Non-metallic side plate seal assembly for a gas turbine engine
A side plate seal assembly for a gas turbine engine includes a multiple of non-metallic side plate seals that are arranged about an axis of the gas turbine engine to form a full hoop seal, each of the multiple of side plate seals comprise a retention surface and a knife edge seal surface that extends at an angle therefrom.
1. A side plate seal assembly for a gas turbine engine, comprising:
a multiple of non-metallic side plate seals that are arranged about an axis of the gas turbine engine to form a full hoop seal, each of the multiple of side plate seals comprise a retention surface and a knife edge seal surface that extends at an angle therefrom.
2. The side plate seal assembly as recited in claim 1 , wherein the multiple of non-metallic side plate seals that are arranged about the axis each interface one to another via a shiplap interface.
3. The side plate seal assembly as recited in claim 1 , wherein the multiple of non-metallic side plate seals are manufactured of a ceramic matrix composite (CMC).
4. The side plate seal assembly as recited in claim 1 , wherein the multiple of non-metallic side plate seals are manufactured of an organic matrix composite (OMC).
5. The side plate seal assembly as recited in claim 1 , wherein the knife edge seal surface extends from the retention surface at the angle between 130-160 degrees.
6. The side plate seal assembly as recited in claim 1 , wherein the retention surface is generally planar.
7. The side plate seal assembly as recited in claim 1 , wherein the retention surface tapers to an inner diameter surface.
8. A rotor assembly for a gas turbine engine, comprising:
a rotor disk that defines an axis;
a full hoop cover plate; and
a non-metallic side plate seal assembly at least partially between the rotor disk and the full hoop cover plate, the non-metallic side plate seal assembly comprises a multiple of non-metallic side plate seals that are arranged about the axis.
9. The assembly as recited in claim 8 , wherein the rotor disk and full hoop cover plate are manufactured of a metallic alloy.
10. The assembly as recited in claim 8 , wherein the multiple of non-metallic side plate seals each interface one to another via a shiplap interface.
11. The assembly as recited in claim 8 , wherein the full hoop cover plate forms at least one knife edge seal and the non-metallic side plate seal assembly forms at least one knife edge seal, the non-metallic side plate knife edge seal outboard of the full hoop cover plate knife edge seal with respect to the axis.
12. The assembly as recited in claim 8 , wherein an outer diameter edge of a retention surface of the non-metallic side plate seal assembly abuts a platform of a rotor blade retained in the disk.
13. The assembly as recited in claim 12 , wherein the non-metallic side plate knife edge seal interfaces with a seal surface attached an inner vane platform, the inner vane platform downstream of the rotor disk.
14. The assembly as recited in claim 12 , wherein a lower surface that includes an inner diameter edge of the retention surface is sandwiched between the rotor disk and the full hoop cover plate.
15. The assembly as recited in claim 8 , wherein each of the multiple of non-metallic side plate seals are identical.
16. A gas turbine engine, comprising:
a rotor disk along an engine axis;
an inner vane platform adjacent to the rotor disk;
a seal surface attached an inner vane platform; and
a non-metallic side plate seal assembly, the non-metallic side plate seal assembly comprises a retention surface adjacent to the rotor disk and a knife edge seal surface that extends at an angle from the retention surface to interface with the seal surface.
17. The gas turbine engine as recited in claim 16 , wherein the non-metallic side plate seal assembly comprises a multiple of non-metallic side plate seals that are identical.
18. The gas turbine engine as recited in claim 17 , wherein the multiple of non-metallic side plate seals each interface one to another via a shiplap interface.
19. The gas turbine engine as recited in claim 18 , wherein an outer diameter edge of a retention surface of the non-metallic side plate seal assembly abuts a platform of a rotor blade retained in the disk.
20. The gas turbine engine as recited in claim 19 , wherein a lower surface that includes an inner diameter edge of the retention surface is sandwiched between the rotor disk and a full hoop cover plate, wherein the full hoop cover plate forms at least one knife edge seal inboard of non-metallic side plate knife edge seal with respect to the engine axis.