Abstract: Acoustic turbofan airfoil apparatus are disclosed. An example apparatus includes a platform of a turbofan engine, the platform including perforations to receive acoustic waves, acoustic chambers protruding from a first side of the platform, the acoustic chambers aligned with the perforations in a radial direction defined by the turbofan engine, the acoustic chambers to attenuate the acoustic waves, and an airfoil protruding from a second side of the platform opposite the first side of the platform.

Abstract: A ducted fan engine is deiced using a ground support deicing apparatus having a support structure, a plurality of sonic wave transmitters, an imaging device, and a controller that controls the sonic wave transmitters to emit sonic waves at varying frequencies. A deicing program causes the controller to control (a) providing imaging signals to obtain image data from imaging sensors, (b) receiving image data provided by each of the imaging sensors, and generates images of at least one component part of the engine, (c) detecting a presence or an absence of ice on the at least one component part of the engine, and (d) controlling the plurality of sonic wave transmitters to emit sonic waves in a given frequency range so as to remove the ice from the component part of the engine.

Abstract: Part-span shrouds for pitch controlled aircrafts are disclosed herein. An example apparatus includes a first portion extending from a first airfoil, the first portion including a first surface, the first surface being convex, a second portion extending from a second airfoil towards the first airfoil, the second portion including a second surface the first airfoil circumferentially adjacent to the second airfoil, the second surface being concave, and an interface formed by the first surface and the second surface, the interface reacting circumferential loads between the first airfoil and the second airfoil.

Abstract: Methods and apparatus to reduce deflection of an airfoil are disclosed. An example apparatus disclosed herein includes a plate including an aperture, the airfoil disposed in the aperture, and a damper operatively coupled between the plate and a hub of the airfoil, the damper to transform flexural deflection of the airfoil to radial deflection of the plate.

Abstract: A fan for a turbine engine having a core air flowpath and a bypass air flowpath. The fan includes a disk, a plurality of fan blades, and a plurality of splitter blades. The disk rotates about a centerline axis. The plurality of fan blades are coupled to the disk. The plurality of splitter blades are coupled to the disk and positioned between the plurality of fan blades. The plurality of splitter blades are axially aligned on the disk at a splitter blade axial distance from an annular inlet of the core air flowpath such that the plurality of splitter blades direct debris that passes through the fan into the bypass air flowpath.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to implement an integrated stator-fan frame assembly. An integrated fan exit stator-fan frame strut assembly for a gas turbine engine includes a fan exit stator portion having an airfoil including a leading edge and a trailing edge, and a fan frame strut portion including a leading edge and a trailing edge, the leading edge of the fan frame strut portion aerodynamically integrated with the trailing edge of the fan exit stator portion.

Abstract: An airfoil structure including an airfoil and a spring and damper system. The airfoil including a longitudinal axis. The spring and damper system is connected to the airfoil to rotate the airfoil about the longitudinal axis to change airfoil pitch in response to a load applied to the airfoil.

Abstract: In one aspect, a device for preventing bird strikes to an engine. The device includes a projector mounted on a component of the engine. The projector is positioned to project an image outside of the engine. In another aspect, an engine for an aircraft. The engine includes an engine component and a projector mounted on the engine component. The projector is positioned to project an image outside of the engine.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to implement a low radius ratio fan blade for a gas turbine engine. A fan blade for a gas turbine engine includes an airfoil including a leading edge and a trailing edge extending between a root and a tip of the airfoil, a distance between the leading edge and the trailing edge defining a flow path length, a leading edge hub point defined by a radially innermost point of the leading edge, and an axial dovetail including a pair of opposed pressure faces, an axial length of the axial dovetail less than the flow path length, a top edge of the axial dovetail separating the pressure faces from the airfoil, the top edge of the axial dovetail radially outward of the leading edge hub point.

Abstract: Methods and apparatus to reduce deflection of an airfoil are disclosed. An example apparatus disclosed herein includes a plate including an aperture, the airfoil disposed in the aperture, and a damper operatively coupled between the plate and a hub of the airfoil, the damper to transform flexural deflection of the airfoil to radial deflection of the plate.

Abstract: Methods, apparatus, systems, and articles of manufacture to provide damping of an airfoil are disclosed. An example airfoil is disposed in a flow path, the airfoil including a shell defining an exterior surface of the airfoil and forming a cavity in an interior surface of the airfoil, and a lattice damper disposed in the cavity, the lattice damper to reduce vibrational loads exerted on the airfoil.

Abstract: Turbofan blade blocking apparatus are disclosed. An example turbofan engine includes a containment casing, a fan, at least one of a trench filler or an abradable layer at least partially aligned with the fan in an axial direction defined by the turbofan engine, at least one of the trench filler or the abradable layer fixed to an inner radial surface of the containment casing, and a metal blocker coupled to the containment casing forward of the fan, an aft end of the metal blocker interfacing with at least one of the trench filler or the abradable layer.

Abstract: Methods and apparatus to reduce deflection of an airfoil are disclosed. An example apparatus disclosed herein includes a plate including an aperture, the airfoil disposed in the aperture, and a damper operatively coupled between the plate and a hub of the airfoil, the damper to transform flexural deflection of the airfoil to radial deflection of the plate.

Abstract: Part-span shrouds for pitch controlled aircrafts are disclosed herein. An example apparatus includes a first portion extending from a first airfoil, the first portion including a first surface, the first surface being convex, a second portion extending from a second airfoil towards the first airfoil, the second portion including a second surface the first airfoil circumferentially adjacent to the second airfoil, the second surface being concave, and an interface formed by the first surface and the second surface, the interface reacting circumferential loads between the first airfoil and the second airfoil.

Abstract: Cantilevered airfoils and methods of forming the same are disclosed herein. An example airfoil disclosed herein includes an airfoil including an airfoil body including a first face and a second face, a first recessed portion formed in the first face and internal temperature-regulating features and a first insert disposed within the first recessed portion, the first insert causing the airfoil body to assume a first predefined curvature profile at a first temperature, the first insert causing the airfoil body to assume a second predefined curvature profile at a second temperature.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed for a variable bleed valve assembly. An example variable bleed valve assembly a variable bleed valve (VBV) door corresponding to a bleed port and a first unison ring, the VBV door coupled to the first unison ring, the first unison ring to move in a circumferential direction between a first position and a second position causing the VBV door to move between the first position and the second position.

Abstract: Methods, apparatus, systems, and articles of manufacture to provide damping of an airfoil are disclosed. An example airfoil is disposed in a flow path, the airfoil including a shell defining an exterior surface of the airfoil and forming a cavity in an interior surface of the airfoil, and a lattice damper disposed in the cavity, the lattice damper to reduce vibrational loads exerted on the airfoil.

Abstract: A blade for an engine includes an airfoil body having a pressure side and a suction side, a base, and a rib located on the pressure side of the airfoil body. The rib includes a radially outer surface inclined radially outwardly with respect to the pressure side of the airfoil body and a scoop formed by the radially outer surface. The radially outer surface is inclined radially outward with respect to a normal axis to the pressure side of the airfoil body. The rib is angled at a positive angle with respect to the platform. An engine for and a method of directing ingestion material in an engine may employ the rib.

Abstract: Methods, apparatus, systems, and articles of manufacture are disclosed to implement an integrated stator-fan frame assembly. An integrated fan exit stator-fan frame strut assembly for a gas turbine engine includes a fan exit stator portion having an airfoil including a leading edge and a trailing edge, and a fan frame strut portion including a leading edge and a trailing edge, the leading edge of the fan frame strut portion aerodynamically integrated with the trailing edge of the fan exit stator portion.

Abstract: Airfoil vibration damping apparatus are disclosed. An example apparatus includes a metallic airfoil including a cavity, and a dilatant material disposed in the cavity to dampen vibrations of the metallic airfoil.