Abstract: A composite airfoil having a non-metallic leading edge protective wrap is provided. In one aspect, the airfoil has a composite core having a pressure sidewall and a suction sidewall each extending between a core leading edge and a core trailing edge. A leading edge protective wrap protects the core leading edge and includes a trailing wrap and a leading wrap. The trailing wrap wraps around the core leading edge and is connected to the composite core. The leading wrap wraps around the core leading edge and is connected to the trailing wrap. The trailing and leading wraps both have leading edges that are spaced from one another. A filler is positioned between the leading edges of the trailing and leading wraps. A protective nose is connected to the leading edge of the leading wrap. The components of the leading edge protective wrap are formed of non-metallic materials.

Abstract: A composite airfoil having a non-metallic leading edge protective wrap is provided. In one aspect, the airfoil has a composite core having a pressure sidewall and a suction sidewall each extending between a core leading edge and a core trailing edge. A leading edge protective wrap protects the core leading edge and includes a trailing wrap and a leading wrap. The trailing wrap wraps around the core leading edge and is connected to the composite core. The leading wrap wraps around the core leading edge and is connected to the trailing wrap. The trailing and leading wraps both have leading edges that are spaced from one another. A filler is positioned between the leading edges of the trailing and leading wraps. A protective nose is connected to the leading edge of the leading wrap. The components of the leading edge protective wrap are formed of non-metallic materials.

Abstract: A turbomachine assembly includes annular stator surrounding rotor circumscribed and rotatable about centerline axis. One or more non-axisymmetric partial arc annular circular stiffeners are disposed around and on stator and may be helical. Non-axisymmetric partial arc annular circular stiffeners may extend about one third to one half of a circumference, be hollow, and located over one or more blade stages of rotor. One or more annular mid-span flanges may be attached to stator and axially positioned within the hollow partial arc annular circular stiffeners. One or more masses or externals may be attached to the stator or to at least one of the one or more annular mid-span flanges between ends of partial arc annular circular stiffeners. Annular stator and rotor may have matching frequencies causing rotating stator waves rotating with rotor. The stator may be fan casing surrounding fan rotor or labyrinth seal land surrounding labyrinth seal teeth.

Abstract: Composite airfoil singlet, includes airfoil extending from base to tip of airfoil, integrally formed with no more than one outer platform at tip and/or no more than one inner platform at base. Parallel composite plies or woven fibers extend through airfoil and through outer and/or inner platforms. Outer and/or inner curved sections extend between outer and/or inner platforms and airfoil respectively. Assembly includes circular row of the composite airfoil singlets depending radially inwardly from and mounted to an outer shroud or casing. Outer and/or inner fasteners may secure outer and inner platforms to outer shroud or casing and an inner shroud respectively and include shanks extending substantially perpendicularly from outer and inner fastening plates though platform holes in outer and inner platforms and through outer and inner holes in outer shroud or casing and inner shroud respectively. Nuts are screwed on threaded ends of shanks.

Abstract: A tooling assembly and method for forming a flange of a composite component is provided. The tooling assembly includes a mold configured to receive a composite material. The composite material may include a plurality of fabric plies impregnated with resin. The fabric plies may be debulked as they are being laid using a plurality of debulking tools, with the radius of each debulking tool growing as additional fabric plies are laid. A gas-permeable bagging material may be placed along the edge of the composite material to restrict resin flow while allowing for outgassing. The tooling assembly may further include a flange shoe tool that is joined with the mold to form the flange of the composite material. The mold and flange shoe tool may define a chamber and venting passageways that allow gases such as volatile compounds to escape while the composite component is being cured.

Abstract: Composite airfoil singlet, includes airfoil extending from base to tip of airfoil, integrally formed with no more than one outer platform at tip and/or no more than one inner platform at base. Parallel composite plies or woven fibers extend through airfoil and through outer and/or inner platforms. Outer and/or inner curved sections extend between outer and/or inner platforms and airfoil respectively. Assembly includes circular row of the composite airfoil singlets depending radially inwardly from and mounted to an outer shroud or casing. Outer and/or inner fasteners may secure outer and inner platforms to outer shroud or casing and an inner shroud respectively and include shanks extending substantially perpendicularly from outer and inner fastening plates though platform holes in outer and inner platforms and through outer and inner holes in outer shroud or casing and inner shroud respectively. Nuts are screwed on threaded ends of shanks.

Abstract: A turbomachine assembly includes annular stator surrounding rotor circumscribed and rotatable about centerline axis. One or more non-axisymmetric partial arc annular circular stiffeners are disposed around and on stator and may be helical. Non-axisymmetric partial arc annular circular stiffeners may extend about one third to one half of a circumference, be hollow, and located over one or more blade stages of rotor. One or more annular mid-span flanges may be attached to stator and axially positioned within the hollow partial arc annular circular stiffeners. One or more masses or externals may be attached to the stator or to at least one of the one or more annular mid-span flanges between ends of partial arc annular circular stiffeners. Annular stator and rotor may have matching frequencies causing rotating stator waves rotating with rotor. The stator may be fan casing surrounding fan rotor or labyrinth seal land surrounding labyrinth seal teeth.