Chordal seal
A vane for a gas turbine engine includes at least one airfoil. A first platform has a first rail located at a first end of the airfoil. A second platform has a second rail located at a second end of the airfoil. A first chordal seal is located on an axially aft surface of the first rail. A second chordal seal is located on an aft surface of the second rail and has a second radius of curvature at least partially truncated by an outer edge of the second rail.
1. A vane for a gas turbine engine comprising;
at least one airfoil;
a first platform having a first rail located at a first end of the airfoil;
a second platform having a second rail located at a second end of the airfoil;
a first chordal seal located on an axially aft surface of the first rail; and
a second chordal seal located on an axially aft surface of the second rail having a second radius of curvature at least partially truncated by an outer edge of the second rail;
wherein the first rail includes a radially outermost edge extending along a curvature, a first plateau on the axially aft surface that is located radially outward from the first chordal seal with the first plateau extending between a first circumferential edge and a second circumferential edge, and the first chordal seal includes a first radius of curvature and the first and second chordal seal extend in a linear direction.
2. The vane of claim 1 , wherein the outer edge of the second rail that at least partially truncated the second chordal seal is a radially inner edge of the second rail.
3. The vane of claim 2 , wherein the radially inner edge at least partially defines a radially innermost surface on the second rail.
4. The vane of claim 1 , wherein the first rail includes a second plateau on the axially aft surface located radially inward from the first chordal seal with the second plateau extending between the first circumferential edge and second circumferential edge, and the first plateau is axially offset from the second plateau.
5. The vane of claim 4 , wherein a radially outer edge of the first chordal seal is connected with the first plateau by a first fillet and a radially inner edge of the first chordal seal is connected with the second plateau by a second fillet.
6. The vane of claim 2 , wherein the second rail includes a first plateau on the axially aft surface of the second rail located radially outward from the second chordal seal.
7. The vane of claim 6 , wherein a radially inner edge of the second chordal seal at least partially defines a radially inner edge of the second rail.
8. The vane of claim 1 , wherein a downstream most point on the first chordal seal is located axially aft of a downstream most point on the second chordal seal.
9. The vane of claim 1 , wherein the first radius of curvature is equal to the second radius of curvature.
10. A gas turbine engine comprising:
a compressor section upstream of a combustor section;
a turbine section located downstream of the combustor section, and at least one of the turbine section or the compressor section includes a vane having:
at least one airfoil
a first platform having a first rail located at a first end of the airfoil;
a second platform having a second rail located at a second end of the airfoil;
a first chordal seal located on an axially aft surface of the first rail; and
a second chordal seal located on an axially aft surface of the second rail having a second radius of curvature at least partially truncated by an outer edge of the second rail;
wherein the first rail includes a radially outermost edge extending along a curvature, a first plateau on the axially aft surface that is located radially outward from the first chordal seal with the first plateau extending between a first circumferential edge and a second circumferential edge of the first rail and the first chordal seal includes a first radius of curvature and the first chordal seal engages a blade outer air seal.
11. The gas turbine engine of claim 10 , wherein the outer edge of the second rail that at least partially truncated the second chordal seal is a radially inner edge of the second rail and the first chordal seal and the second chordal seal extend in a linear direction.
12. The gas turbine engine of claim 11 , wherein the radially inner edge at least partially defines a radially innermost surface on the second rail.
13. The gas turbine engine of claim 10 , wherein the first rail includes a second plateau on the axially aft surface located radially inward from the first chordal seal with the second plateau extending between the first circumferential edge of the first rail and the second circumferential edge of the first rail and the first plateau is axially offset from the second plateau.
14. The gas turbine engine of claim 13 , wherein a radially outer edge of the first chordal seal is connected with the first plateau by a first fillet and a radially inner edge of the first chordal seal is connected with the second plateau by a second fillet.
15. The gas turbine engine of claim 10 , wherein the second rail includes a first plateau on the axially aft surface of the second rail located radially outward from the second chordal seal.
16. The gas turbine engine of claim 15 , wherein a radially inner edge of the second chordal seal at least partially defines a radially inner edge of the second rail.
17. The gas turbine engine of claim 10 , wherein a downstream most point on the first chordal seal is located axially aft of a downstream most point on the second chordal seal.
18. The gas turbine engine of claim 10 , wherein the first radius of curvature is equal to the second radius of curvature.