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

Patent metadata

Field	Value
Publication number	US-10119476-B2
Application number	US-201113234338-A
Country	US
Kind code	B2
Filing date	Sep 16, 2011
Priority date	Sep 16, 2011
Publication date	Nov 6, 2018
Grant date	Nov 6, 2018

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.

First claim

What is claimed is:

1. A gas turbine engine comprising:
a spool defining an axis and including a thrust bearing supporting a hub and a compressor mechanically coupled to a turbine by said hub;
a first non-contacting dynamic seal including a first body attached to a first floating shoe configured to seal first rotatable inner surfaces of said spool to define a first flow cavity, the first floating shoe radially inward of said first rotatable inner surfaces with respect to said axis;
a second non-contacting dynamic seal including a second body attached to a second floating shoe configured to seal second rotatable inner surfaces of said spool to define a second flow cavity, the second floating shoe radially inward of said second rotatable inner surfaces with respect to said axis; and
a third non-contacting dynamic seal including a third body attached to a third floating shoe configured to seal rotatable outer surfaces of said hub and is positioned in an axial direction relative to said axis between said first and second floating shoes to define said first flow cavity and said second flow cavity, the third floating shoe radially outward of said rotatable outer surfaces with respect to said axis; and
wherein each of said first non-contacting dynamic seal, said second non-contacting dynamic seal and said third non-contacting dynamic seal is a hydrostatic seal.

2. The gas turbine engine as recited in claim 1 , wherein said first flow cavity and said second flow cavity are dimensioned in a radial direction with respect to said axis to reduce net thrust loads exerted on said thrust bearing.

3. The gas turbine engine as recited in claim 1 , wherein each of said first and second non-contacting dynamic seals are positioned radially outward of said third non-contacting dynamic seal with respect to said axis.

4. The gas turbine engine as recited in claim 3 , wherein each of said first, second and third floating shoes is moveable in a radial direction with respect to said axis in response to rotating at least one of said first rotatable inner surfaces, said second rotatable inner surfaces and said outer rotatable surfaces.

5. The gas turbine engine as recited in claim 1 , wherein said first flow cavity and said second flow cavity are positioned axially between said compressor and said turbine.

6. The gas turbine engine as recited in claim 1 , wherein each of said first body, said second body, and said third body is fixedly attached to and extends from a static structure of said spool.

7. The gas turbine engine as recited in claim 6 , wherein said third non-contacting dynamic seal is positioned radially between an outer shaft of said spool and an inner diffuser case, said third body of said third non-contacting dynamic seal extends from and is fixedly attached to said inner diffuser case, and said rotatable outer surfaces are located along said outer shaft.

8. The gas turbine engine as recited in claim 7 , wherein said second non-contacting dynamic seal is positioned radially inboard of a high pressure turbine vane, and said second rotatable inner surfaces are located along a platform of a turbine blade.

9. The gas turbine engine as recited in claim 7 , wherein said second non-contacting dynamic seal is positioned aft of a high pressure turbine rotor of said spool.

10. The gas turbine engine as recited in claim 7 , wherein said second non-contacting dynamic seal is positioned radially inboard of a high pressure turbine vane, said second rotatable inner surfaces are located along a platform of said high pressure turbine vane, and said first non-contacting dynamic seal is positioned forward of said turbine.

11. The gas turbine engine as recited in claim 1 , wherein each of said second non-contacting dynamic seal and said third non-contacting dynamic seal is positioned aft of a high pressure compressor of said spool.

12. The gas turbine engine as recited in claim 11 , wherein said first non-contacting dynamic seal is positioned radially inboard of a high pressure compressor vane, and said first rotatable inner surfaces are located along a platform of a compressor blade.

13. The gas turbine engine as recited in claim 12 , wherein said third non-contacting dynamic seal is positioned between an outer shaft of said spool and an inner diffuser case.

14. The gas turbine engine as recited in claim 11 , wherein each of said first non-contacting dynamic seal, said second non-contacting dynamic seal and said third non-contacting dynamic seal is positioned forward of a high pressure turbine of said spool.

15. The gas turbine engine as recited in claim 1 , further comprising a low spool along an axis of said spool.

16. The gas turbine engine as recited in claim 15 , wherein said gas turbine engine is a high bypass engine.

17. The gas turbine engine as recited in claim 16 , further comprising a geared architecture driven by said low spool.

Assignees

• Caprario Joseph T
• United Technologies Corp

Inventors

• Caprario Joseph T

Classifications

• F02C7/28

  Arrangement of seals · CPC title

• F01D11/025

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

• F05D2260/15

  Load balancing · CPC title

• F01D5/081

  Cooling fluid being directed on the side of the rotor disc or at the roots of the blades (F01D5/087 takes precedence) · CPC title

• F05D2240/55

  Seals · CPC title