Composite case armor for jet engine fan case containment

• US 8,016,543 B2
• Filed: 04/02/2007
• Issued: 09/13/2011
• Est. Priority Date: 04/02/2007
• Status: Active Grant

• Current Assignee: A & P Technology Inc., United States Of America As Represented By The Administrator Of The National Aeronautics And Space Administration, Williams International Company LLC
• Original Assignee: A & P Technology Inc.
• Inventors: Roberts, Gary D., Dorer, James D., Braley, Michael Scott
• Primary Examiner(s): Look; Edward
• Assistant Examiner(s): Eastman; Aaron R
• Application Number:
  US11/695,435
• Publication Number:
  US 20090067979A1
• Time in Patent Office: 1,625 Days
• Field of Search: 415/9, 415/108, 415/170.1, 415/173.1, 415/173.4, 415/173.6, 415/174.4, 415/196, 415/197, 415/200, 415/215.1
• US Class Current: 415/9
• CPC Class Codes: F01D 21/045 special arrangements in stators or in rotors dealing with breaking-off of part of rotor
• CPC Class Codes: F02C 7/05 having provisions for obviating the penetration of damaging objects or particles
• 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

A gas turbine fan blade containment assembly includes a fan case having an inner surface surrounding a jet engine fan and an outer surface. Mounted on the inner surface and across a blade containing region of the fan case is a load spreader layer for initially receiving a point load from a fan blade release (a “blade-out event”). A band layer is mounted to an outer surface of the fan case for carrying at least a portion of a hoop tensile load on the fan case resulting from the blade-out event, and separator film layer is mounted between the outer surface of the fan case and the band layer to retard the formation of stress concentrations in the band layer. In one embodiment, the load spreader layer includes a plurality of circumferentially-arrayed load spreader layer segments.

Claims

1. A fan blade containment assembly for a gas turbine engine, comprising:

a fan case having an inner surface for surrounding a fan mounted for rotation about an engine axis and an outer surface, the fan case in addition having a circumferentially and axially extending blade containing region; and

a first load spreader layer attached in contacting engagement with the fan case inner surface and located within the blade containing region;

wherein in response to a blade-out event, the first load spreader layer mitigates cutting and gouging of the inner surface of the fan case by a fan blade released during the blade-out event, and acts as a point load spreader to distribute a point load to the fan case that is generated on the first load spreader layer by the released blade, and

a first band layer mounted to the fan case outer surface in proximity to the blade containing region, wherein the first band layer is capable of carrying at least a portion of a hoop tensile load on the fan case that results from the blade-out event.

2. The fan blade containment assembly according to claim 1, wherein the first load spreader layer includes a plurality of load spreader segments circumferentially arrayed within the blade containing region and positioned to define a plurality of gaps between ends of adjacent ones of the plurality of load spreader segments, wherein each load spreader segment is capable of acting as a point load spreader to isolate and uniformly distribute a point load to the fan case that is generated on the first load spreader segment as the result of a blade-out event.

3. The fan blade containment assembly according to claim 2, wherein each of the plurality of first load spreader segments has an arcuate length ranging between 1/14 and 1/10 of the circumference of the first load spreader layer.

4. The fan blade containment assembly according to claim 2, wherein the ends of each load spreader segment are canted at an angle greater than 0 degrees and less than 90 degrees.

5. The fan blade containment assembly according to claim 4, wherein the ends of each load spreader segment are canted at an angle ranging between 30 degrees and 50 degrees.

6. The fan blade containment assembly according to claim 1, wherein the fan case comprises a material selected from the group consisting of fiber-reinforced polymers and metals, wherein the fiber-reinforced polymers comprise one or more of carbon braid, cloth fiber or triaxial braid, and wherein the triaxial braid includes one or more of carbon fibers, quartz fibers, glass fibers or aramid fibers.

7. The fan blade containment assembly according to claim 1, wherein the first load spreader layer comprises a material selected from the group consisting of fiber-reinforced polymers, non-reinforced polymers, ceramics and metals.

8. The fan blade containment assembly according to claim 1, wherein the first band layer comprises a material selected from the group consisting of fiber-reinforced polymers, cloth fiber, wound fiber, biaxial braid and triaxial braid, wherein the biaxial braid and the triaxial braid each include one or more of carbon fibers, quartz fibers, glass fibers or aramid fibers.

9. The fan blade containment assembly according to claim 1, wherein the blade containing region of the fan case has a circular cross-section.

10. The fan blade containment assembly according to claim 1, further comprising:

at least a second band layer mounted to an outer surface of the first band layer and extending across the blade containing region.

11. A fan blade containment assembly for a gas turbine engine comprising:

a fan case having an inner surface for surrounding a fan mounted for rotation about an engine axis and an outer surface, the fan case in addition having a circumferentially and axially extending blade containing region; and

a first load spreader layer attached to the fan case inner surface and located within the blade containing region;

wherein in response to a blade-out event, the first load spreader layer mitigates cutting and gouging of the inner surface of the fan case by a fan blade released during the blade-out event, and acts as a point load spreader to distribute a point load to the fan case that is generated on the first load spreader layer by the released blade,

a first band layer mounted to the fan case outer surface in proximity to the blade containing region, wherein the first band layer is capable of carrying at least a portion of a hoop tensile load on the fan case that results from the blade-out event, further comprising

a separator film layer mounted between the fan case outer surface and the first band layer, wherein the separator film layer is capable of retarding the formation of stress concentrations in the first band layer as a result of the blade-out event.

12. A fan blade containment assembly for a gas turbine engine comprising:

a fan case having an inner surface for surrounding a fan mounted for rotation about an engine axis and an outer surface, the fan case in addition having a circumferentially and axially extending blade containing region; and

a first load spreader layer attached to the fan case inner surface and located within the blade containing region;

wherein in response to a blade-out event, the first load spreader layer mitigates cutting and gouging of the inner surface of the fan case by a fan blade released during the blade-out event, and acts as a point load spreader to distribute a point load to the fan case that is generated on the first load spreader layer by the released blade, further comprising

a second load spreader layer mounted to an inner surface of the first load spreader layer and located within the blade containing region.

13. The fan blade containment assembly according to claim 12, wherein the first load spreader layer includes a plurality of load spreader segments circumferentially arrayed within the blade containing region and positioned to define a plurality of gaps between ends of adjacent ones of the plurality of load spreader segments, wherein each load spreader segment is capable of acting as a point load spreader to isolate and uniformly distribute a point load to the fan case that is generated on the first load spreader segment as the result of a blade-out event, further comprising:

the second load spreader layer including a plurality of second load spreader segments circumferentially arrayed within the blade containing region and positioned to define a plurality of gaps between ends of adjacent ones of the plurality of second load spreader segments.

14. The fan blade containment assembly according to claim 13, wherein each of the first load spreader segments and the second load spreader elements has an arcuate length, and the second load spreader segments are positioned so that the gaps defined between ends of adjacent ones of the second load spreader segments fall along the arcuate lengths of the first load spreader segments.

15. The fan blade containment assembly according to claim 13, further comprising:

at least a third load spreader layer mounted to an inner surface of the second load spreader layer and located within the blade containing region;

the third load spreader layer including a plurality of third load spreader segments circumferentially arrayed within the blade containing region and positioned to define a plurality of gaps between ends of adjacent ones of the plurality of third load spreader segments.

16. The fan blade containment assembly according to claim 13, wherein the first load spreader segments comprise a material selected from the group consisting of polymers and polycarbonates, and the second load spreader segments comprise a material selected from the group consisting of steels and ceramics.

17. The fan blade containment assembly according to claim 12, wherein the first load spreader layer comprises a material selected from the group consisting of polymers and polycarbonates, and the second load spreader layer comprises a material selected from the group consisting of steels and ceramics.

18. A fan blade containment assembly for a gas turbine engine comprising:

a fan case having an inner surface for surrounding a fan mounted for rotation about an engine axis and an outer surface, the fan case in addition having a circumferentially and axially extending blade containing region; and

a first load spreader layer attached to the fan case inner surface and located within the blade containing region;

wherein in response to a blade-out event, the first load spreader layer mitigates cutting and gouging of the inner surface of the fan case by a fan blade released during the blade-out event, and acts as a point load spreader to distribute a point load to the fan case that is generated on the first load spreader layer by the released blade,

a first band layer mounted to the fan case outer surface in proximity to the blade containing region, wherein the first band layer is capable of carrying at least a portion of a hoop tensile load on the fan case that results from the blade-out event,

at least a second band layer mounted to an outer surface of the first band layer and extending across the blade containing region, further comprising

a separator film layer mounted between the first band layer and the at least second band layer.

19. A fan blade containment assembly for a gas turbine engine, comprising:

a fan case having an inner surface for surrounding a fan mounted for rotation about an engine axis and an outer surface, the fan case in addition having a circumferentially and axially extending blade containing region;

at least one load spreader layer attached to the fan case inner surface and located within the blade containing region;

at least one band layer mounted to the fan case outer surface in proximity to the blade containing region, and

a separator film layer mounted between the fan case outer surface and the at least one band layer,

wherein in response to a blade-out event, the at least one load spreader layer mitigates cutting and gouging of the inner surface of the fan case by a fan blade released during the blade-out event and acts as a point load spreader to distribute a point load to the fan case that is generated on the first load spreader layer by the released blade, wherein the at least one band layer is capable of carrying at least a portion of a hoop tensile load that is generated in the fan case from the blade-out event, and wherein the separator film layer is capable of retarding the formation of stress concentrations in the first band layer as a result carrying the portion of the hoop tensile load.

20. The fan blade containment assembly according to claim 19, wherein the at least one load spreader layer includes a plurality of load spreader segments circumferentially arrayed within the blade containing region and positioned to define a plurality of gaps between ends of adjacent ones of the plurality of load spreader segments, wherein each load spreader segment is capable of acting as a point load spreader to isolate and uniformly distribute a point load to the fan case that is generated on the first load spreader segment as the result of a blade-out event.