Reinforced fan containment case for a gas turbine engine

Patent metadata

Field	Value
Publication number	US-10655500-B2
Application number	US-201615351009-A
Country	US
Kind code	B2
Filing date	Nov 14, 2016
Priority date	Sep 6, 2016
Publication date	May 19, 2020
Grant date	May 19, 2020

Abstract

A fan containment case for a gas turbine engine is provided which includes a barrel having an outermost portion, an innermost portion, and an interior portion in-between the outermost portion and the innermost portion. The outermost portion has an outermost band of material made of carbon fiber composite and the innermost portion has an innermost band of material made of carbon fiber composite. The interior portion includes a first interior band and a second interior band adjacent the first interior band. The first interior band is made of poly p-phenylene-2,6-benzobisoxazole (PBO) and the second interior band is made of an aramid material. The innermost portion has an innermost band of material made of carbon fiber composite.

First claim

I claim:

1. A fan containment case for a gas turbine engine comprising:
a barrel comprising an outermost portion, an innermost portion, and an interior portion in-between the outermost portion and the innermost portion;
an outermost band of material of the outermost portion, wherein the outermost band is made of carbon fiber composite;
a first interior band, a second interior band, and a third interior band of the interior portion, wherein the first interior band is disposed between and adjacent to the second and third interior bands, wherein the first interior band is made of poly p-phenylene-2,6-benzobisoxazole (PBO) and the second and third interior bands are made of an aramid material; and
an innermost band of material of the innermost portion, wherein the innermost band is made of carbon fiber composite;
wherein the second interior band is adjacent the outermost band and the third interior band is adjacent the innermost band.

2. The fan containment case of claim 1 , wherein the second and third interior bands are made of one of a para-aramid and meta-aramid material.

3. The fan containment case of claim 2 , wherein the second and third interior bands comprise a honeycomb structure.

4. The fan containment case of claim 1 , wherein a thickness of the first interior band is substantially less than a thickness of the innermost band and a thickness of the outermost band.

5. The fan containment case of claim 1 , wherein the innermost band of the innermost portion comprises a first innermost band and the innermost portion further comprises a second innermost band made of PBO, and wherein the first innermost band is embedded and disposed between the interior portion and the second innermost band.

6. The fan containment case of claim 1 , wherein the barrel includes along an axial extent thereof a forward portion, a middle portion, and an aft portion, and wherein the forward portion and the aft portion are thinner than the middle portion.

7. The fan containment case of claim 6 , wherein each of the forward portion and the aft portion is reduced in thickness with distance away from the middle portion, and wherein the interior portion is disposed in the middle portion of the barrel.

8. The fan containment case of claim 6 , wherein each of the outermost portion, the interior portion, and the innermost portion is selectively located in a projected path of a fan blade-out such that a failed blade of the gas turbine engine is adapted to be impacted onto the selected location of the outermost, interior, and innermost portions.

9. The fan containment case of claim 2 , wherein the outermost band and the innermost band each comprises multiple layers of carbon fiber composite, and wherein the first interior band comprises multiple layers of PBO composite.

10. A gas turbine engine, comprising:
a fan containment case including a barrel comprising an outermost portion, an innermost portion, and an interior portion in-between the outermost portion and the innermost portion;
an outermost band of material of the outermost portion, wherein the outermost band is made of carbon;
a first interior band, a second interior band, and a third interior band of the interior portion, wherein the first interior band is disposed between and adjacent to the second and third interior bands, wherein the first interior band is made of poly p-phenylene-2,6-benzobisoxazole (PBO) and the second and third interior bands are made of an aramid material; and
an innermost band of material of the innermost portion, wherein the innermost band is made of carbon;
wherein the second interior band is adjacent the outermost band and the third interior band is adjacent the innermost band.

11. The gas turbine engine of claim 10 , wherein the second and third interior bands are made of one of a para-aramid and meta-aramid material.

12. The gas turbine engine of claim 11 , wherein the second and third interior band comprise bands comprise a honeycomb structure.

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

14. The gas turbine engine of claim 13 , wherein a thickness of the first interior band is substantially less than a thickness of the innermost band and a thickness of the outermost band.

15. The gas turbine engine of claim 13 , wherein the innermost band comprises a first innermost band and the interior portion further comprises a second innermost band made of PBO, and wherein the first innermost band is embedded and disposed between the interior portion and the second innermost band.

16. The gas turbine engine of claim 10 , 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, wherein each of the forward portion and the aft portion is reduced in thickness with distance away from the middle portion, and wherein the interior portion is disposed in the middle portion of the barrel.

17. The gas turbine engine of claim 16 , wherein a thickness of each of the outermost and innermost bands is at least as thick as a thickness of the interior portion.

18. The gas turbine engine of claim 15 , wherein each of the outermost portion, the interior portion, and the innermost portion is selectively located in a projected path of a fan blade-out such that a failed blade of the gas turbine engine is adapted to be impacted onto the selected location of the outermost, interior, and innermost portions.

Assignees

• Rolls Royce Corp

Inventors

• Heeter Robert W

Classifications

• B32B2262/02

  Synthetic macromolecular fibres · CPC title

• F05D2300/603

  Composites; e.g. fibre-reinforced · CPC title

• F05D2300/224

  Carbon, e.g. graphite · CPC title

• B32B2250/42

  Alternating layers, e.g. ABAB(C), AABBAABB(C) · CPC title

• B32B2605/18

  Aircraft · CPC title