Hydrodynamic carbon face seal pressure booster

Patent metadata

Field	Value
Publication number	US-9909438-B2
Application number	US-201615096952-A
Country	US
Kind code	B2
Filing date	Apr 12, 2016
Priority date	Apr 12, 2016
Publication date	Mar 6, 2018
Grant date	Mar 6, 2018

Abstract

Aspects of the disclosure are directed to a system associated with an engine of an aircraft, the system comprising: a fluid source that is configured to provide a fluid at a first pressure value, a carbon seal, a seal plate that includes at least one lift-off feature that interfaces to the carbon seal, and a pressure boosting mechanism configured to obtain the fluid from the fluid source, increase the pressure of the fluid to a second pressure value, and provide the fluid at the second pressure value to the at least one lift-off feature.

First claim

What is claimed is:

1. A seal for a component of a gas turbine engine, the seal comprising:
a rotating seal disposed against a first axial side of the component;
a stationary seal disposed against a first axial side of the rotating seal;
a groove in a surface between the rotating seal and the stationary seal; and
a spacer;
wherein a cavity is disposed in the rotating seal, the cavity opening to a radially interior side of the rotating seal;
wherein a channel is disposed in the rotating seal, fluidly connecting the cavity and the groove;
wherein a radially inner surface of the rotating seal and a radially outer surface of the spacer define a gap; and
wherein the gap has an axial length within a range of 0.05 inches and 0.10 inches and a radial width within a range of 0.02 inches and 0.03 inches to cause a rotational component to be imparted on a fluid that traverses the axial length of the gap at an end of the gap proximate the cavity.

2. The seal of claim 1 , wherein the component is a bearing compartment.

3. The seal of claim 1 , wherein the stationary seal is a carbon seal.

4. The seal of claim 1 , wherein the groove is in the rotating seal.

5. The seal of claim 1 , wherein the groove is a spiral groove.

6. The seal of claim 1 , wherein the groove is a plurality of grooves.

7. The seal of claim 1 , wherein a radially outer end of the groove is circumferentially offset from a radially inner end of the groove.

8. A gas turbine engine comprising:
a component;
a seal for the component, the seal including
a rotating seal disposed against a first axial side of the component;
a stationary seal disposed against a first axial side of the rotating seal; and
a groove in a surface between the rotating seal and the stationary seal;

a shaft; and
a spacer coupled to the shaft and located radially outward of the shaft;
wherein a cavity is disposed in the rotating seal, the cavity opening to a radially interior side of the rotating seal;
wherein a channel is disposed in the rotating seal, fluidly connecting the cavity and the groove;
wherein a radially inner surface of the rotating seal and a radially outer surface of the spacer define a gap; and
wherein the gap has an axial length within a range of 0.05 inches and 0.10 inches and a radial width within a range of 0.02 inches and 0.03 inches to cause a rotational component to be imparted on a fluid that traverses the axial length of the gap at an end of the gap proximate the cavity.

9. The gas turbine engine of claim 8 , further comprising:
a compressor that provides at least a portion of the fluid.

10. The gas turbine engine of claim 8 , further comprising:
an o-ring seal that prevents fluid in the cavity from flowing to a fluid source.

11. The gas turbine engine of claim 8 , wherein the component is a bearing compartment.

12. The gas turbine engine of claim 8 , wherein the stationary seal includes a carbon seal.

13. The gas turbine engine of claim 8 , wherein the channel is angled relative to a radial reference direction associated with the engine and has a value within a range of 0 to 90 degrees.

Assignees

• United Technologies Corp

Inventors

• Duffy Kevin
• Kovacik Ronald K
• Walker Brady
• Artiles Antonio F

Classifications

• F01D11/003 Primary

  by packing rings; Mechanical seals · CPC title

• F05D2220/32

  in gas turbines · CPC title

• F05D2240/50

  Bearings · CPC title

• F16J15/406

  by at least one pump · CPC title

• F01D11/04 Primary

  using sealing fluid, e.g. steam · CPC title