Seal assembly for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-12428969-B1
Application number	US-202418796888-A
Country	US
Kind code	B1
Filing date	Aug 7, 2024
Priority date	Aug 7, 2024
Publication date	Sep 30, 2025
Grant date	Sep 30, 2025

Abstract

A gas turbine engine includes a compressor section and a turbine section in axial flow arrangement defining an axially extending, longitudinal centerline, and arranged as a rotor and a stator. A seal assembly defines a primary seal at an interface of the rotor and the stator and separates an inlet plenum from an outlet plenum. The seal assembly includes one or more aspiration conduits fluidly connected to the primary seal. One or more flingers are positioned at least partially between the seal assembly and the inlet plenum that define one or more passageways fluidly connecting the inlet plenum to the one or more aspiration conduits. The flingers are positioned to direct at least a portion of an airflow within the inlet plenum away from the one or more passageways.

First claim

We claim:

1. A gas turbine engine comprising:
a compressor section and a turbine section in axial flow arrangement defining an axially extending, longitudinal centerline, and arranged as a rotor and a stator;
a seal assembly defining a primary seal at an interface of the rotor and the stator, the seal assembly separating an inlet plenum from an outlet plenum, the seal assembly comprising one or more aspiration conduits fluidly connected to the primary seal; and
one or more flingers positioned at least partially between the seal assembly and the inlet plenum, the one or more flingers defining one or more passageways fluidly connecting the inlet plenum to the one or more aspiration conduits, the one or more flingers positioned to direct at least a portion of an airflow within the inlet plenum away from the one or more passageways.

2. The gas turbine engine of claim 1 , wherein the one or more flingers are coupled to the seal assembly.

3. The gas turbine engine of claim 1 , wherein the one or more passageways comprise one or more first passageways and one or more second passageways, wherein the one or more first passageways define an axial airflow direction with respect to the one or more aspiration conduits, and wherein the one or more second passageways define a radial airflow direction with respect to the one or more aspiration conduits.

4. The gas turbine engine of claim 1 , wherein the one or more flingers extend axially with respect to the inlet plenum.

5. The gas turbine engine of claim 1 , wherein the one or more flingers comprise at least one portion angled radially outward with respect to the inlet plenum.

6. The gas turbine engine of claim 1 , wherein the one or more flingers comprise at least one wedge-shaped baffle.

7. The gas turbine engine of claim 1 , wherein at least one flinger of the one or more flingers comprises at least one surface defining a radially inward boundary of the inlet plenum, and wherein the at least one flinger of the one or more flingers comprise:
a first portion having a first end coupled to the at least one surface and a second end disposed radially outward from the first end; and
a second portion extending from the at least one surface to the second end.

8. The gas turbine engine of claim 1 , wherein the one or more flingers comprise a first baffle and a second baffle, wherein the first baffle is axially spaced apart from the second baffle.

9. The gas turbine engine of claim 1 , wherein the one or more flingers comprise a first baffle and a second baffle, wherein the first baffle is circumferentially spaced apart from the second baffle.

10. The gas turbine engine of claim 1 , wherein at least one flinger of the one or more flingers is positioned to direct the airflow within the inlet plenum circumferentially with respect to the one or more passageways.

11. The gas turbine engine of claim 1 , wherein the seal assembly comprises at least one of a floating face seal assembly or a floating radial seal assembly.

12. The gas turbine engine of claim 1 , wherein at least one flinger of the one or more flingers comprises a first end coupled to the seal assembly and a second end spaced apart from the seal assembly.

13. The gas turbine engine of claim 12 , wherein at least one inlet of at least one passageway of the one or more passageways is defined between the second end and the seal assembly.

14. The gas turbine engine of claim 12 , wherein the at least one flinger of the one or more flingers comprises at least one baffle positioned at the second end.

15. The gas turbine engine of claim 1 , wherein at least one flinger of the one or more flingers comprises one or more tabs extending radially inward toward the seal assembly.

16. A gas turbine engine comprising:
a compressor section and a turbine section in axial flow arrangement defining an axially extending, longitudinal centerline, and arranged as a rotor and a stator;
a seal assembly defining a primary seal at an interface of the rotor and the stator, the seal assembly separating an inlet plenum from an outlet plenum, the seal assembly comprising one or more aspiration conduits fluidly connected to the primary seal to provide an airflow from the inlet plenum to the primary seal; and
one or more flingers positioned at least partially between the seal assembly and the inlet plenum, the one or more flingers defining a first passageway defining a first airflow direction and a second passageway defining a second airflow direction, wherein the second airflow direction is different than the first airflow direction, wherein the first and second passageways are fluidly connected to the inlet plenum and the one or more aspiration conduits.

17. The gas turbine engine of claim 16 , wherein the airflow within the inlet plenum is flowing in a third airflow direction different than the first airflow direction.

18. The gas turbine engine of claim 16 , wherein the one or more flingers include one or more baffles positioned to direct the airflow within the inlet plenum radially outward with respect to the one or more flingers.

19. The gas turbine engine of claim 18 , wherein at least one flinger of the one or more flingers comprises a ramp-shaped flinger.

20. A gas turbine engine comprising:
a compressor section and a turbine section in axial flow arrangement defining an axially extending, longitudinal centerline, and arranged as a rotor and a stator;
a seal assembly defining a primary seal at an interface of the rotor and the stator, the seal assembly separating an inlet plenum from an outlet plenum, the seal assembly comprising one or more aspiration conduits fluidly connected to the primary seal to provide an airflow from the inlet plenum to the primary seal; and
one or more flingers positioned at least partially between the seal assembly and the inlet plenum, the one or more flingers defining one or more passageways between the seal assembly and the inlet plenum, wherein the one or more passageways are fluidly connected to the inlet plenum, and wherein the one or more flingers comprise one or more baffles configured to cause the airflow flowing within the inlet plenum in a first direction to enter the one or more passageways in a second direction, wherein the second direction is different than the first direction by at least 180°.

Assignees

• Gen Electric

Inventors

• Jalan Prateek
• Johnson Steven Douglas
• Kumar Rajesh
• Singh Tajinder
• Kumar Alok
• Parisot Lucas
• Ratzlaff Jonathan Russell

Classifications

• F01D11/001 Primary

  for sealing space between stator blade and rotor · CPC title

• F05D2240/55

  Seals · CPC title

• F01D11/06 Primary

  Control thereof · CPC title