CONTACTLESS SEALS FOR GAS TURBINE ENGINES

• US 20160053623A1
• Filed: 07/27/2015
• Published: 02/25/2016
• Est. Priority Date: 08/19/2014
• Status: Abandoned Application

• Current Assignee: United Technologies Corporation (Rtx Corporation)
• Original Assignee: United Technologies Corporation (Rtx Corporation)
• Inventors: Alvanos, Ioannis
• Application Number:
  US14/809,894
• Publication Number:
  US 20160053623A1
• Time in Patent Office: Days
• US Class Current: 1/1
• CPC Class Codes: F01D 11/001 for sealing space between stator blade and rotor
• CPC Class Codes: F01D 11/04 using sealing fluid, e.g. steam
• CPC Class Codes: F01D 11/10 using sealing fluid, e.g. steam
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2240/55 Seals
• CPC Class Codes: F16J 15/40 by means of fluid
• CPC Class Codes: F16J 15/447 Labyrinth packings

Abstract

A seal for a gas turbine engine includes a first seal structure and a second seal structure. The first seal structure is separated from the second seal structure by a gap. The first seal structure includes an injector extending into the gap with an outlet that is in fluid communication with a fluid source. Fluid issuing from the outlet and against the second seal structure magnifies a vortex formed within the gap by fluid traversing the gap.

Claims

1. A seal, comprising:

a first seal structure;

a second seal structure separated from the first seal structure by a gap; and

an injector with an outlet extending from the first seal structure into the gap, wherein the outlet is in fluid communication with a fluid source for issuing fluid against the second seal structure for magnifying a vortex formed within the gap by fluid traversing the gap.

2. A seal as recited in claim 1, wherein the second seal structure defines an impingement area with a planar surface opposite the outlet of the injector.

3. A seal as recited in claim 1, wherein the second seal structure defines an impingement area with an arcuate profile opposite the outlet of the injector.

4. A seal as recited in claim 1, wherein the first seal structure is connected to a rotor portion of a gas turbine engine.

5. A seal as recited in claim 4, wherein the first seal structure is defined by a disk cover connected to the rotor portion of the gas turbine engine.

6. A seal as recited in claim 5, wherein the injector outlet is communicative with a cavity disposed on a side of the disk cover opposite the gap.

7. A seal as recited in claim 1, wherein the first seal structure is defined by a stator portion of a gas turbine engine.

8. A seal as recited in claim 1, wherein the seal is a labyrinth seal with a first knife-edge and a second knife-edge, wherein the injector is arranged between the first and second knife-edges.

9. A seal as recited in claim 8, wherein the first seal structure defines a swirl region between the first and second seal structures, the first seal structure bounding a portion of the swirl region with a contoured surface having a curvilinear profile.

10. A seal as recited in claim 9, wherein the swirl region is a first swirl region, and wherein the first and second seal structure define a second swirl region, the first seal structure bounding a portion of the swirl region with a contoured surface having a curvilinear profile.

11. A seal as recited in claim 10, wherein curvilinear profiles bounding the first and second swirl regions minor one another with respect to an axis defined by the injector.

12. A seal as recited in the claim 10, wherein a gap width defined between the contoured surface of the first swirl region and the second seal element is greater than a gap width defined between the contoured surface of the second swirl region and the second seal element.

13. A seal as recited in claim 1, wherein the injector is arranged within a flow discouraging seal separating the rotor portion from the stator portion.

14. A seal as recited in claim 1, wherein the injector defines a linear channel extending between an inlet and the outlet of the channel.

15. A seal as recited in claim 14, wherein the linear channel defines a substantially uniform flow area along a length of the channel between the inlet and the outlet of the channel.

16. A seal as recited in claim 1, wherein the fluid outlet is oriented one of (a) toward a forward end of a gas turbine engine, (b) toward an aft end of gas turbine engine, (c) in a direction of rotation of a gas turbine engine rotor portion, or (d) in a direction opposite that of a direction of rotation of a gas turbine engine rotor portion.

17. A gas turbine engine, comprising:

a stator portion;

a rotor portion separated from the stator portion by a gap;

a first seal structure arranged on the rotor portion; and

a second seal structure arranged on the stator portion opposite the first seal structure, wherein the first seal structure includes an injector with an outlet extending from the first seal structure into the gap, wherein the outlet is in fluid communication with a fluid source for issuing fluid against the second seal structure, thereby magnifying a first and second vortices within the gap and creating a third vortex within the gap.

18. An engine as recited in claim 17, wherein the first seal structure includes a labyrinth seal having a first knife-edge and a second knife-edge, wherein the injector is defined between the first and second knife-edges.

19. An engine as recited in claim 18, wherein the first seal structure defines a swirl region in the gap bounded by a contoured surface with a curvilinear profile extending between the first knife-edge and the injector.

20. An engine as recited in claim 19, wherein the swirl region is a first swirl region, and wherein the first the seal structure defines second swirl region in the gap bounded by a contoured surface with a curvilinear profile extending between second knife-edge and the injector.