Blade containment structure

Claim 2

A blade containment structure surrounding a fan in a fan jet engine comprising: a honeycomb structure spaced radially outwardly from and surrounding the entire tips of blades of said fan; a fabric blanket surrounding said honeycomb structure; said fabric blanket being of a type effective to contain fragments of said blades thrown outward by damage to said fan; said honeycomb structure including an inner honeycomb region having an inner wall and a septum, said septum being an outer wall of said inner honeycomb region and being spaced a predetermined distance radially outward from said inner wall; and said honeycomb structure further including an outer honeycomb region disposed radially outwardly of said inner honeycomb region and being bounded by said septum and an outer wall.

Claim 3

A blade containment structure according to claim 1 wherein said blade containment structure is a portion of a fan casing and said predetermined distance exceeds a maximum radial penetration distance by tips of said blades in a maximum unbalanced condition of said fan whereby said outer honeycomb region remains intact and provides structural strength to said blade containment structure for supporting an inlet cowl attached thereto.

Claim 4

A blade containment structure according to claim 1 wherein said septum is a single layer.

Claim 5

A blade containment structure according to claim 3 wherein said single layer is aluminum.

Claim 6

A blade containment structure according to claim 1 wherein said outer wall is a fiber material in a resin matrix.

Claim 7

A blade containment structure according to claim 5 wherein said fiber is a graphite fiber and said resin matrix is an epoxy resin matrix.

Claim 8

A blade containment structure according to claim 1 wherein said fabric blanket is a plurality of layers of Kevlar fabric.

Claim 9

A blade containment structure according to claim 7 wherein said fabric blanket includes an outer protective shell of Kevlar fabric in an epoxy matrix.

Claim 10

A blade containment structure for surrounding blades of a gas turbine engine comprising: an annular honeycomb structure positionable radially outwardly of the entire axially extent of blade tips of said blades and including: a radially inner honeycomb region bounded by a septum and an inner wall spaced radially inwardly therefrom and being faceable toward said blade tips; and a radially outer honeycomb region bounded by said septum and an outer wall spaced radially outwardly therefrom; and a fabric containment blanket disposed radially outwardly of said outer wall of said second honeycomb region and being of a type effective for containing blade fragments thrown outwardly upon damage to said blades.

Claim 11

A blade containment structure for surrounding blades of a gas turbine engine comprising: an annular honeycomb structure positionable radially outwardly of the entire axially extent of blade tips of said blades and including: a radially inner honeycomb region bounded by a septum and an inner wall spaced radially inwardly therefrom and being faceable toward said blade tips; and a radially outer honeycomb region bounded by said septum and an outer wall spaced radially outwardly therefrom; and a fabric containment blanket disposed radially outwardly of said outer wall of said second honeycomb region and being of a type effective for containing blade fragments thrown outwardly upon damage to said blades.

Claim 12

A blade containment structure according to claim 9 wherein said septum is spaced a predetermined distance radially outwardly from said inner wall so that said outer honeycomb region is not damaged due to orbiting of said blades upon damage thereof and is thereby effective for retaining blade fragments which puncture said inner wall, septum, and outer wall and are contained by said containment blanket.

Claim 13

A blade containment structure according to claim 10 wherein said blade containment structure is effective as a portion of a casing of said engine and said outer honeycomb region including said septum and said outer wall are effective for providing load carry-through to support a second structure of said engine.

Claim 14

A blade containment structure according to claim 9 wherein said inner wall, septum, and outer wall of said honeycomb structure join at axially spaced ends thereof to define an aft flange and a forward flange, said blade containment structure being effective as a portion of an engine casing and being fixedly joinable thereto at said aft flange, said honeycomb structure being effective for providing load carry-through to said forward flange for supporting a second structure of said engine attachable thereto.

Claim 15

A blade containment structure according to claim 12 wherein said casing is a fan casing, said blades are fan blades and said second structure is an inlet cowl.

Claim 16

A blade containment structure according to claim 9 wherein said containment blanket comprises a plurality of layers of Kevlar fabric.

Claim 17

In a gas turbine engine including a fan having a plurality of blades, a fan casing, and an inlet cowl, a fan blade containment structure comprising: an annular honeycomb structure disposed radially outwardly of the entire axial extent of blade tips of said fan blades and including: a radially inner honeycomb region bounded by a septum and an inner wall spaced radially inwardly therefrom and facing toward said blade tips; a radially outer honeycomb region bounded by said septum and an outer wall spaced radially outwardly therefrom; and said inner wall, septum and outer wall being fixedly joined at axially spaced ends thereof to define an aft flange and a forward flange, said aft flange being fixedly joined to said fan casing and said forward flange being fixedly joined to said inlet cowl, said honeycomb structure being effective for providing load carry-through to said forward flange for supporting said inlet cowl to said fan casing; and a fabric containment blanket disposed radially outwardly of said outer wall of said second honeycomb region and being effective for containing blade fragments thrown outwardly upon damage to said blades.

Claim 18

In a gas turbine engine including a fan having a plurality of blades, a fan casing, and an inlet cowl, a fan blade containment structure comprising: an annular honeycomb structure disposed radially outwardly of the entire axial extent of blade tips of said fan blades and including: a radially inner honeycomb region bounded by a septum and an inner wall spaced radially inwardly therefrom and facing toward said blade tips; a radially outer honeycomb region bounded by said septum and an outer wall spaced radially outwardly therefrom; and said inner wall, septum and outer wall being fixedly joined at axially spaced ends thereof to define an aft flange and a forward flange, said aft flange being fixedly joined to said fan casing and said forward flange being fixedly joined to said inlet cowl, said honeycomb structure being effective for providing load carry-through to said forward flange for supporting said inlet cowl to said fan casing; and a fabric containment blanket disposed radially outwardly of said outer wall of said second honeycomb region and being effective for containing blade fragments thrown outwardly upon damage to said blades.

Claim 19

A fan blade containment structure according to claim 15 wherein said septum is spaced a predetermined distance radially outwardly from said inner wall so that said outer honeycomb region is not damaged due to orbiting of said blades upon damage thereof and is thereby effective for retaining blade fragments which puncture said inner wall, septum and outer wall and are contained by said containment blanket.

Claim 20

A fan blade containment structure according to claim 15 wherein said containment blanket comprises a plurality of layers of Kevlar fabric.