Rotor assembly for a gas turbine engine
A rotor assembly is provided, along with gas turbine engines for its use. The rotor assembly may include a spool defining a plurality of apertures arranged in a first row and spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade extends through a respective aperture.
1. A rotor assembly comprising:
a spool defining a plurality of apertures spaced circumferentially around the spool, wherein each aperture of the plurality of apertures extends through the spool from a radially inward-facing surface to a radially outward-facing surface; and
a blade assembly comprising at least two blades connected to each other via a platform, wherein each blade of the at least two blades extends through a respective aperture of the plurality of apertures,
wherein the platform is disposed radially inward of the radially inward-facing surface of the spool and extends circumferentially from a first blade of the at least two blades to a second blade of the at least two blades and has a convex surface facing radially outward.
2. The rotor assembly of claim 1 , wherein at least one of the spool or the blade assembly comprises a ceramic matrix composite.
3. The rotor assembly of claim 1 , wherein the blade assembly further comprises a retention device positioned in contact with the blade assembly.
4. The rotor assembly of claim 3 , wherein the retention device comprises a pin between the platform and the radially inward-facing surface of the spool.
5. The rotor assembly of claim 4 , wherein the platform has a radially outward surface with a shape configured to accept the pin between the radially inward-facing surface of the spool and the radially outward surface of the platform.
6. The rotor assembly of claim 3 , wherein the retention device comprises a fastener extending through an aperture within the platform and attaching to the radially inward-facing surface of the spool.
7. The rotor assembly of claim 3 , wherein the retention device comprises a retention ring positioned adjacent to a radially inward surface of the platform.
8. The rotor assembly of claim 1 , wherein the platform has a radially outward surface that conforms to the radially inward-facing surface of the spool.
9. The rotor assembly of claim 8 , wherein the radially outward surface of the platform is in direct contact with the radially inward-facing surface of the spool.
10. The rotor assembly of claim 1 , further comprising:
a spacer positioned between the radially inward-facing surface of the spool and a radially outward surface of the platform.
11. The rotor assembly of claim 1 , further comprising:
a seal positioned within each aperture to couple each blade of the at least two blades with the spool.
12. The rotor assembly of claim 1 , further comprising:
at least one balancing component.
13. The rotor assembly of claim 12 , wherein the at least one balancing component includes a plurality of voids formed in the spool, in the blade assembly, or both.
14. The rotor assembly of claim 13 , wherein the at least one balancing component further comprises at least one balancing mass positioned within at least one of the plurality of voids.
15. The rotor assembly of claim 1 , wherein the first blade, the second blade, and the platform form a monolithic structure.
16. The rotor assembly of claim 1 , wherein the blade assembly comprises a ceramic matrix composite.