Fluid-cooled seal arrangement for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10100672-B2
Application number	US-201414771867-A
Country	US
Kind code	B2
Filing date	Mar 7, 2014
Priority date	Mar 8, 2013
Publication date	Oct 16, 2018
Grant date	Oct 16, 2018

Abstract

A component for a gas turbine engine includes a compartment housing that redirects oil from at least one passage in a rotational component onto a backside of a seal land.

First claim

What is claimed is:

1. A component for a gas turbine engine having an engine axis, the component comprising:
a rotationally fixed compartment housing that redirects oil from at least one passage in a rotational component onto a backside of a seal land, a surface of said compartment housing is angled, with respect to the engine axis, in a direction away from said at least one passage at a component surface angle; and
a flange that extends from said rotational component, said flange extends axially beyond said seal land to direct the oil axially past said seal land, said flange is angled at a flange angle with respect to the engine axis in a direction opposite the direction said component surface angle is angled in.

2. The component as recited in claim 1 , wherein said rotational component at least partially supports a carbon element.

3. The component as recited in claim 2 , wherein said rotational component is a seat for said carbon element.

4. The component as recited in claim 2 , wherein said rotational component is an aft seat for said carbon element.

5. The component as recited in claim 1 , further comprising a swirl interrupter that extends from said surface of said compartment housing to redirect oil.

6. The component as recited in claim 5 , wherein said seal land is radially inboard of said swirl interrupter.

7. The component as recited in claim 1 , wherein said seal land is radially inboard of said compartment housing.

8. The component as recited in claim 1 , wherein said seal land axially extends from said compartment housing and includes an end section with a hooked end, said end section defines an angle with respect to the engine axis in a direction of said flange angle.

9. The component as recited in claim 1 , wherein said flange extends from an aft seat mounted to the rotational component.

10. The component as recited in claim 9 , wherein said rotational component is a shaft.

11. The component as recited in claim 10 , wherein said aft seat is a rotating seat for a carbon element.

12. The component as recited in claim 11 , wherein said carbon element rides upon said seal land opposite said backside.

13. The component as recited in claim 1 , further comprising two swirl interrupters that extend from said surface of said compartment housing to redirect oil, said two swirl interrupters located (30) thirty degrees from top dead center (TDC).

14. The component as recited in claim 1 , further comprising three swirl interrupters that extend from said surface of said compartment housing to redirect oil, one swirl interrupter located at top dead center (TDC) and each of the two others (30) thirty degrees therefrom.

Assignees

• United Technologies Corp

Inventors

• Vdoviak Jr Garth J
• Grogg Gary L

Classifications

• F04D29/321

  for axial flow compressors · CPC title

• F02C7/06

  Arrangements of bearings (bearings F16C); Lubricating ({of turbo machines F01D25/18; of machines or} engines in general F01M) · CPC title

• F05D2260/20

  Heat transfer, e.g. cooling · CPC title

• F01D25/183 Primary

  Sealing means · CPC title

• F16J15/162

  Special parts or details relating to lubrication or cooling of the sealing itself (F16J15/324, F16J15/3404, F16J15/40 take precedence) · CPC title