Fan containment case for a gas turbine engine

• US 10,641,287 B2
• Filed: 09/06/2016
• Issued: 05/05/2020
• 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: Kappes, Matthew J., Heeter, Robert W., Hodgson, Benedict N.
• Primary Examiner(s): Seabe, Justin D
• Assistant Examiner(s): Corday, Cameron A
• Application Number:
  US15/257,206
• Publication Number:
  US 20180066675A1
• Time in Patent Office: 1,337 Days
• Field of Search: 415 9
• 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;

second through sixth bands of material inboard of the first band, wherein each of the second through sixth bands is made of poly p-phenylene-2,6-benzobisoxazole (PBO) composite;

seventh through tenth bands, wherein each of the seventh through tenth bands is made of carbon fiber composite and the seventh band separates the second and third bands, the eight band separates the third and fourth bands, the ninth band separates the fourth and fifth bands, and the tenth band separates the fifth and sixth bands; and

an eleventh band of material inboard of the tenth band, wherein the eleventh band is made of carbon fiber composite.

2. The fan containment case of claim 1, wherein the second through tenth bands are encased by the first band and the eleventh band.

3. The fan containment case of claim 2, wherein the first band and the eleventh band comprise 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 eleventh 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 1, further comprising a twelfth band of material inboard the fifth band of material, wherein the sixth band is made of PBO composite.

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

10. The fan containment case of claim 1, wherein each of the first through eleventh bands 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 through eleventh 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 fiber composite;

second through sixth bands of material inboard of the first band, wherein each of the second through sixth bands is made of poly p-phenylene-2,6-benzobisoxazole (PBO);

seventh through tenth bands, wherein each of the seventh through tenth bands is made of carbon fiber composite and the seventh band separates the second and third bands, the eight bands separates the third and fourth bands, the ninth band separates the fourth and fifth bands, and the tenth band separates the fifth and sixth bands; and

an eleventh band of material inboard of the tenth band, wherein the eleventh-band is made of carbon fiber composite.

12. The gas turbine engine of claim 11, wherein the second through tenth bands are encased by the first band and the eleventh band.

13. The gas turbine engine of claim 12, wherein the first band and the eleventh band comprise 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 eleventh 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 11, further comprising a twelfth band of material inboard the eleventh band of material, wherein the twelfth band is made of dry PBO.

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

20. The gas turbine engine of claim 11, wherein each of the first through eleventh bands 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 through eleventh bands.