Turbine wheel catcher

Patent metadata

Field	Value
Publication number	US-9163525-B2
Application number	US-201213534085-A
Country	US
Kind code	B2
Filing date	Jun 27, 2012
Priority date	Jun 27, 2012
Publication date	Oct 20, 2015
Grant date	Oct 20, 2015

Abstract

A catcher for a gas turbine engine includes a central hub, a plurality of struts, and a first ring. The plurality of struts are connected to and extend outward from the central hub. The first ring is connected to a mid-section of the plurality of struts and extends therebetween.

First claim

The invention claimed is:

1. A gas turbine engine comprising:
a compressor impeller;
a turbine wheel connected to the compressor impeller, wherein the turbine wheel has a center section with a first radial extent at a forward end and second radial extent at an aft end, the second radial extent being less than the first radial extent; and
an exhaust housing positioned adjacent an outer perimeter of the turbine wheel, wherein the exhaust housing forms an outer boundary for a flow path directly aft of the turbine wheel;
a catcher positioned axially aft of and spaced at a distance from the turbine wheel, wherein the catcher comprises:
a central hub positioned directly aft of the turbine wheel, wherein the central hub has a radial extent substantially matching the second radial extent;
a plurality of struts connected to and extending outward from the central hub;
a first ring connected to the plurality of struts and extending therebetween wherein the first ring is positioned within a flow path of the gas turbine engine aft of the turbine wheel and in a radial position between the first radial extent and the second radial extent; and
a second ring positioned generally radially outward of the first ring and connected both to outer radial ends of the plurality of struts and to an inner perimeter of the exhaust housing, wherein the second ring has an inner radial surface positioned along the flow path of the gas turbine engine aft of the turbine wheel.

2. The gas turbine engine of claim 1 , wherein the second ring is connected to the exhaust housing of the gas turbine engine.

3. The gas turbine engine of claim 1 , wherein the first ring is connected to a mid-section of the plurality of struts.

4. The gas turbine engine of claim 1 , wherein the first ring is shaped as an airfoil.

5. The gas turbine engine of claim 1 , wherein the struts are tilted with respect to a direction of airflow along the gas turbine engine.

6. The gas turbine engine of claim 1 , wherein the central hub has a hollow interior.

7. The gas turbine engine of claim 1 , wherein the first ring has a leading edge and the second ring has a forward edge and, wherein the leading edge of the first ring is positioned aft of the forward edge of the second ring.

8. The gas turbine engine of claim 1 , wherein the turbine wheel is a centrifugal turbine wheel.

9. A turbine wheel catcher assembly for use in a gas turbine engine comprising:
a turbine wheel having a center section with a first radial extent at a forward end and second radial extent at an aft end, the second radial extent being less than the first radial extent;
an exhaust housing positioned adjacent the turbine wheel, wherein the exhaust housing forms an outer boundary for a flow path directly aft of the turbine wheel; and
a catcher comprising:
a central hub positioned directly aft of the turbine wheel, wherein the central hub has a radial extent substantially matching the second radial extent;
a plurality of struts connected to and extending outward from the central hub;
a first ring connected to a mid-section of the plurality of struts and extending therebetween, and wherein the first ring is positioned within the flow path aft of the turbine wheel and in a radial position between the first radial extent and the second radial extent; and
a second ring positioned generally radially outward of the first ring and connected both to outer radial ends of the plurality of struts and to an inner perimeter of the exhaust housing, wherein the second ring has an inner radial surface positioned along the flow path aft of the turbine wheel.

10. The turbine wheel catcher assembly of claim 9 , wherein the first ring is shaped as an airfoil.

11. The turbine wheel catcher assembly of claim 9 , wherein the struts, first ring, and central hub of the catcher act to impede or substantially reduce a speed of aft axial movement of the turbine wheel in the event of a catastrophic failure of the turbine wheel.

12. The turbine wheel catcher assembly of claim 9 , wherein the struts are tilted with respect to a direction of airflow along the catcher.

13. The turbine wheel catcher assembly of claim 9 , wherein the central hub has a hollow interior.

14. The turbine wheel catcher assembly of claim 9 , wherein an outer perimeter surface of the second ring abuts an inner perimeter surface of the exhaust housing.

15. The turbine wheel catcher assembly of claim 9 , wherein the second ring is hoop-shaped.

16. The turbine wheel catcher assembly of claim 9 , wherein the first ring has a leading edge and the second ring has a forward edge and, wherein the leading edge of the first ring is positioned aft of the forward edge of the second ring.

17. The turbine wheel catcher assembly of claim 9 , wherein the turbine wheel is a centrifugal turbine wheel.

18. A turbine wheel catcher assembly for a gas turbine engine, comprising:
a turbine wheel having a center section with a first radial extent at a forward end and second radial extent at an aft end, the second radial extent being less than the first radial extent;
an exhaust housing positioned adjacent an outer perimeter of the turbine wheel, wherein the exhaust housing forms an outer boundary for a flow path directly aft of the turbine wheel;
a central hub positioned directly aft of the turbine wheel, wherein the central hub has a radial extent substantially matching the second radial extent;
a plurality of struts connected to and extending outward from the central hub, wherein the struts are tilted with respect to a direction of airflow along the gas turbine engine;
a first ring connected to a mid-section of the plurality of struts and extending therebetween, wherein the first ring is positioned within a flow path aft of the turbine wheel and in a radial position between the first radial extent and the second radial extent; and
a second ring positioned generally radially outward of the first ring and connected both to outer radial ends of the plurality of struts and to an inner perimeter of the exhaust housing, wherein the second ring has an inner radial surface positioned along the flow path aft of the turbine wheel.

19. The turbine wheel catcher assembly of claim 18 , wherein the turbine wheel is a centrifugal turbine wheel.

Assignees

• Alexander Eric J
• Hagshenas Behzad
• Elgin Richard L
• United Technologies Corp

Inventors

• Alexander Eric J
• Hagshenas Behzad
• Elgin Richard L

Classifications

• F05D2220/3215

  the last stage of the turbine · CPC title

• F05D2220/50

  for auxiliary power units (APU's) · CPC title

• F01D21/045

  special arrangements in stators or in rotors dealing with breaking-off of part of rotor · CPC title

• F01D25/00 Primary

  Component parts, details, or accessories, not provided for in, or of interest apart from, other groups · CPC title

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title