Seal for a gas turbine engine
A component for a gas turbine engine includes a first platform that has a first pair of circumferential surfaces and a first axially aft surface. A first axially extending seal slot is located in each of the first pair of circumferential surfaces and the first axially aft surface. A first cover plate is attached to the first axially aft surface and encloses at least a portion of the first axially extending seal slots.
1. A component for a gas turbine engine comprising:
a first platform having a first pair of circumferential surfaces that are circumferentially opposing, a first axially aft surface, and a surface defining a core gas flow path;
a first axially extending seal slot located in each of the first pair of circumferential surfaces and the first axially aft surface; and
a first cover plate attached to the first axially aft surface enclosing at least a portion of the first axially extending seal slot located in each of the first pair of circumferential surfaces, wherein a radial direction and a circumferential direction are defined with respect to a central longitudinal axis of the gas turbine engine.
2. The component of claim 1 , wherein the first axially aft surface intersects the pair of circumferential surfaces.
3. The component of claim 1 , wherein the first axially extending seal slots are formed with a grinding process.
4. The component of claim 1 , wherein the first cover plate is welded to the first axially aft surface.
5. The component of claim 4 , wherein the first axially extending seal slots extend through a leading edge of the first platform.
6. The component of claim 1 , wherein a portion of the first axially aft surface defines a trailing edge rail and the axially aft surface intersects the pair of circumferential surfaces and the component includes one of a blade outer air seal or an airfoil.
7. The component of claim 6 , wherein the component is an airfoil and includes a first airfoil end adjacent the first platform and a second airfoil end adjacent a second platform having a second pair of circumferential surfaces and a second axially aft surface and a second axially extending seal slot located in each of the second pair of circumferential surfaces and the second axially aft surface.
8. The component of claim 7 , including a second cover plate attached to the second axially aft surface enclosing at least a portion of the second axially extending seal slots.
9. A gas turbine engine comprising:
a compressor section upstream of a combustor section; and
a turbine section downstream of the combustor section wherein at least one of the compressor section or the turbine section includes a component having:
a first platform having a first pair of circumferential surfaces that are circumferentially opposing and a first axially aft surface;
a first axially extending seal slot located in each of the first pair of circumferential surfaces and the first axially aft surface; and
a first cover plate attached to the first axially aft surface enclosing at least a portion of the first axially extending seal slot located in each of the first pair of circumferential surfaces;
an airfoil having a first end adjacent the first platform and a second end adjacent a second platform, the second platform having a second pair of opposing circumferential surfaces and a second axially aft surface and a second axially extending seal slot located in each of the second pair of circumferential surfaces and the second axially aft surface, wherein a radial direction and a circumferential direction are defined with respect to a central longitudinal axis of the gas turbine engine.
10. The gas turbine engine of claim 9 , wherein the first axially aft surface intersects the pair of circumferential surfaces.
11. The gas turbine engine of claim 9 , wherein the first axially extending seal slots are formed with a grinding process.
12. The gas turbine engine of claim 9 , wherein the first cover plate is welded to the first axially aft surface.
13. The gas turbine engine of claim 12 , wherein the first axially extending seal slot extends through a leading edge of the first platform.
14. The gas turbine engine of claim 9 , including a second cover plate attached to the second axially aft surface enclosing at least a portion of the second axially extending seal slots.
15. A method of forming a seal slot in a component including the steps of:
forming a first axially extending seal slot through each of a pair of first circumferential surfaces and through a first axially aft surface on a first platform, wherein the pair of first circumferential surfaces are circumferentially opposed, the first platform includes a surface defining a core flow path, and a circumferential direction is defined with respect to a central longitudinal axis of a gas turbine engine; and
enclosing a portion of the first axially extending seal slot located in each of the pair of first circumferential surfaces with a cover plate attached to the first axially aft surface.
16. The method of claim 15 , wherein the first axially extending seal slot located in each of the pair of first circumferential surfaces is formed through a grinding process.
17. The method of claim 15 , further comprising the steps of:
forming a second axially extending seal slot through each of a pair of second circumferential surfaces and a second axially aft surface on a second platform, wherein the pair of second circumferential surfaces are circumferentially opposed, an airfoil includes a first end adjacent the first platform and a second end adjacent the second platform; and
enclosing at least a portion of the pair of second axially extending seal slot, with a second cover plate attached to the second axially aft surface.
18. The method of claim 17 , wherein the second axially extending seal slot is formed through a grinding process.
19. The method of claim 18 , including welding the second cover plate to the first axially aft surface.