13 results about "Leading-edge extension" patented technology

A reinforced gasket for use in a Rieber joint can include a flexible annular gasket body and a reinforcing / stiffening ring. The flexible annular gasket body can include a leading nose section, a trailing tail section, and a radial tip section. The reinforcing / stiffening ring can include an inner diameter cylindrical wall having a leading edge and a trailing edge, and an annular angled front wall extending from the leading edge of the inner diameter cylindrical wall. The flexible annular gasket body can be molded around and encapsulates the reinforcing / stiffening ring. The leading edge of the inner diameter cylindrical wall can extend into the leading nose section, the annular angled front wall can extend into the radial tip section, and the trailing edge of the inner diameter cylindrical wall can extend into the trailing tail section. Preferably, the reinforced gasket includes stiffening ribs extending between the cylindrical wall and angled front wall.

A propeller blade comprising a de-icing system is described, wherein the propeller blade comprises a blade body 1 comprising a carbon fiber fabric skin, a leading edge 11, a trailing edge 12, a hub end 9 and a tip end 10. The blade body 1 comprises a resistive wire 4 that extends along the leading edge 11 to a conductive glue 6. The resistive wire 11, the conductive glue 6 and the carbon fiber fabric in the skin of the blade body 1 form a conductive path for an electrical current. A propeller comprising a plurality of the propeller blades, a UAV comprising one or more of the propellers are also described.

A system for providing a simple, safe and inexpensive mechanism to provide flight control in an aircraft. In one embodiment, an anti-torque system 20 for a rotary-wing aircraft has an airfoil 22 with a first surface 24 extending from a first trailing edge 28 and a leading edge 30, and a second surface 26 extending from a second trailing edge 32 to join the first surface 24 at the leading edge 30. The airfoil 22 has a first moveable deflector panel 34 pivotally coupled to the first trailing edge 28, and a second moveable deflector panel 36 pivotally coupled to the second trailing edge 32. Means are provided to pivot the deflector panels 34, 36 in unison about their respective pivot axes 35, 37 to alter the direction of travel of the airflow downstream of the pivot axes 35, 37 over the surfaces of the deflector panels 34, 36, thereby producing a lift in a direction perpendicular to the airflow to counteract the torque applied on the aircraft. In another embodiment, the flight control system 10 is arranged within a fixed-wing aircraft.

The present invention relates to an open impeller (7) and a submersible pump configured for pumping a liquid comprising abrasives and including the open impeller (7). The open impeller (7) includes a cover plate (11), a centrally located hub (12), and at least two helical swept blades, each blade including a leading edge (14) adjacent to the hub (12), a trailing edge (15) located at the periphery of the impeller (7), and a lower edge (16), wherein the lower edge (16) extends from the leading edge (14) to the trailing edge (15) and separates the suction side (17) of the blade from the pressure side (18) of the blade, and wherein the lower edge (16) is configured to face and oppose a wear plate of the submersible pump, at least one blade including a winglet (19) at the lower edge (16), wherein the winglet (19) is connected to and protrudes from the suction side (17) of the at least one blade. The impeller (7) is characterized in that the winglet (19) is located radially outside the inner radius of the impeller (7) and extends circumferentially to the trailing edge (15) of the blade at the suction side (17) of the blade at the maximum radius (r_max) of the impeller (7), the winglet (19) having a lower wear surface (20) configured to face and be opposite to the wear plate of the submersible pump, wherein the inner radius is equal to the maximum value of the following: the maximum radius (r_max) of the impeller (7) multiplied by 0.6; and the inlet radius of the impeller (7) multiplied by 1.2, wherein the inlet radius is obtained at the interface between the leading edge (14) of the blade and the lower edge (16) of the blade at the suction side (17) of the blade.

In accordance with one embodiment of the present disclosure, an aircraft assembly is described. The aircraft assembly can include an airfoil structure, which can extend in a chordwise direction from a leading edge to a trailing edge and can include a first component having one or more hinge loops. The first component can have one or more hinge loops that include a first monolithic, integrally formed structure. The airfoil structure can also include a rear component positioned behind the first component in the chordwise direction. The rear component can have an interface member extending within the one or more hinge loops. The rear component, including the interface member, can include a second monolithic, integrally formed structure.

Actuation assembly for a trailing edge flap of an aircraft wing, comprising: a base unit configured to be fixated to a main body of the aircraft wing; an intermediate unit movably connected to the base unit and configured to be hingeably connected to the flap at a leading edge of the flap about a first hinging axis extending along the leading edge of the flap, wherein the movability provides adjustability of the flap between a retracted flap position and an extended flap position; and a second actuator configured to controllably rotate the flap with respect to the intermediate unit about the first hinging axis, the second actuator being configured to be movable along with the intermediate unit with respect to the at least one base unit.

A stator vane is provided and includes an airfoil section. The airfoil section includes a leading edge, a trailing edge opposite the leading edge, a pressure side extending from the leading edge to the trailing edge and a suction side opposite the pressure side and extending from the leading edge to the trailing edge. The pressure and suction sides form a whale-shaped forward portion proximate to the leading edge. The suction side forms a reverse-turning section proximate to the trailing edge.

A mainmast (21) for a sailing boat (1) has a support base (S) and an upright (P), which extends along an axis from the support base (S) and defines an airfoil symmetrical with respect to an ideal median plane (M), with a leading edge (50) and two convex surfaces (21a,21b) that extend from the leading edge (50); the upright (P) can be oriented about its axis with respect to the support base (S), in order to position, in use, the leading edge (50) with respect to an incident air flow; the upright (P) has a lower portion (P1) and an upper portion (P2), which supports two slats (52a,52b), symmetrical to each other with respect to the ideal median plane (M), in positions spaced apart from the convex surfaces (21a,21b), respectively, so as to define respective slots.

An aircraft engine including a core casing extending circumferentially about an axis and defining a core flow passage, a nacelle located radially outward from and around the casing, and a bypass passage defined between the nacelle and the casing. A mixer includes a peripheral wall having a leading edge and a trailing edge, the leading edge attached to the casing. A first mixer portion and a second mixer portion are circumferentially spaced apart and respectively extend away from the leading edge from a first location to a second location. The first and second mixer portions respectively have a first and second stiffness, the first stiffness greater than the second stiffness and greater than a stiffness of an upstream portion of the wall extending from the first mixer portion at the first location toward the leading edge.

The present disclosure may relate to a system (100) for an enhanced airflow industrial axial fan The system (100) may comprise at least two Carbon Fibre Reinforced Plastic (CFRP) blades (102). Each CFRP blade (102) may be configured as a single structure with a varying chord length longitudinally and a camber transversely. The blades (102) may include a leading edge (202) with a defined radius, an extended curved trailing edge (204), a shoulder side (208), a tip side (206), an upper surface (302) with curvature, and a lower surface (304). The upper (302) and lower (304) surfaces may form an aerofoil profile. The shoulder side (208) may have a straight profile. The blades (102) may be hollow and symmetrically arranged on the fan. Each blade (102) may generate a pressure differential between the upper (302) and lower (304) surfaces when powered, potentially enhancing airflow parallel to a hub axis.

An airfoil includes a leading edge, a trailing edge, and a pressure side wall and a suction side wall each extending between the leading edge and the trailing edge. The pressure side wall and the suction side wall define a main body region and a trailing edge region. The main body region extends from the leading edge to the trailing edge region and defines an upstream plenum. The trailing edge region extends from the main body region to the trailing edge. The trailing edge region defines pressure side channels and suction side channels in fluid communication with the upstream plenum and arranged in a trussed structure to reduce stress in the trailing edge region. The pressure side channels are disposed adjacent the pressure side wall, and the suction side channels are disposed adjacent the suction side wall.

The invention relates to an aerodynamic airfoil for an aircraft, which has a first outer flow surface and an opposing second outer flow surface, which are arranged on a supporting structure of the airfoil and extend from a leading edge of the airfoil to a trailing edge of the airfoil, so that the airfoil is given an aerodynamic profile shape in cross-section, wherein the airfoil has a main section to which a flap section is attached, wherein the flap section is pivotably arranged on the main section by means of a pivoting device, and both the main cross-section of the main section and the flap cross-section of the flap section have a fixed shape, wherein in a transition section between the main section and the flap section the first outer flow surface is flexible, characterized in thatthat the pivoting device has at least one linear actuator which is rotatably arranged with a first attachment point on the main section-side support structure of the main section and with an opposing second attachment point on the flap section-side support structure of the flap section, such that when the linear actuator is actuated, a change in length is effected between the first and the second attachment point, wherein the linear actuator is operatively connected to a cam mechanism in such a way that the second attachment point on the flap section-side support structure follows a trajectory defined by the cam mechanism when actuated.

An aircraft propulsion system includes a bladed rotor configured for rotation about a rotational axis. A rotor blade of the bladed rotor of rotor blades includes a blade body. The blade body has a blade span extending between and to a base end and a tip end. The blade body has a blade chord extending between and to a leading edge and a trailing edge. The blade body forms a pressure side surface and a suction side surface. The blade body forms a recess at the pressure side surface. The recess includes a recess surface portion forming a portion of the pressure side surface. The recess surface portion has a recess height. The recess height is greater than or equal to a Y-value of 0.025 for a normalized two-dimensional curve of a surface profile of the recess surface portion taken along a Y-Z plane orthogonal to the rotational axis for a recess span.