A turbofan engine is provided. The turbofan engine includes a fan having a plurality of fan blades; a turbomachine operably coupled to the fan for driving the fan, the turbomachine having a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath; a nacelle surrounding and at least partially enclosing the fan, the nacelle defining a radius and a longitudinal axis; and an inlet pre-swirl vane located upstream of the plurality of fan blades and defining a chord, the inlet pre-swirl vane coupled to the nacelle, wherein the inlet pre-swirl vane is angled at a first angle with respect to the radius of the nacelle, and wherein the chord of the inlet pre-swirl vane is angled at a second angle with respect to the longitudinal axis of the nacelle.

A system 100 for increasing the efficiency of an axial ducted fan 105 includes, a duct 110 for enclosing the axial ducted fan 105, wherein the axial ducted fan 105 is operationally mounted inside the duct 110. In use, the system 100 further includes, a shaft 115 operably connected to the axial ducted fan 105 for facilitating rotation of the axial ducted fan 105 inside the duct 110; and, a static fan 120 operably positioned parallel to the axial ducted fan 105. In use, the static fan 120 includes same number of blades as the axial ducted fan 105. The system 100 further includes a propulsion efficiency improvement mechanism 125 operably positioned inside the duct 110 for controlling, (a) a position of the static fan 120, and, (b) speed of rotation of the axial ducted fan 105.

A turbofan engine includes a fan having a plurality of fan blades, a turbomachine operably coupled to the fan for driving the fan, the turbomachine including a compressor section, a combustion section, and a turbine section in serial flow order and together defining a core air flowpath, a nacelle surrounding and at least partially enclosing the fan, the nacelle including an inlet at a leading edge of the nacelle, the inlet defining an interior inlet surface that is non-annular, and an inlet pre-swirl feature located upstream of the plurality of fan blades, the inlet pre-swirl feature attached to or integrated into the nacelle.

A pre-swirler unit can include: a shroud including a bottom surface and a top surface opposite to the bottom surface; a blade disposed on the top surface and including a leading edge and a trailing edge, wherein the blade comprises a concave side surface and a convex side surface that are disposed between the leading edge and the trailing edge, wherein the convex side surface comprises a first plurality of dimples, and wherein the concave side surface comprises a second plurality of dimples.

Methods, compositions, and kits for adhering polymers and other materials to another material, and in particular to bone or bone-like structures or surfaces. A composition of matter includes a urethane dimethacrylate-methyl methacrylate copolymer with a plurality of first polymer regions based on urethane dimethacrylate and a plurality of second polymer regions based on methyl methacrylate. The method includes placing an orthopedic joint implant having an attachment surface in a joint space, applying a first non-urethane-containing precursor, a second urethane-containing precursor, and a initiator to the attachment surface; contacting the first and second precursors and the initiator with the joint surface; and copolymerizing the first and second precursors and forming an adhesive copolymer and attaching the implant to the joint.

A diffuser and deswirl flow structure includes a plurality of tube structures with an outer wall that is hollow and elongate and that extends between a first portion and a second portion. The plurality of tube structures is disposed in an annular arrangement about the longitudinal axis. The flow structure also includes a plurality of flow passages extending through the tube structures. The plurality of flow passages extend from the first portion to the second portion, respectively. The plurality of flow passages respectfully include a diffuser portion, which is proximate the first portion and configured to diffuse a fluid flow from a compressor wheel. The plurality of flow passages respectfully include a deswirl portion, which is proximate the second portion and configured to deswirl the fluid flow from the diffuser portion. The outer wall defines the diffuser portion and the deswirl portion. The outer wall is self-supporting.

A tangential on-board injector (TOBI), comprising: a body defining an annular passageway to receive cooling air, the TOBI defining a plurality of discharge nozzles; a rotating component mounted for rotation relative to the body about an axis of rotation; a seal extending between the body and the rotating component; a plurality of vanes circumferentially distributed about the axis of rotation and located downstream of the plurality of discharge nozzles relative to a flow of the cooling air circulating toward the seal from the plurality of discharge nozzles and upstream of the seal; and flow passages defined between the plurality of vanes, a flow passage of the flow passages extending along a passage axis, the passage axis having a tangential component at an outlet of the flow passage that is different than a tangential component of an exit flow axis of a nozzle of the plurality of discharge nozzles.

A gas turbine engine having a pre-swirler adjustability is presented. The pre-swirler includes a pre-swirler insert installed in a component enclosed by a cover. The component includes an inner compressor exit diffusor enclosed by an outer casing or a shaft cover enclosed by the inner compressor exit diffusor. The pre-swirler is adjustable by replacing the pre-swirler insert. An access port including an access window is arranged on the cover. The access port gives access to the pre-swirler insert for replacement through the access window. The access window includes a manhole or combustor assembly installation hole on the outer casing, or a cutout on the inner compressor exit diffusor. The access port allows adjusting the pre-swirler by replacing the pre-swirler insert installed in the component without lifting the cover enclosing the component.

The gas turbine engine includes a casing assembly located proximate a turbine section of the gas turbine engine, and a tangential on-board injector (TOBI) having a body defining a plurality of air passages extending in a radial direction, the plurality of air passages circumferentially distributed and directing cooling air toward a turbine rotor of the turbine section of the gas turbine engine. An interference fit is provided between a face of the body and a face of a member of the casing assembly, the interference fit defining a fastener-free engagement between the bearing housing and the TOBI to prevent relative movement between the member of the casing and the TOBI.

Accelerators, methods of manufacturing accelerators, and gas turbine engines are provided. For example, an accelerator for a gas turbine engine defines a radial direction and an axial direction and comprises an annular outer wall, an annular inner wall, an annular channel defined between the outer and inner walls, and a plurality of vanes disposed within the channel. The channel has an inlet for ingress of a cooling fluid and an outlet for egress of the cooling fluid. Each vane extends from the outer wall to the inner wall adjacent the outlet, which is angled such that an exit angle of the cooling fluid is nonzero with respect to both the radial and axial directions. The accelerator may be manufactured using an additive manufacturing method. The accelerator outlet may be disposed immediately upstream of a first turbine rotor blade stage of a gas turbine engine to direct the cooling fluid thereto.