Abstract: An airfoil material loss control structure is provided. This structure includes at least one fuse zone that, during impact from a foreign object, fail before the surrounding structure. In a further aspect, a rotary machine is provided. This rotary machine includes a ducted fan gas turbine engine including a composite airfoil with at least one fuse zone.

Abstract: A blade for a propulsion apparatus. The blade includes a body having opposed pressure and suction sides. The blade extends in span between a root and a tip and the blade extends in chord between a leading edge and a trailing edge. The blade includes a fracture structure that is defined within the body and positioned such that it is spaced-away from the tip. The fracture structure includes at least one chamber. A first fracture wall is disposed between the at least one chamber and the pressure side, and a second fracture wall is disposed between the at least one chamber and the suction side. The fracture structure is configured to fail when a predetermined force is applied to the tip such that the tip separates from the remainder of the body.

Abstract: A blade for a propulsion apparatus that includes a body formed of a first material having opposed pressure and suction sides, and extending in span between a root and a boundary, and extending in chord between a leading edge and a trailing edge. A tip region that is formed of a second material and that is positioned such that it extends from the body and defines a tip. The tip region joins the body at the boundary. The tip region is configured to fail when a predetermined force is applied to the tip such that the tip separates from the blade and defines a fused tip.

Abstract: A propulsion system including a casing surrounding a fan rotor assembly is provided. The casing includes an outer layer material defining a first coefficient of thermal expansion (CTE) and an inner layer material. The casing further includes a spring member disposed between the outer layer material and the inner layer material coupling the outer layer material and the inner layer material. The spring member is coupled to each of the outer layer material and the inner layer material within a flow passage defined between the outer layer material and the inner layer material. The spring member defines a second CTE greater than the first CTE.

Abstract: A gas turbine engine composite article having a composite article airfoil extending outwardly to an article root to an article airfoil tip. Within the article airfoil is a core including a core airfoil attached to a core root including a core dovetail. A continuous outer three-dimensional braided layer including braided composite material tows are braided on the core and the braided layer covers the entire core airfoil and the core root. The core may be an inflatable mandrel or a composite core made of a composite material. The core may include stiffeners such as an I beam or hollow rectangular cross-section box beams. A method for making such an article includes braiding a continuous outer three-dimensional braided layer including braided composite material tows on the core including covering the entire core airfoil and the core root with the continuous outer three-dimensional braided layer.

Abstract: Fan blade platform includes axially extending I beam supporting radially outer skin having flowpath surface. I beam includes upper and lower or radially outer and inner I flanges on radially outer and inner beam ends of axially extending I web. Radially outer skin on top of and bonded or otherwise attached to radially outer I flange. I beam may be integral and monolithic and made from a non-metallic composite or thermoplastic material and have post cure formed weight relief holes. I beam may include oppositely facing or back to back first and second C beams. First C beam including axially extending first C web disposed between radially outer and inner first C flanges. Second C beam including axially extending second C web disposed between upper and lower or radially outer and inner second C flanges. I beam may be asymmetrical about center plane of I web.

Abstract: A containment structure configured to provide close tolerance for a rotation structure. The containment structure includes an annular inner casing having an inner annular surface being formed of an abradable material. The rotation structure is configured to be received within the annular inner casing such that the rotation structure is normally spaced-apart from the inner annular surface. The inner annular surface surrounds the rotation structure and has a first width. The rotation structure has a second width and the first width is greater than the second width. At least a section of the inner annular surface of the abradable material is cylindrical.

Abstract: A turbine engine airfoil apparatus, including an airfoil defined by a plurality of airfoil sections arrayed along a stacking axis that extends between a root and a tip, wherein at least two of the airfoil sections spaced apart from each other have differing airfoil section thermal expansion properties.

Abstract: An airfoil assembly including a composite body having a mounting edge and a trailing edge which is secured to a leading edge element defining a 3-D leading edge geometry with both chord and camber variation.

Abstract: A blade containment structure surrounding a fan in a turbofan engine is disclosed. The blade containment structure includes a cellular material to absorb energy and contain fragments of a blade thrown outward; an inner shell; a ductile back sheet spaced radially outward from the inner shell, the ductile back sheet and inner shell cooperating to define a nesting area for the cellular material, wherein the cellular material is bound at its radially inner surface by the inner shell and at its outer surface by the ductile back sheet; and a containment blanket overlaid on the ductile back sheet, the containment blanket being of the type effective to contain fragments of the blade that penetrate through the ductile back sheet.

Abstract: A composite airfoil comprises a leading edge and a trailing edge, a pressure side and a suction side extending between the leading edge and the trailing edge, a tip at a radial outer end of the airfoil, a shank at a radial inner end of the airfoil, a dovetail connected to the shank, and a metal patch disposed between the dovetail and the shank.

Abstract: An aircraft can include an anti-icing system. The anti-icing system can include an array of carbon nanotubes thermally coupled to at least a first exposed surface of the aircraft. The anti-icing system can also include an array of solar cells carried by the aircraft and electrically coupled to the array of carbon nanotubes.

Abstract: An aircraft can include a turbine engine including a rotor and a stator, and also including a compressor, a combustor, and a turbine in axial flow arrangement. The aircraft can further include an anti-icing system with a magnetic field generator having a rotating portion and a non-rotating portion, as well as an array of carbon nanotubes thermally coupled to an exposed surface.

Abstract: A system for actuating components of a gas turbine engine may generally include a turbine component incorporating a jamming device. The jamming device may include a bladder and a jammable media contained within the bladder. The jammable media may be jammable within the bladder from an unjammed state, wherein a fluid is contained within the bladder, to a jammed state, wherein the fluid is at least partially evacuated from the bladder. The system may also include a fluid coupling in fluid communication with the bladder. A portion of the turbine component may be located at a first position when the jammable media is in the unjammed state. Additionally, such portion of the turbine component may be located at a second position when the jammable media is in the jammed state.

Abstract: Fan blade includes airfoil with leading and trailing edges, pressure and suction sides extending outwardly from airfoil base to airfoil tip, and tip cladding with non-symmetric pressure and suction side cladding flanks bonded to airfoil tip along pressure and suction sides respectively. Pressure and suction side cladding flanks may include non-symmetric or different pressure and suction side cladding radial heights and/or different pressure and suction side cladding radial locations of pressure and suction side cladding flank portions of pressure and suction side cladding flanks in tip cladding portion of tip cladding. One cladding radial heights may be variable in tip cladding portion. Chordwise extending seam may be in pressure side cladding flank portion and/or chordwise extending slot may be in suction side cladding flank portion. Cladding flanks may be stronger, more ductile, or less brittle than composite material of composite core of airfoil.

Abstract: A propeller assembly that includes a hub having an outer radial surface and a plurality of wedge retaining members removably coupled to the hub. The plurality of wedge retaining members are spaced circumferentially about the outer radial surface such that a dovetail slot is defined between adjacent wedge retaining members. The assembly also includes at least one propeller blade including a root portion having a dovetail profile. The root portion is coupled to the hub and positioned within the dovetail slot. The plurality of wedge retaining members are configured to restrict radial movement of the root portion within the dovetail slot.

Abstract: An airfoil for an aircraft engine is provided. The airfoil may include a plurality of composite plies extending in a chordwise direction from a leading edge to a trailing edge and in a spanwise direction between an airfoil tip and an airfoil base. The airfoil may include at least one discontinuous ply having a first ply segment, a second ply segment, and a butt joint disposed between the first ply segment and the second ply segment. The butt joint may be disposed along a first fragment profile to frangibly attach the first and second ply segments.

Abstract: A backsheet for use in a turbine engine fan case includes a first portion including a first portion first end and an opposing first portion second end. The first portion is tapered between the first portion first end and the first portion second end. The backsheet also includes a second portion coupled to the first portion. The second portion includes a second portion first end and an opposing second portion second end. The second portion defines a constant thickness between the second portion first end and the second portion second end.

Abstract: A containment structure comprising an annular structure configured to provide close tolerance to a rotation structure. The containment structure includes a first abradable structure, a second abradable structure, and a shroud that is defined in part by the first abradable structure and in part by the second abradable structure. An annular surface of the shroud is defined by the first abradable structure and by the second abradable structure. The first abradable structure is harder than the second abradable structure.

Abstract: According to present embodiments or aspects thereof, a composite booster spool with separable composite blades is provided. The blades are inserted radially from within the inner circumference of the spool and extend outwardly through the spool. The system provides a reduced weight assembly as compared to prior art metallic or composite/metallic combination systems. Additionally, the blades are separable which results in a more field-serviceable assembly over a fully integral system wherein the blades and spool are integrally formed from composites or combination of metal and composites.