608 results about "Variable geometry" patented technology

An acetabular shell liner having a variable rim surface geometry, which improves range of motion of the femoral component within the liner and decreases the incidence of dislocation and subluxation, and methods of making and using the acetabular shell liner. Prosthetic devices, more particularly hip joint prostheses, containing the acetabular shell liner having a variable rim surface geometry are also provided.

There is provided an acetabular shell liner, and particularly a constrained liner, having a variable rim surface geometry to improve the range of motion of a femoral component within the liner and decrease the incidence of dislocation and subluxation. There are also provided methods of making and using the acetabular shell liner. Prosthetic devices, and particularly hip joint prostheses, containing the acetabular shell liner having a variable rim surface geometry are also provided.

A variable geometry inlet guide vane for a gas turbine aircraft engine includes an aerodynamic shell for turning inlet flow to a turbine or compressor and an internal spar spaced from the airfoil shell by an air gap. A number of actuation mechanisms grounded to the spar and connected to the inner surface of the aerodynamic shell adjust the shape of the shell in response to varying operating conditions of the engine, imbalanced aerodynamic loading of the shell or vibration or other transient loads on the shell.

An implantable osmotically driven delivery system having a dynamic, two-way valve and a self-adjusting, variable geometry fluid flow channel. As pressure within the agent delivery system increases, the fluid channel narrows, thereby restricting flow. At exceptionally high pressures, the valve can be designed to close altogether at the orifice or delivery end, or it can provide a minimal leak path so that a maximum fluid flow is never exceeded. At zero or very low pressures, the valve will close completely at the beneficial agent reservoir end, isolating the beneficial agent formulation from external fluid infiltration and thereby eliminating diffusion of external fluid into the beneficial agent formulation.

A turbofan engine includes a variable geometry fan exit guide vane (FEGV) system having a multiple of circumferentially spaced radially extending fan exit guide vanes. Rotation of the fan exit guide vanes between a nominal position and a rotated position selectively changes a fan bypass flow path to permit efficient operation at various flight conditions.

An improved surgical retractor stay system has a variable geometry retractor frame and disposable retractor stay clips. The retractor stay clips are adapted to snap onto the variable geometry retractor frame and are slidably movable thereon. The retractor frames are custom made having variable geometry and are prepared from extruded metals. The surgical retractor stay system uses the snap-on retractor stay clips in conjunction with the variable geometry retractor frame.

Systems and methods for providing variable geometry winglets to an aircraft are disclosed. In one embodiment, a winglet includes a base portion configured to attach to a wing. The winglet further includes a body portion. In turn, the body portion includes at least one of a deflectable control surface, a shape memory alloy (SMA) bending plate, and a SMA torque tube. The base portion is configured to attach to the wing such that the body portion projects at an upward angle from the wing.

Multi-stage turbocharging, and more particularly, an advanced multi-stage turbocharging system using the variable turbine power of one or more variable turbine geometry (VTG) turbochargers to adjust compressor boost and exhaust back pressure to engine operating demands. The invention further relates to a turbocharged internal combustion engine, in particular a turbocharged internal combustion engine with at least one high-pressure turbine stage and one downstream low-pressure turbine stage, wherein the high-pressure turbine may be a single-flow or double-flow type, wherein the high pressure or low pressure compressor may be variable geometry, wherein the high pressure or low pressure compressor may be variably bypassed, and wherein the high pressure or low pressure turbine may be provided with an active control variable bypass or wastegate.

The invention provides a medical image synthesis method based on double generative adversarial networks. The method comprises the main content of performing data management, generating the generativeadversarial networks, training a U-NET, establishing assessment indexes and obtaining processed pictures, wherein first, a DRIVE database is used to manage a first-stage GAN, then the first-stage GANgenerates a partitioning mask representing variable geometry of a dataset, a second-stage GAN converts the mask produced at the first stage into an image with a sense of reality, an generator minimizes a loss function of the true data in classification through a descriminator, then the U-NET is trained to assess the reliability of synthetic data, and finally the assessment indexes are establishedto measure a generated model. According to the method, by use of a pair of generative adversarial networks to create a new image generation path, the problem that the synthetic image contains a fake shadow and noise is solved, the stability and the sense of reality of the image are improved, and meanwhile image details are clearer.

The invention consists of a specific, matched arrangement of aeronautical elements which (1) eliminates aerodynamic interference of, and (2) adds variable-cycle propulsion to, the level flight mode of a four-propulsor tilt-wing VTOL (vertical takeoff & landing) aircraft, without an additional element of variable geometry. This is achieved by configuring the components such that the rotor planes on either side pass through each other in the transition maneuver to form adjacent, close-coupled, counter-rotating pairs in level flight.

An exhaust gas turbocharger comprising: a twin scroll turbine housing; a turbine wheel positioned in the twin scroll housing; an exhaust gas inlet, operatively connected to port exhaust gas through each side of the twin scroll turbine housing and onto the turbine wheel; a bypass, operatively connected to the exhaust gas inlet to port exhaust gas around the twin scroll turbine housing to bypass the turbine wheel; and a valve, operatively positioned to control exhaust gas flow to each side of the twin scroll turbine housing and the bypass.

A system and method for generating a visualized data representation preserving independent variable geometric relationships is described. A pair of convex clusters are selected. Each convex cluster is rendered on a display. Each convex cluster has a center of mass located at an original fixed distance from a common origin, and is oriented along a vector formed at a fixed angle from a common polar axis. A span is measured between the centers of mass of each convex cluster. For each convex cluster, a segment is measured from the center of mass of each convex shape to a point closest to the other convex shape along the span. A new fixed distance from the common origin for the center of mass for one of the convex clusters located along the vector for that convex cluster is evaluated if the span is less than the sum of the segments of the convex clusters. The pair of convex clusters are displayed rendered using at least the new fixed distance for the center of mass of the one convex cluster.

All-internal compression inlets for supersonic aircraft, with variable geometry systems and shock stability bleed systems provide high performance, large operability margins, i.e. terminal shock stability that reduces the probability of inlet unstart, and contribute little or nothing to the overall sonic boom signature of the aircraft. These inlets have very high internal area contraction or compression and very low external surface angles. All shocks from the internal inlet surfaces are captured and reflected inside the inlet duct, and all of the external nacelle surfaces are substantially aligned with the external airflow. The inlet shock stability system consists of bleed regions that duct bleed airflows to variable area exits with passive or active exit area controls. This reduces the risk of inlet unstarts by removing airflow through a large open throat bleed region to compensate for reductions in diffuser (engine) corrected airflow demand. Because the stability bleed is not removed until the inlet terminal shock moves upstream over the bleed region, the necessary normal shock operability margin is provided without compromising inlet performance (total pressure recovery, and distortion).

A more efficient multi-stage turbocharging system and method for internal combustion engine systems is set forth. The present invention recovers the loss of a portion of exhaust energy that conventionally occurs in bypassing exhaust flow from one stage to another in a multi-stage turbocharging system. The preferred method of preserving such exhaust energy is through converting a portion of the exhaust energy of the bypassed flow from pressure to kinetic energy (velocity) by passing the bypassed flow through a VGT vane outlet or other variable geometry valve / nozzle, and then not allowing the accelerated flow to dissipate energy before reaching the subsequent stage's turbine wheel, where the accelerated flow may then be converted to a mechanical rotational force by the lower pressure turbine's wheel. Preferred hardware for achieving the object of the invention is also set forth, including a preferred two-volute low pressure turbocharging system with a VGT mechanism in one turbine volute only, or an alternative low pressure turbocharger with two low pressure turbines on a common shaft (again, preferably, with a VGT mechanism in one turbine only).

A method for operating a turbocharged internal combustion engine having an after-treatment device for treating exhaust gas discharged from the turbocharger, wherein exhaust gas from the engine is passed through a variable-geometry mechanism for regulating power produced by the turbine. The method comprises the steps of measuring a boost pressure of the air delivered to the intake of the engine, measuring a temperature of the exhaust gas delivered to the after-treatment device, causing the temperature of the exhaust gas delivered to the after-treatment device to substantially match a predetermined target temperature by controlling the variable-geometry mechanism of the turbine to control the amount of power extracted by the turbine, and causing the boost pressure to substantially match a predetermined target boost pressure by either inputting mechanical power into or extracting mechanical power from the turbocharger, as required, using a power addition / extraction device, such as a motor / generator, coupled to the turbocharger.

Within a turbine engine a heat exchanger may be provided to cool compressor air flows to be utilized for cabin ventilation or other functions. A fluid flow acting as a coolant for the heat exchanger is generally drawn from the by-pass duct of the engine and a dedicated outlet duct is provided such that the exhausted fluid flow from the heat exchanger is delivered along the conduit duct to a low pressure region. In such circumstances, an appropriate pressure differential across the heat exchanger is maintained for operational efficiency when required, whilst the exhausted fluid flow is isolated and does not compromise the usual engine ventilation vent exit area sizing. Over-sized ventilation vents would create an aerodynamic step and therefore drag upon the thrust of the engine. Typically, the outlet end of the outlet duct has a variable geometry to enable adjustment in the pressure differential across the heat exchanger such that an air fan valve used to control flow rate through the heat exchanger may not be required.

A bone reamer has an ablation device for forming cavities in body tissue, the ablation device is movable with respect to a head of the reamer, and is capable of protruding at least partially beyond a surface of the head. The amount of protrusion the ablation device protrudes beyond the surface of the head has a variable geometry and the geometry is remotely modifiable. More particularly, the amount the ablation device extends beyond the outer surface of a reamer head body can be varied by an actuator located on the reamer outside the body.

An agricultural metering device with a variable geometry meter roller is provided. The agricultural metering device includes a meter roller having a plurality of flutes. An aggregate cross sectional area of the flutes increases along a longitudinal axis of the meter roller.

One or more heat exchangers mounted in a duct have heat transfer cooling passages therein and a variable geometry flow restrictor is integral with each of the heat exchangers. An annular slide valve axially translatable within the duct is operable to open and close or vary a variable area between the heat exchangers and one of inner and outer casings bounding the duct. The heat exchangers may be being circumferentially distributed around an annular duct and include radial or circumferentially curved heat transfer tubes or vanes.

A system is provided. The system includes an internal combustion engine having an intake manifold and an exhaust manifold. The system also includes a high pressure turbocharger having a variable geometry high pressure turbine drivingly coupled to a high pressure compressor, wherein the variable geometry high pressure turbine is driven by a first portion of exhaust gases from the exhaust manifold, wherein the high pressure compressor is configured to compress an intake air and to provide the compressed intake air to the intake manifold. The system also includes a low pressure turbocharger having a variable geometry low pressure turbine drivingly coupled to a low pressure compressor, wherein the variable geometry low pressure turbine is driven by a second portion of the exhaust gases from the exhaust manifold, wherein the low pressure compressor is configured to compress a third portion of the exhaust gases from the exhaust manifold and to provide the compressed third portion to the intake manifold, wherein the first and second portions of the exhaust gases are different from one another.

An oscillating mechanism for a timepiece movement, including a first rigid element and a second rigid element, each one fixed on a different element of the movement and at least one of which is mobile relative to the other and pivots about an axis. The mechanism is monobloc and flexible with a variable geometry, and includes a first elastic restoring mechanism producing an elastic connection between the first rigid element and an intermediate rigid element, and a second elastic restoring mechanism producing an elastic connection between the intermediate element and the second rigid element, which all are coplanar according to one plane and configured to be deformed according to the plane.

There is provided an acetabular shell liner, and particularly a constrained liner, having a variable rim surface geometry to improve the range of motion of a femoral component within the liner and decrease the incidence of dislocation and subluxation. There are also provided methods of making and using the acetabular shell liner. Prosthetic devices, and particularly hip joint prostheses, containing the acetabular shell liner having a variable rim surface geometry are also provided.

A device for compressing gas using thermal energy. In a subsonic embodiment the heat gas passes through a convergent pipe C1 where it is provided with operating velocity, a convergent pipe C2 where it is simultaneously maintained at high speed and cooled by evaporation of liquid sprayed by nozzles R with adjustable position distributed in C2. In a supersonic embodiment, the gas reaches sonic velocity at the throat of C2 and supersonic velocity in a divergent DG, then compressed in a convergent CG1 and simultaneously cooled by evaporation of sprayed liquid. In both embodiments, the gas is finally compressed in a subsonic divergent DG1. Pipes with variable geometry enable to modify the cross-sections of the throats of the device. The device is essentially designed for thermoelectric power stations.

An exercise apparatus comprises: a frame having a base portion and having first and second right support elements and first and second left support elements; a crank system comprising first and second crank coupling locations, the crank system being supported by the frame; a right foot support member; a left foot support member; a right guide element coupled to the right foot support member and; a left guide element coupled to the left foot support member; a first flexible support system comprising a first flexible element, the first flexible element coupled to the first and second right support elements and the right guide element and coupled to the first crank coupling location; and a second flexible support system comprising a second flexible element, the second flexible element coupled to the first and second left support elements and the left guide element and coupled to the second crank coupling location, wherein alternating motion of the right and left foot support members causes the first and second crank coupling locations to rotate.