A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during o
A fan case for use in a gas turbine engine of an aircraft includes an outer shroud and a liner extending along the outer shroud. The fan case provides a protective band that blocks fan blades from being thrown out of the fan case in case of a blade-off event in which a fan blade is released during operation of the gas turbine engine.
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1. A fan case that extends around fan blades of a fan rotor included in a gas turbine engine, the fan case comprising an annular outer shroud arranged to extend around a central axis of the fan case such that the annular outer shroud extends around the fan blades of the fan rotor, the annular outer
1. A fan case that extends around fan blades of a fan rotor included in a gas turbine engine, the fan case comprising an annular outer shroud arranged to extend around a central axis of the fan case such that the annular outer shroud extends around the fan blades of the fan rotor, the annular outer shroud having an outer surface facing away from the central axis and an inner surface facing toward the central axis,a first liner segment coupled to the inner surface of the annular outer shroud, the first liner segment including an inner radial surface, an outer radial surface spaced apart radially from the inner radial surface of the first liner segment, and a head surface extending between and interconnecting the inner and outer radial surfaces, wherein the head surface intersects a first ray extending from the central axis to the annular outer shroud, anda second liner segment coupled to the inner surface of the annular outer shroud, the second liner segment including an inner radial surface, an outer radial surface spaced apart radially from the inner radial surface of the second liner segment, and a tail surface extending between and interconnecting the inner and outer radial surfaces, wherein the tail surface intersects the first ray and the head surface and the tail surface are aligned such that the head surface overlaps the tail surface when viewed radially inwardly along the first ray toward the central axis. 2. The fan case of claim 1, wherein the head surface is curved. 3. The fan case of claim 1, wherein the head surface is linear and an acute angle α is defined between the head surface and the first ray and the acute angle α is between 10 degrees and 30 degrees. 4. The fan case of claim 3, wherein the acute angle α is 20 degrees. 5. The fan case of claim 1, wherein the head surface includes a first sub-surface extending from the inner radial surface toward the outer radial surface and a second sub-surface extending from the outer radial surface toward the inner radial surface and connected to the first sub-surface. 6. The fan case of claim 5, wherein the first sub-surface is linear and an acute angle α is defined between the first sub-surface and the first ray and the acute angle α is between 10 degrees and 30 degrees. 7. The fan case of claim 6, wherein the acute angle α is 20 degrees. 8. The fan case of claim 6, wherein the second sub-surface included in the head surface is linear and an acute angle β is defined between the second sub-surface included in the head surface and the first ray, and the acute angle β is between 10 degrees and 30 degrees. 9. The fan case of claim 8, wherein the acute angle β is different than the acute angle α. 10. The fan case of claim 1, wherein the first liner segment includes an abradable inner radial layer that defines the inner radial surface, an outer radial layer that defines the outer radial surface, and a liner-filler body located radially between the inner radial layer and the outer radial layer of the first liner segment. 11. The fan case of claim 10, wherein the liner-filler body is honeycomb shaped. 12. A fan case that extends around fan blades of a fan rotor included in a gas turbine engine, the fan case comprising an annular outer shroud arranged to extend around a central axis of the fan case such that the annular outer shroud extends around the fan blades of the fan rotor, the annular outer shroud having an outer surface facing away from the central axis and an inner surface facing toward the central axis,a first liner segment having an outer radial surface coupled to the inner surface of the annular outer shroud and an inner radial surface radially spaced apart from the outer radial surface, the inner radial surface positioned at a first radius from the central axis, the first liner segment including a body, a head coupled to the body and extending toward a second liner segment, and a tail coupled to the body and extending away from the body, anda second liner segment having an outer radial surface coupled to the inner surface of the annular outer shroud and an inner radial surface radially spaced apart from the outer radial surface, the inner radial surface positioned at a first radius from the central axis, the second liner segment including a body, a tail coupled to the body and extending toward the first liner segment, and a head coupled to the body and extending away from the first liner segment,wherein the head of the first liner segment includes a head surface that intersects a first ray extending from the central axis to the annular outer shroud and the tail of the second liner segment includes a tail surface that intersects the first ray,wherein movement of the first liner segment in a radially outward direction causes the head of the first liner segment to engage the tail of the second liner segment and to move therewith to cause the inner surface of the first liner segment to be positioned at a second radius from the central axis and the inner surface of the second liner segment to be positioned at the second radius from the central axis. 13. The fan case of claim 12, wherein a first acute angle α is defined between the head surface and the first ray and the first acute angle α0 is between 10 degrees and 30 degrees. 14. The fan case of claim 13, wherein the first acute angle α is 20 degrees. 15. The fan case of claim 14, wherein a second acute angle θ is defined between the tail surface and the second ray and the second acute angle θ is between 10 degrees and 30 degrees. 16. The fan case of claim 15, wherein the second acute angle θ is 20 degrees. 17. The fan case of claim 12, wherein the first liner segment includes an abradable inner radial layer that defines the inner radial surface, an outer radial layer that defines the outer radial surface, and a liner-filler body located radially between the inner radial layer and the outer radial layer of the first liner segment. 18. A method of removing a liner segment from a fan case included in a gas turbine engine mounted to an aircraft, the method comprising the steps of providing a gas turbine engine mounted to an aircraft, the gas turbine engine including a plurality of fan blades and a fan case that extends circumferentially around a central axis and the plurality of fan blades and the fan case including an annular outer shroud, a first liner segment coupled to the annular outer shroud to lie between the annular outer shroud and the central axis, and a second liner segment coupled to the annular outer shroud to lie between the annular outer shroud and the central axis, wherein the first liner segment includes an inner radial surface, an outer radial surface spaced apart radially from the inner radial surface of the first liner segment, and a head surface extending between and interconnecting the inner and outer radial surfaces, wherein the head surface intersects a first ray extending from the central axis to the annular outer shroud, the second liner segment includes an inner radial surface, an outer radial surface spaced apart radially from the inner radial surface of the second liner segment, and a tail surface extending between and interconnecting the inner and outer radial surfaces, the tail surface intersects the first ray, and the head surface and the tail surface are aligned such that the head surface overlaps the tail surface when viewed radially inwardly along the first ray toward the central axis,uncoupling the first liner segment from the annular outer shroud, andmoving the first liner segment radially inward along a path toward the central axis without moving the first liner segment axially relative to the central axis. 19. The method of claim 18, wherein the path is curved. 20. The method of claim 18, wherein the fan blades rotate in a direction of travel from the tail to the head of the first liner segment.
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