Thrust bearing system with inverted non-contacting dynamic seals for gas turbine engine

Patent metadata

Field	Value
Publication number	US-10815903-B2
Application number	US-201816151596-A
Country	US
Kind code	B2
Filing date	Oct 4, 2018
Priority date	Sep 16, 2011
Publication date	Oct 27, 2020
Grant date	Oct 27, 2020

Abstract

A gas turbine engine includes a first non-contacting dynamic rotor seal interfaced with a spool, the first non-contacting dynamic seal operates to seal adjacent to an outer diameter and a second non-contacting dynamic rotor seal with respect to the spool, the second non-contacting dynamic seal operates to seal adjacent to an inner diameter. A method of controlling a net thrust load on a thrust bearing of a gas turbine engine spool is also disclosed.

First claim

What is claimed is:

1. A method of controlling a net thrust load on a thrust bearing of a gas turbine engine spool comprising:
providing a spool defining a longitudinal axis and including a thrust bearing supporting a hub and a compressor mechanically coupled to a turbine by said hub;
establishing a first sealing relationship along the spool, including positioning a first non-contacting dynamic seal relative to the spool, the first non-contacting dynamic seal including a first body attached to a first floating shoe that seals with first rotatable inner surfaces of the spool to define a first flow cavity, and the first floating shoe radially inward of the first rotatable inner surfaces with respect to the longitudinal axis;
establishing a second sealing relationship along the spool, including positioning a second non-contacting dynamic seal relative to the spool, the second non-contacting dynamic seal including a second body attached to a second floating shoe that seals with second rotatable inner surfaces of the spool to define a second flow cavity, and the second floating shoe radially inward of the second rotatable inner surfaces with respect to the longitudinal axis; and
establishing a third sealing relationship along the spool, including positioning a third non-contacting dynamic seal relative to the spool, the third non-contacting dynamic seal including a third body attached to a third floating shoe that seals with rotatable outer surfaces of the hub, the third non-contacting dynamic seal positioned axially between the first and second floating shoes relative to the longitudinal axis to define the first flow cavity and the second flow cavity, and the third floating shoe radially outward of the rotatable outer surfaces with respect to the longitudinal axis.

2. The method as recited in claim 1 , wherein each of the first non-contacting dynamic seal, the second non-contacting dynamic seal and the third non-contacting dynamic seal is a hydrostatic seal.

3. The method as recited in claim 2 , wherein each of the first, second and third floating shoes is moveable in a radial direction with respect to the longitudinal axis in response to rotating at least one of the first rotatable inner surfaces, the second rotatable inner surfaces and the outer rotatable surfaces.

4. The method as recited in claim 2 , wherein the compressor is a high pressure compressor, and each of the second non-contacting dynamic seal and the third non-contacting dynamic seal is positioned aft of the high pressure compressor with respect to the longitudinal axis.

5. The method as recited in claim 4 , wherein the first non-contacting dynamic seal is positioned radially inboard of a high pressure compressor vane of the turbine with respect to the longitudinal axis, and the first rotatable inner surfaces are located along a platform of a compressor blade of the compressor.

6. The method as recited in claim 5 , wherein the third non-contacting dynamic seal is positioned between an outer shaft of the spool and an inner diffuser case of a combustor.

7. The method as recited in claim 4 , wherein each of the first non-contacting dynamic seal, the second non-contacting dynamic seal and the third non-contacting dynamic seal is positioned axially forward of the turbine with respect to the longitudinal axis, and the turbine is a high pressure turbine axially forward of a second turbine with respect to the longitudinal axis.

8. The method as recited in claim 6 , wherein the third non-contacting dynamic seal is positioned between an outer shaft of the spool and an inner diffuser case of a combustor.

9. The method as recited in claim 2 , wherein the spool is a high spool coaxial with a low spool including a low pressure compressor and a low pressure turbine.

10. The method as recited in claim 9 , wherein the low spool drives a fan through a geared architecture.

11. The method as recited in claim 2 , wherein each of the first and second non-contacting dynamic seals is positioned radially outward of the third non-contacting dynamic seal with respect to the longitudinal axis.

12. The method as recited in claim 11 , wherein each of the first, second and third floating shoes is moveable in a radial direction with respect to the longitudinal axis in response to rotating at least one of the first rotatable inner surfaces, the second rotatable inner surfaces and the outer rotatable surfaces.

13. The method as recited in claim 12 , wherein the first flow cavity and the second flow cavity are dimensioned in the radial direction such that net thrust loads exerted on the thrust bearing are reduced.

14. The method as recited in claim 12 , wherein the first flow cavity and the second flow cavity are positioned axially between the compressor and the turbine with respect to the longitudinal axis.

15. The method as recited in claim 2 , wherein each of the first body, the second body, and the third body is fixedly attached to and extends from a static structure of the spool.

16. The method as recited in claim 15 , wherein the third non-contacting dynamic seal is positioned radially between an outer shaft of the spool and an inner diffuser case of a combustor with respect to the longitudinal axis, the third body of the third non-contacting dynamic seal extends from and is fixedly attached to the inner diffuser case, and the rotatable outer surfaces are located along the outer shaft.

17. The method as recited in claim 16 , wherein the first flow cavity and the second flow cavity are positioned axially between the compressor and the turbine with respect to the longitudinal axis.

18. The method as recited in claim 16 , wherein the second non-contacting dynamic seal is positioned radially inboard of a high pressure turbine vane of the turbine with respect to the longitudinal axis, and the second rotatable inner surfaces are located along a platform of a turbine blade of the turbine.

19. The method as recited in claim 16 , wherein the second non-contacting dynamic seal is positioned axially aft of a high pressure turbine rotor of the turbine with respect to the longitudinal axis.

20. The method as recited in claim 16 , wherein the second non-contacting dynamic seal is positioned radially inboard of a high pressure turbine vane of the turbine with respect to the longitudinal axis, the second rotatable inner surfaces are located along a platform of the high pressure turbine vane, and the first non-contacting dynamic seal is positioned axially forward of the turbine with respect to the longitudinal axis.

Assignees

• United Technologies Corp
• Raytheon Tech Corp

Inventors

• Caprario Joseph T

Classifications

• F16J15/441

  with floating ring · CPC title

• F01D11/025

  Seal clearance control; Floating assembly; Adaptation means to differential thermal dilatations · CPC title

• F02C9/18 Primary

  by bleeding, bypassing or acting on variable working fluid interconnections between turbines or compressors or their stages {(F02C3/113 takes precedence)} · CPC title

• F05D2260/15

  Load balancing · CPC title

• F01D3/00

  Machines or engines with axial-thrust balancing effected by working-fluid · CPC title