756 results about "Leading-edge slats" patented technology

An air bearing surface for read / write head of a magnetic disk drive is disclosed. The air bearing surface includes a trailing edge pad and a leading edge pad with trailing portions. A cavity is defined between the trailing edge pad and the trailing portions of the leading edge pad. A cavity patch is disposed within the cavity. The cavity patch can be disposed within the cavity towards one side of the read / write head.

A stent delivery catheter includes at least an inner and outer body, and a specially shaped balloon affixed near one end of both of the inner and outer bodies. At least the outer body is tubular, and the space between the outer and inner bodies defines an inflation lumen for inflating and deflating the balloon. The balloon is designed to surround and hold a compressed self-expanding stent in a small initial size. An inner portion of the cylindrical balloon extends from where it is affixed to the inner body of the catheter shaft at a point proximal to the stent to a distal leading edge at a point distal to the stent. At this leading edge, the balloon is folded back upon itself, and an outer portion of the balloon extends proximally from the leading edge to a point proximal of the stent where it is affixed to the outer body of the catheter shaft. When the outer body is retracted in the proximal direction, the balloon progressively peels back or everts, to progressively release the stent. This peeling action minimizes any friction that may exist between the stent and balloon during stent deployment. The leading distal folded edge of the balloon, both inner and outer portions, are tapered inward. This inner and outer tapering of the balloon portions tends to protect the leading edge of the stent, provides for easier advancement of the catheter system along the desired body passageway for treatment, and minimizes friction as the balloon is retracted or peeled back upon itself.

A hub-side leading edge part of a fan first-stage rotating blade 10 for taking an air thereinto more extends in a forward direction of an engine than a tip-side leading edge part and a mid-span leading edge part. The hub side of the fan first-stage rotating blade 10 is integrally connected as one with the tip side and the mid span while having a longer chord length than those of the tip side and the mid span. A radius at a root of the hub-side leading edge part is set in a boss ratio of 0 to 0.4.

A turbine blade outer air seal assembly includes a hot side exposed to a combustion hot gas flow, and a back side that is exposed to a supply of cooling air. The outer air seal segment includes a trailing edge cavity and a leading edge cavity separated by a divider. The cavities are feed cooling air through a plurality of inlet openings disposed transverse to the gas flow. The cooling air enters the cavities and flows toward a plurality of outlets at the leading edge and a plurality of outlets along the trailing edge. A plurality of pedestals within each of the cavities disrupts cooling air flow to increase heat absorption capacity and to increase the surface area capable of transferring heat from the hot side.

A swirler including an annular housing with limiting walls. At least two vanes are arranged in the annular housing including the sidewalls of the swirler. The leading edge area of each vane has a profile, which is oriented parallel to a main flow direction prevailing at the leading edge position, wherein the profiles of the vanes turn from the main flow direction prevailing at the leading edge position to impose a swirl on the flow, and wherein, with reference to a central plane of the vanes the trailing edges are provided with at least two lobes in opposite transverse directions. A burner for a combustion chamber of a gas turbine including such a swirler and at least one nozzle having its outlet orifice at or in a trailing edge of the vane and to a method of operation of such a burner.

A mechanism for extending and supporting a high-lift device relative to an airfoil has a pair of support ribs coupled to the airfoil. A carrier track is pivotally coupled to the high-lift device and positioned between the pair of support ribs. The carrier track has a slot opening along a lower length thereof. A gear rack is coupled within the slot opening. A pinion gear is positioned between the support ribs and below the carrier track. The pinion gear engages with the gear rack for extending the high-lift device relative to the airfoil. A plurality of rollers is rotateably coupled to the support ribs and in bearing contact with the carrier track. At least one roller is positioned above the carrier track and a second roller is positioned below the carrier track. The second roller is positioned concentrically with the pinion gear.

An airfoil part includes a plurality of cooling chambers that are spaces into which the inside of the airfoil part is partitioned, from a leading edge side to a trailing edge side, by a partition wall, that extend in a vane-longitudinal-section direction, and that include division parts on inner walls of a body; insert cylinders that are disposed in the cooling chambers and that have a plurality of impingement holes; and film holes that are provided in the body. The insert cylinders include partitioning parts that extend from the leading edge side to the trailing edge side and that extend in the vane-longitudinal-section direction. The insides of the insert cylinders are partitioned into pressure-surface-side insert spaces close to a pressure surface and suction-surface-side insert spaces close to a suction surface.

A blade outer air seal system includes a body that extends between two circumferential sides, a leading edge and a trailing edge, and a radially inner side and a radially outer side. An attachment section associated with the body and includes at least one engagement surface that is transverse to the radially outer side.

An airflow guide stator vane for an axial flow fan and a shrouded axial flow fan assembly having such stator vanes are disclosed. The airflow guide stator vane has a leading edge line, a trailing edge line, and an airflow guide surface extending from the leading edge line to the trailing edge line. The stator vane is radially positioned in an axial flow fan and is curved so that its leading edge line is perpendicular to oblique velocity components of an airflow each of which is a sum vector of a rotation-directional velocity component and a radius-directional component of an air particle of the airflow. The axial flow fan assembly comprises an axial flow fan and a shroud. The axial flow fan consists of a circular central hub connected with a driving shaft of a motor and a plurality of blades radially arranged along the circumference of the hub. The shroud consists of a housing surrounding the peripheral ends of said axial flow fan and forming an airflow passage, a motor support being positioned at its center portion and holding a motor for driving said axial flow fan, and the above-described stator vanes.

A rotor blade assembly for a wind turbine is disclosed. The rotor blade assembly includes a rotor blade having surfaces defining a pressure side, a suction side, a leading edge, and a trailing edge extending between a tip and a root. The rotor blade assembly further includes an erosion protection coating configured on a surface of the rotor blade. The erosion protection coating includes a ceramic layer, the ceramic layer having a thickness of less than approximately 10 millimeters. The ceramic layer is configured to reduce erosion of the rotor blade.

An ultrasonic transmitter generates a reference signal based on a clock signal of a specific frequency and a control signal made up of binary values 0 and 1 for controlling how the level (High or Low) of a carrier drive signal should change, and generates an analog signal constituting the carrier drive signal by pulse-duration-modulating the reference signal. Produced from the carrier drive signal, a driving pulse signal is shaped into a curved waveform having a gradually rising leading edge and a gradually falling trailing edge as the amplitude of the carrier drive signal is gradually increased and decreased based on the control signal.

The invention relates to a turbomachine blade comprising an aerodynamic surface made of a composite material and extending in a first direction between a leading edge and a trailing edge, and in a second direction between a root and a tip of the blade. The blade includes solid metal reinforcement that is adhesively bonded to the leading edge of its aerodynamic surface, which reinforcement extends along the first direction beyond the leading edge of the aerodynamic surface and along the second direction between the root and the tip, and includes at least one recess for absorbing at least a portion of the energy that results from an impact of a foreign body against the leading edge of the blade.

A cutting platform for use with an agricultural harvesting machine includes at least one platform section. Each platform section has a cutterbar assembly movable in a localized manner in upwards and downwards directions, an endless belt with a leading edge, and a plurality of skid shoes. Each skid shoe extends rearwardly from the cutterbar assembly and has an upper surface defining a belt support for the leading edge of the endless belt.

An air-cooled turbine blade is provided having an airfoil shape defined by a convex suction side wall, a concave pressure side wall, a leading edge, a trailing edge, a root and a tip, the walls and the tip each including an interior surface that defines an interior with the root, the trailing edge including a plurality of slots formed thereon. The blade includes a suction side flow circuit formed therein comprising a forward and an aft flow circuit. The blade also includes a tip flow circuit extending along the tip interior surface to at least one of the trailing edge slots and including a first and a second opening, the first opening in flow communication with the suction side forward flow circuit outlet, and the second opening in flow communication with a cross-over hole of the suction side aft flow circuit. Methods of manufacturing the blade are also provided.

A turbine blade outer air seal assembly includes a hot side exposed to a combustion hot gas flow, and a back side that is exposed to a supply of cooling air. The outer air seal segment includes a trailing edge cavity and a leading edge cavity separated by a divider. The cavities are feed cooling air through a plurality of inlet openings disposed transverse to the gas flow. The cooling air enters the cavities and flows toward a plurality of outlets at the leading edge and a plurality of outlets along the trailing edge. A plurality of pedestals within each of the cavities disrupts cooling air flow to increase heat absorption capacity and to increase the surface area capable of transferring heat from the hot side.

The invention relates to an optimised wind turbine blade including: a first component (7) having an aerodynamic profile with a leading edge (11), a blunt trailing edge (13) with a thickness T greater than 2 mm and suction and pressure sides (17, 19) between the leading edge (11) and the blunt trailing edge (13); and a second component (9, 12) for reducing the noise from the blunt trailing edge, having a constant cross-section along the radius of the blade, which is securely joined to the blunt trailing edge (13) of the first component (7) in at least part of the wind turbine blade using coupling means that enable same to be replaced.