Fan blade containment system for gas turbine engine

Patent metadata

Field	Value
Publication number	US-11118472-B2
Application number	US-201916399138-A
Country	US
Kind code	B2
Filing date	Apr 30, 2019
Priority date	Oct 18, 2018
Publication date	Sep 14, 2021
Grant date	Sep 14, 2021

Abstract

A fan blade containment system is arranged to surround a fan including a plurality of fan blades in a gas turbine engine for an aircraft. The fan blade containment system includes a composite fan case arranged to surround the fan; and a metallic insert mounted on the composite fan case and including a metallic hook arranged to prevent forward debris release should all or part of a fan blade become detached from the fan.

First claim

The invention claimed is:

1. A fan blade containment system for surrounding a fan comprising a plurality of fan blades in a gas turbine engine for an aircraft, the fan blade containment system comprising:
a composite fan case; and
a metallic insert mounted on the composite fan case and comprising:
a first metallic hook arranged to prevent forward debris release should all or part of one of the plurality of fan blades become detached from the fan when the fan blade containment system is installed in the gas turbine engine;
a first trap door having a forward edge and a rearward edge, the first trap door being detachably connected to the metallic insert at its forward edge such that a forward region of the first trap door can move toward the fan case if struck when the fan blade containment system is installed in the gas turbine engine; and
a protection portion that extends in a rearward direction from the first metallic hook and terminates in the rearward direction before reaching the rearward edge of the first trap door.

2. The fan blade containment system of claim 1 , wherein the metallic insert is mounted on the composite fan case by means of an adhesive layer arranged to account for differences in Coefficient of Thermal Expansion between the metallic insert and the composite fan case.

3. The fan blade containment system of claim 1 , wherein the metallic insert further comprises a second metallic hook, the second metallic hook being located forward of the first metallic hook.

4. The fan blade containment system of claim 3 , wherein the metallic insert further comprises a second trap door located forward of the first metallic hook and having a forward edge and a rearward edge, the second trap door being detachably connected to the metallic insert at its forward edge such that a forward region of the second trap door can move toward the fan case if struck when the fan blade containment system is installed in the gas turbine engine.

5. The fan blade containment system of claim 4 , wherein the second trap door is arranged to be detachably connected to the second metallic hook at the forward edge of the second trap door.

6. The fan blade containment system of claim 4 , wherein the second trap door is arranged to be detachably connected to the metallic insert by a frangible connector, the frangible connector being arranged to break in response to pressure applied by a released blade or blade fragment when the fan blade containment system is installed in the gas turbine engine.

7. The fan blade containment system of claim 4 , wherein the second trap door extends from forward of the first metallic hook to adjacent the second metallic hook and is configured to facilitate the detached all or part of the one of the plurality of fan blades engaging the second metallic hook when the fan blade containment system is installed in the gas turbine engine.

8. The fan blade containment system of claim 3 , wherein the second metallic hook is arranged to arrest forward motion of the detached all or part of the one of the plurality of fan blades when the fan blade containment system is installed in the gas turbine engine.

9. The fan blade containment system of claim 3 , wherein the second metallic hook is located between 10 cm and 50 cm forward of the first metallic hook.

10. The fan blade containment system of claim 3 , wherein the second metallic hook is located at a forward edge of the fan case.

11. The fan blade containment system of claim 3 , wherein at least one of the first metallic hook and the second metallic hook comprises a fence extending around an internal circumference of the fan case, the fence extending inwardly from the fan case.

12. The fan blade containment system of claim 11 , wherein at least one of the first metallic hook and the second metallic hook comprises a lip extending rearwardly from the fence, the lip extending circumferentially and spaced inwardly from the fan case.

13. The fan blade containment system of claim 12 , wherein the lip of either or both of the first metallic hook and the second metallic hook extends axially rearwardly.

14. The fan blade containment system of claim 12 , wherein the lip of either or both of the first metallic hook and the second metallic hook extends rearwardly from an inward end region of the corresponding fence.

15. The fan blade containment system of claim 12 wherein the lip of either or both of the first metallic hook and the second metallic hook extends rearwardly from the corresponding fence by between 3 mm and 10 mm.

16. The fan blade containment system of claim 11 wherein the fence of either or both debris retainers extends inwardly from the fan case by between 40 mm and 60 mm.

17. The fan blade containment system of claim 11 , wherein the fence of either or both of the first metallic hook and the second metallic hook extends radially inward from the fan case.

18. The fan blade containment system of claim 1 , wherein the metallic insert is arranged to be mounted on an inner surface of the composite fan case.

19. The fan blade containment system of claim 1 , wherein the first trap door is arranged to be detachably connected to the first metallic hook at the forward edge of the first trap door.

20. The fan blade containment system of claim 1 wherein the first trap door is arranged to be detachably connected to the metallic insert by a frangible connector, the frangible connector being arranged to break in response to pressure applied by a released blade or blade fragment when the fan blade containment system is installed in the gas turbine engine.

21. The fan blade containment system of claim 1 , wherein the metallic insert is mounted by one or more through-case fasteners.

22. A gas turbine engine for an aircraft comprising:
a fan comprising a plurality of fan blades; and
a fan blade containment system according to claim 1 surrounding the fan.

23. The fan blade containment system of claim 1 , wherein the first metallic hook is configured to be located between 1 cm and 15 cm forward of leading edge tips of the fan blades when the fan blade containment system is installed in the gas turbine engine.

24. The fan blade containment system of claim 1 , wherein the first trap door extends from rearward of the fan to adjacent the first metallic hook and is configured to facilitate the detached all or part of the one of the plurality of fan blades engaging the first metallic hook when the fan blade containment system is installed in the gas turbine engine.

25. A metallic insert for mounting on a composite fan case surrounding a fan comprising a plurality of fan blades in a gas turbine engine for an aircraft, the metallic insert comprising:
a first metallic hook arranged to prevent forward debris release should all or part of one of the plurality of fan blades become detached from the fan when the metallic insert is mounted on the composite fan case;
a first trap door having a forward edge and a rearward edge, the first trap door being detachably connected to the metallic insert at its forward edge such that a forward region of the first trap door can move toward the fan case if struck when the metallic insert is mounted on the composite fan case; and
a protection portion that extends in a rearward direction from the first metallic hook and terminates in the rearward direction before reaching the rearward edge of the first trap door.

26. The metallic insert of

Assignees

• Rolls Royce Plc

Inventors

• Finlayson James A
• Reed Julian M

Classifications

• F05D2240/14

  Casings or housings protecting or supporting assemblies within · CPC title

• F05D2260/96

  Preventing, counteracting or reducing vibration or noise · CPC title

• F01D25/24

  Casings (modified for heating or cooling F01D25/14); Casing parts, e.g. diaphragms, casing fastenings (casings for rotary machines or engines in general F16M {; special arrangements in stators dealing with breaking-off of part of rotor F01D21/045}) · CPC title

• F05D2250/283

  honeycomb · CPC title

• F01D21/045 Primary

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