54 results about "Leading-edge extension" patented technology

A method of reducing crack propagation in an airfoil includes: providing an airfoil having a root spaced apart from a tip, spaced-apart leading and trailing edges, a suction side extending from the leading edge to the trailing edge, and an opposed pressure side extending from the leading edge and the trailing edge, supporting the airfoil against bending loads; and burnishing the airfoil using a burnishing element, so as to create at least one burnished section of residual compressive stress, the at least one burnished section being located adjacent the leading edge and spaced from the leading edge by an offset distance selected so as to avoid deformation of the leading edge.

A drill nozzle includes a housing having a bristle brush ring attached. The housing of the drill nozzle may include an air intake, multiple coolant inlets, multiple coolant jets, a vacuum tube, and mounting flanges. The air intake may provide a thrust-vectored down draft into the vacuum tube. The coolant inlets may receive coolant fluid that may be expelled from the coolant jets towards a drill bit. Drilling debris and coolant fluid may be contained inside the bristle brush ring preventing damage and soiling of surrounding structures and areas and may be extracted with the vacuum tube. The drill nozzle may be attached to a drill motor unit of a numerically controlled drill jig, enabling the use of such numerically controlled drill jig for drilling high quality holes effectively into non-flat surfaces, for example, the leading edge extension spar of the F-18 aircraft.

A vertical take-off and landing (VTOL) aircraft comprises (1) a fuselage having a front end, a rear end and two lateral sides, the fuselage defining a substantially horizontal central longitudinal axis of the aircraft; (2) an aircraft tail arranged at the rear end of the fuselage and including a rudder and an elevator on each side of the fuselage with movable surfaces for controlling the aircraft; and (3) a wing on each side of the fuselage having a front edge, a trailing edge and an upper surface extending from the front edge to the trailing edge. According to the invention, means are provided for increasing the speed of an airstream flowing over the upper surface of each wing, and an air deflector is disposed on each side of the fuselage between the trailing edge of each wing and the aircraft tail. These deflectors each have a deflection surface to deflect downward the airstream flowing over the upper surface of the wing to act as a “brake” to the forward motion of the aircraft and to provide additional lift so that the aircraft may hover.

A fairing for streamlining the junction between the horizontal stabilizer and the fuselage or the fin of an aircraft, comprising an upper fairing shell, a lower fairing shell, a leading edge extension, and several fittings to join the upper and lower fairing shells to the horizontal stabilizer. The upper and lower fairing shells are solid laminates of composite material that are designed with a shape, composition, and thickness such that they can be elastically deformed when they are fitted to the horizontal stabilizer, providing a contact force permitting them to lay permanently in contact with the fuselage or fin. A process for manufacturing the fairing shells.

A fan section for a gas turbine engine is provided. The fan section having a fan hub with a slot and a fan blade with an airfoil extending from a root to a tip, the airfoil having a leading edge and the root is received in the slot, wherein a first platform is secured to the fan hub and arranged between adjacent fan blades of the fan section, the first platform having a first platform seal including a platform seal leading edge and a base is secured to a side of the first platform and a first winglet extends from the platform seal leading edge and contacts the airfoil leading edge.

An aircraft comprises a fuselage, a wing (2) attached to the fuselage, a wing tip device (6) attached to a wing end (4) of the wing (2), at least one additional wing-like element (14) having a wing root (22), a wing leading edge (18) and a wing trailing edge (20), and a torque control device having a rotatable interface means. The torque control device is adapted for rotatably supporting the wingroot of the wing-like element on the interface means under creation of a rotational axis (16) extending from the interface means into the wing-like element (14), about which rotational the wing-like element (14) is rotatable. The wing-like element (14) is adapted to induce a rotation around the rotational axis (16) in an air flow. The torque control device is adapted to limit the degree of rotation depending on a torque introduced into the interface means by the wing-like element (14) and the wing root (22) of the at least one wing-like element (14) is coupled with at least one of the wing tipdevice (6), the wing (2) and the fuselage through the torque control device such that the leading edge (18) extends into an airflow surrounding the aircraft.

A sail for a wind-powered craft includes a web which forms a flying shape upon engagement with the wind, flying shape extending from leading to trailing edges. The web includes a combination of wind-impermeable and wind-permeable portions disposed between the leading and trailing edges, with a permeability ratio of wind-permeable area to wind-impermeable area within a range of about 5 to 80 percent.

A tip structure for a turbine blade comprises a tip surface of an airfoil that extends from a leading edge to a trailing edge and from a pressure side to a suction side of the airfoil. A suction side rail protrudes from the tip surface and comprises: a trailing portion extending flush with the suction side of the airfoil from an origination location at or near the trailing edge to an intermediate location on the suction side; and a leading portion extending from the intermediate location across the tip surface so as to create a suction side shelf region between the leading portion of the suction side rail and the suction side of the airfoil. A pressure side rail protrudes from the tip surface and comprises: a trailing segment extending flush with the pressure side of the airfoil from an origination location at or near the trailing edge to a middle location on the pressure side; and a leading segment extending from the middle location across a camber line on the tip surface so as to create a pressure side shelf region between the leading segment of the pressure side rail and the pressure side of the airfoil.

The invention discloses a blended wing body aircraft including a center body having a lower side and an upper side opposed to the lower side. The center body has a central chord extending from a leading edge to a trailing edge of the center body. The lower side has a lowest point located between a first location forward of a pivot point about which the aircraft rotates during take-off and a secondlocation aft of the pivot point. The first location is at a first distance corresponding to about 10% of a length of the central chord forward of the pivot point.