Turbomachine fan casing assembly

Patent metadata

Field	Value
Publication number	US-9810096-B2
Application number	US-201514657601-A
Country	US
Kind code	B2
Filing date	Mar 13, 2015
Priority date	Mar 26, 2014
Publication date	Nov 7, 2017
Grant date	Nov 7, 2017

Abstract

A turbomachine casing assembly including an inner casing element for arrangement radially outward of a turbomachine fan; an outer casing element for arrangement radially further outward of the turbomachine fan; a retaining lip arranged radially inward of a portion of the inner casing element; and a separator extending between the inner and outer casing elements and arranged to urge a portion of the inner casing element against the lip. The separator is arranged in compression between the inner and outer casing elements to urge the portion of the inner casing element against the lip. The separator is arranged to engage a frangible region of the inner casing element such that the frangible region is configured to break in response to an impact satisfying predetermined conditions, allowing the inner casing element to displace radially outwards exposing features to improve retention of a released fan blade.

First claim

The invention claimed is:

1. A turbomachine casing assembly comprising:
an inner casing element for arrangement radially outward of a turbomachine fan;
an outer casing element for arrangement radially further outward of the turbomachine fan;
a retaining lip arranged radially inward of at least a region of the inner casing element;
a separator located downstream of the retaining lip extending between the inner and outer casing elements, and the seperator arranged to urge a portion of the inner casing element against the lip;
wherein the separator is arranged to engage a frangible region of the inner casing element such that the frangible region is configured to break in preference to the separator.

2. The turbomachine casing assembly according to claim 1 , wherein the separator is arranged in compression between the inner and outer casing elements to urge the portion of the inner casing element against the lip.

3. The turbomachine casing assembly according to claim 1 , wherein the separator is arranged to engage the frangible region of the inner casing element such that the frangible region is configured to break in response to an impact satisfying predetermined conditions.

4. The turbomachine casing assembly according to claim 3 , wherein breaking the frangible region allows the inner casing element to disengage from the lip and move towards the outer casing element.

5. The turbomachine casing assembly according to claim 4 , wherein the separator is arranged to pass through the broken frangible region as the inner casing element moves towards the outer casing element.

6. The turbomachine casing assembly according claim 3 , wherein in response to a fan blade-off event, the separator breaks the frangible region to allow the inner casing element to disengage from the lip and to move towards the outer casing element.

7. The turbomachine casing assembly according claim 3 , wherein the frangible region of the inner casing element is configured to be structurally weaker than a surrounding region of the inner casing element to facilitate breaking of the frangible region in response to said impact.

8. The turbomachine casing assembly according to claim 3 , wherein the separator includes:
a separating leg arranged to extend between the inner and outer casing elements, and
a clamping sub-assembly arranged to couple the separating leg to the frangible region of the inner casing element.

9. The turbomachine casing assembly according to claim 8 , wherein the clamping sub-assembly includes a sleeve defining a passageway through the inner casing element, the separating leg extending at least partway along the passageway and being adapted for complementary locking engagement with the sleeve.

10. The turbomachine casing assembly according to claim 9 , wherein an inner surface of the sleeve, at least partially defining the passageway, is threaded for complementary engagement with a threaded surface of the separating leg.

11. The turbomachine casing assembly according to claim 8 , wherein the clamping sub-assembly is arranged to clamp, between mutually opposing flange elements, at least a portion of the inner casing element.

12. The turbomachine casing assembly according to claim 11 , wherein a radially innermost flange of the mutually opposing flange elements is a collar provided integrally with the sleeve.

13. The turbomachine casing assembly according to claim 11 , wherein a radially outermost flange of the mutually opposing flange elements is a body movable along an outer surface of the sleeve, adapted for complementary locking engagement with the sleeve to be capable of clamping a region of the inner casing element between itself and a radially innermost flange of the mutually opposing flange elements.

14. The turbomachine casing assembly according claim 11 , wherein a radially outermost flange of the mutually opposing flange elements is a threaded nut for complementary engagement with a threaded outer surface of the sleeve.

15. The turbomachine casing assembly according to claim 8 , wherein the clamping sub-assembly includes a breaking member, adapted to cause the breaking of the frangible region in response to said impact.

16. The turbomachine casing assembly according to claim 14 , wherein the nut is configured to include one or more sharpened ridges engageable with the inner casing element.

17. The turbomachine casing assembly according to claim 8 , wherein the separating leg extends at a non-radial angle relative to the axis of the casing assembly.

18. The turbomachine casing assembly according to claim 8 , wherein the inner casing element is a fan track liner panel, and the clamping sub-assembly is arranged to clamp only a septum of the panel.

19. A turbomachine casing assembly according to claim 8 , wherein the inner casing element is a fan track liner panel, and the clamping sub-assembly is arranged to clamp a portion of a tray liner holding a honeycomb structure and a septum of the panel.

20. A gas turbine engine comprising the turbomachine casing assembly according to claim 1 .

Assignees

• Rolls Royce Plc

Inventors

• Evans Dale Edward
• Christmas David Laker

Classifications

• F01D25/26 Primary

  Double casings; Measures against temperature strain in casings · CPC title

• F05D2220/36

  specially adapted for the fan of turbofan engines · CPC title

• F01D25/28

  Supporting or mounting arrangements, e.g. for turbine casing · CPC title

• F05D2230/51

  in a modular way, e.g. using several identical or complementary parts or features · CPC title

• F01D21/045

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