Trailing edge platform seals
A platform trailing edge seal for a turbomachine airfoil (e.g., a blade or vane) assembly includes a body configured to extend into an aft portion of a mateface gap defined between a circumferentially adjacent pair of turbomachine airfoil platforms to minimize flow from entering a blade-vane cavity through the aft portion of the mateface gap.
1. A platform trailing edge seal for a turbomachine airfoil assembly, comprising:
a body having a first portion that reaches across a mateface gap defined between a circumferentially adjacent pair of turbomachine airfoil platforms and partially into an adjacent blade platform and a second portion that extends towards a blade root to minimize flow from entering a blade-vane cavity through an aft portion of the mateface gap, the body being shaped to match a platform trailing edge shape.
2. The seal of claim 1 , wherein the body includes at least one of aluminum, titanium, or nickel.
3. The seal of claim 1 , wherein the body is annular.
4. The seal of claim 1 , wherein the body defines a segment of an annular structure.
5. A turbomachine blade assembly, comprising:
a blade having a blade platform which defines a platform trailing edge portion;
and a platform trailing edge seal extending from the trailing edge portion, comprising:
a retaining feature attached to a blade platform at the platform trailing edge portion configured to retain the platform trailing edge seal to the blade platform; and
an annular body that engages the retaining feature and is configured to extend towards an aft portion of a mateface gap defined between the blade platform and an adjacent blade platform to minimize flow from entering a blade-vane cavity through the aft portion of the mateface gap.
6. The assembly of claim 5 , wherein the platform trailing edge seal is formed integrally with the platform trailing edge.
7. The assembly of claim 5 , wherein the platform trailing edge seal attached to the platform trailing edge.
8. The assembly of claim 5 , wherein the body includes at least one of aluminum, titanium, or nickel.
9. The assembly of claim 5 , wherein the body is shaped to match the platform trailing edge shape.
10. The assembly of claim 5 , wherein the body defines a segment of an annular structure.
11. The assembly of claim 5 , wherein the blade is located in one of a low pressure compressor, a high pressure compressor, a low pressure turbine, or a high pressure turbine.
12. The assembly of claim 5 , wherein the platform trailing edge seal is friction fit, thermally fit, or expansion fit to the blade platform.
13. The assembly of claim 5 , further including another retaining feature attached to a blade root and is configured to retain the platform trailing edge seal to the blade platform.
14. A turbomachine, comprising:
a turbomachine blade assembly, including:
a blade having a blade platform which defines a platform trailing edge portion; and
a platform trailing edge seal extending from the trailing edge portion and is at least one of formed integrally with and attached to a platform trailing edge, comprising:
a body having a first portion that extends into an aft portion of a mateface gap defined between the blade platform and an adjacent blade platform and a second portion that extends towards and engages a retaining feature that is attached to a blade root to minimize flow from entering a blade-vane cavity through the aft portion of the mateface gap.
15. The turbomachine of claim 14 , wherein the body includes at least one of aluminum, titanium, or nickel.
16. The turbomachine of claim 14 , wherein the body is shaped to match the platform trailing edge shape.