Rotor hub seal
A gas turbine engine includes a rotor hub which includes a substantially axially extending projection and a substantially radially extending projection. A seal ring includes a body portion and at least one knife edge that extends outward from the body portion. A recess is in the body portion for accepting the axially extending portion of the rotor hub. The seal ring includes at least one cooling passage that extends through the seal ring. A lock ring is in abutting contact with the seal ring and the radially extending projection on the rotor hub for securing the seal ring to the rotor hub.
1. A gas turbine engine comprising:
a rotor hub including a substantially axially extending projection and a substantially radially extending projection;
a seal ring including a body portion and at least one knife edge extending outward from the body portion, a recess in the body portion for accepting the substantially axially extending portion of the rotor hub, wherein the seal ring includes at least one cooling passage extending through the seal ring; and
a lock ring in abutting contact with the seal ring and the substantially radially extending projection on the rotor hub for securing the seal ring to the rotor hub, wherein an axially downstream-most surface on the seal ring is located upstream of a contact surface on the lock ring.
2. The gas turbine engine of claim 1 , wherein the at least one cooling passage includes at least one of an impingement cooling passage and a film cooling passage.
3. The gas turbine engine of claim 1 , including a plenum at least partially defined by the rotor hub and the seal ring.
4. The gas turbine engine of claim 3 , including a feed passage in the rotor hub in fluid communication with the plenum.
5. The gas turbine engine of claim 1 , wherein the at least one cooling passage extends in a radially outward direction.
6. The gas turbine engine of claim 1 , wherein a radially innermost surface on the seal ring is located radially outward from a radially outermost surface on the substantially radially extending projection.
7. A gas turbine engine comprising,
a rotor hub including a substantially axially extending projection and a substantially radially extending projection;
a seal ring including a body portion and at least one knife edge extending outward from the body portion, a recess in the body portion for accepting the substantially axially extending portion of the rotor hub, wherein the seal ring includes at least one cooling passage extending through the seal ring;
a lock ring in abutting contact with the seal ring and the substantially radially extending projection on the rotor hub for securing the seal ring to the rotor hub; and
a rotor disk supporting a plurality of rotor blades, wherein the rotor hub abuts the rotor disk at an axially forward end and a spool on an axially downstream end.
8. The gas turbine engine of claim 7 , wherein the rotor hub tapers from an axially upstream end toward an axially downstream end.
9. The gas turbine engine of claim 7 , wherein an axially downstream-most surface on the seal ring is located upstream of a contact surface on the lock ring.
10. A seal assembly for a gas turbine engine comprising:
a seal ring including:
a body portion including a recess in the body portion for accepting a portion of a rotor hub on an axially upstream end;
at least one knife edge extending outward from the body portion; and
at least one cooling passage extending through the seal ring; and
a stop extending from a downstream end of the body portion for engaging a lock ring; and
the lock ring in abutting contact with the seal ring, wherein an axially downstream-most surface on the seal ring is located upstream of a contact surface on the lock ring.
11. The seal assembly of claim 10 , wherein the rotor hub includes a substantially axially extending projection and a substantially radially extending projection, wherein the substantially axially extending projection is accepted within the recess in the seal ring.
12. The seal assembly of claim 10 , wherein the at least one cooling passage includes at least one of an impingement cooling passage and a film cooling passage.
13. The seal assembly of claim 11 , including a plenum at least partially defined by the rotor hub and the seal ring.
14. The seal assembly of claim 13 , including a feed passage in the rotor hub in fluid communication with the plenum.
15. The seal assembly of claim 11 , wherein the rotor hub includes a rotor disk contact surface on an axially upstream portion for contacting a rotor disk and a spool contact surface on an axially downstream portion for contacting a spool.
16. The seal assembly of claim 10 , wherein the at least one cooling passage extends in a radially outward direction.
17. The seal assembly of claim 10 , including a rotor hub having a substantially axially extending projection and a substantially radially extending projection, wherein the lock ring is in abutting contact with the substantially radially extending projection on the rotor hub for securing the seal ring to the rotor hub.