Rotor hub seal

Patent metadata

Field	Value
Publication number	US-10954953-B2
Application number	US-201916251488-A
Country	US
Kind code	B2
Filing date	Jan 18, 2019
Priority date	Jan 8, 2016
Publication date	Mar 23, 2021
Grant date	Mar 23, 2021

Abstract

A gas turbine engine includes a rotor hub that extends along a longitudinal axis of the gas turbine engine and includes a radially outer surface that has 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. 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.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a rotor hub extending along a longitudinal axis of the gas turbine engine including a radially outer surface having 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 axially extending projection of the rotor hub; and
a lock ring 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, 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 , including a plenum at least partially defined by the rotor hub and the seal ring.

3. 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 radially extending projection.

4. The gas turbine engine of claim 1 , including a rotor disk supporting a plurality of rotor blades.

5. The gas turbine engine of claim 4 , wherein the rotor hub abuts the rotor disk at an axially forward end and a spool on an axially downstream end.

6. The gas turbine engine of claim 5 , wherein the rotor hub tapers from an axially upstream end toward an axially downstream end.

7. The gas turbine engine of claim 1 , wherein the axially extending projection is located axially upstream of the radially extending projection and both the axially extending projection and the axially extending projection are located on a common axial side of the rotor hub.

8. A gas turbine engine comprising:
a rotor huh extending along a longitudinal axis of the gas turbine engine including a radially outer surface having 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 axially extending projection of the rotor hub;
a lock ring 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;
a plenum at least partially defined by the rotor hub and the seal ring; and
a feed passage in the rotor hub in fluid communication with the plenum.

9. The gas turbine engine of claim 8 , wherein the substantially axially extending projection is located axially upstream of the substantially radially extending projection.

10. The gas turbine engine of claim 9 , wherein a radially inward facing surface on the substantially axially extending projection is located radially outward from a distal end of the substantially radially extending projection.

11. The gas turbine engine of claim 10 , wherein the recess in the body portion is at least partially defined by an axially extending projection of the seal ring and directly contacts the radially inward facing surface.

12. The gas turbine engine of claim 8 , wherein the seal ring includes at least one cooling passage extending through the seal ring.

13. The gas turbine engine of claim 12 , wherein the at least one cooling passage includes at least one of an impingement cooling passage and a film cooling passage.

14. The gas turbine engine of claim 12 , wherein the at least one cooling passage extends in a radially outward direction.

Assignees

• Raytheon Tech Corp

Inventors

• Wilber John E

Classifications

• F05D2260/201

  by impingement of a fluid · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F01D5/08

  Heating, heat-insulating or cooling means {(specially adapted for radial flow machines or engines F01D5/04)} · CPC title

• F04D29/083 Primary

  especially adapted for elastic fluid pumps · CPC title

• F05D2240/55

  Seals · CPC title