Fan Containment Case for a Gas Turbine Engine

• US 20180066675A1
• Filed: 09/06/2016
• Published: 03/08/2018
• Est. Priority Date: 09/06/2016
• Status: Active Grant

• Current Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Original Assignee: Rolls-Royce Corporation (Rolls-Royce Holdings Plc)
• Inventors: Heeter, Robert W., Hodgson, Benedict N., Kappes, Matthew J.
• Granted Patent: US 10,641,287 B2
• Time in Patent Office: Days
• CPC Class Codes: F01D 21/04 responsive to undesired position of rotor relative to stator or to breaking-off of a part of the rotor, e.g. indicating such position
• CPC Class Codes: F02K 3/06 with front fan
• CPC Class Codes: F04D 19/002 Axial flow fans
• CPC Class Codes: F04D 29/164 of an axial flow wheel
• CPC Class Codes: F04D 29/324 Blades
• CPC Class Codes: F04D 29/526 Details of the casing section radially opposing blade tips ducts F04D29/545
• CPC Class Codes: F05D 2220/32 in gas turbines
• CPC Class Codes: F05D 2300/224 Carbon, e.g. graphite
• CPC Class Codes: F05D 2300/603 Composites; e.g. fibre-reinforced
• CPC Class Codes: Y02T 50/60 Efficient propulsion technologies, e.g. for aircraft

Abstract

According to one aspect, a fan containment case for a gas turbine engine is provided which includes a barrel having a first band of material on an outside of the barrel. The first band is made of carbon fiber composite. The barrel further includes a second band of material inboard of the fan case and made of poly p-phenylene-2,6-benzobisoxazole (PBO) composite. The barrel also includes a third band of material made of carbon fiber composite inboard of the second band.

Claims

1. A fan containment case for a gas turbine engine comprising:

a barrel comprising;

a first band of material on an outside of the barrel, wherein the first band is made of carbon fiber composite;

a second band of material inboard of the fan case, wherein the second band is made of poly p-phenylene-2,6-benzobisoxazole (PBO) composite; and

a third band of material inboard of the second band, wherein the third band is made of carbon fiber composite.

2. The fan containment case of claim 1, wherein the second band is embedded and disposed between the first band and the third band.

3. The fan containment case of claim 2, wherein the first band and the third band each comprises multiple layers of carbon fiber composite, and wherein the second band comprises multiple layers of PBO composite.

4. The fan containment case of claim 3, wherein the barrel includes along an axial extent thereof a forward portion, a middle portion, and an aft portion, wherein the forward portion and the aft portion are thinner than the middle portion.

5. The fan containment case of claim 4, wherein each of the forward portion and the aft portion is reduced in thickness with distance away from the middle portion.

6. The fan containment case of claim 4, wherein a thickness of each of the first and third bands is at least as thick as a thickness of the second band.

7. The fan containment case of claim 4, wherein the second band is disposed in the middle portion of the barrel.

8. The fan containment case of claim 4, further comprising a fourth band of material inboard the third band of material, wherein the fourth band is made of PBO composite.

9. The fan containment case of claim 8, further comprising a fan track liner disposed on the fourth band.

10. The fan containment case of claim 1, wherein each of the first band, the second band and the third band is selectively located in a projected path of a fan blade-out such that a failed blade is adapted to be impacted onto the selected location of the first, second, and third bands.

11. A gas turbine engine, comprising:

a fan containment case including a barrel comprising;

a first band of material on an outside of the barrel, wherein the first band is made of carbon;

a second band of material inboard of the fan case, wherein the second band is made of poly p-phenylene-2,6-benzobisoxazole (PBO); and

a third band of material inboard of the second band, wherein the third band is made of carbon.

12. The gas turbine engine of claim 11, wherein the second band is embedded and disposed between the first band and the third band.

13. The gas turbine engine of claim 12, wherein the first band and the third band each comprises multiple layers of carbon fiber composite, and wherein the second band comprises multiple layers of dry PBO.

14. The gas turbine engine of claim 13, wherein the fan containment case is a hardwall containment casing.

15. The gas turbine engine of claim 14, wherein the barrel includes along an axial extent thereof a forward portion, a middle portion, and an aft portion, wherein the forward portion and the aft portion are thinner than the middle portion such that each of the forward portion and the aft portion is reduced in thickness with distance away from the middle portion.

16. The gas turbine engine of claim 14, wherein a thickness of each of the first and third bands is at least as thick as a thickness of the second band.

17. The gas turbine engine of claim 14, wherein the second band is disposed in the middle portion of the barrel.

18. The gas turbine engine of claim 14, further comprising a fourth band of material inboard the third band of material, wherein the fourth band is made of dry PBO.

19. The gas turbine engine of claim 18, further comprising a fan track liner disposed on the fourth band.

20. The gas turbine engine of claim 11, wherein each of the first band, the second band and the third band is selectively located in a projected path of a fan blade-out such that a failed blade is adapted to be impacted onto the selected location of the first, second, and third bands.