at opposed ends thereof to the first platform and the second platform, the first platforms meeting at distinct first joints with each other and the second platforms meeting at distinct second joints with each other such that the plurality of vane segments form an annular structure, wherein at least the distinct first joints run parallel to a line that is tangent to a leading edge fillet and a trailing edge fillet on a pressure side of the at least one vane airfoil.
14. The gas turbine engine as recited in claim 13 , wherein the first platform has a first circumferential side and the second platform has a second circumferential side that is coplanar with the first circumferential side.
15. The assembly as recited in claim 14 , wherein between neighboring vane airfoils there is a boundary where a first flow field defined around one of the neighboring vane airfoils meets a second flow field defined around another of the neighboring vane airfoils, one of the distinct first joints is located between neighboring vane airfoils such that the distinct first joint does not breach the boundary, and the distinct first joints are straight.
16. A method for controlling aerodynamic performance of a stator vane assembly, the method comprising:
providing a plurality of distinct vane segments each respectively including a first platform, a second platform and at least one vane airfoil connected at opposed ends thereof to the first platform and the second platform, the first platforms meeting at distinct first joints with each other and the second platforms meeting at distinct second joints with each other such that the plurality of vane segments form an annular structure; and
situating the distinct first joints, the distinct second joints or both in locations between neighboring vane airfoils to reduce gas flow separation compared to at least one other, different location between the neighboring ones of the vane airfoils, including situating each of the distinct first joints such that it runs parallel to a line that is tangent to a leading end fillet and a trailing end fillet on a pressure side of an adjacent one of the vane airfoils.
17. The method as recited in claim 16 , including situating each of the distinct first joints between neighboring vane airfoils such that, at two points that are respectively nearest to the neighboring vane airfoils, the distinct first joint is closer to a pressure side of one of the neighboring vane airfoils than to a suction side of another of the neighboring vane airfoils.
18. The method as recited in claim 16 , including situating each of the distinct first joints in a linear band between neighboring vane airfoils.