1330results about How to "Improve aerodynamic performance" patented technology

A high volume aerodynamic golf club head having a post apex attachment promoting region with a club head volume of at least 400 cc and a front-to-back dimension of at least 4.4 inches producing reduced aerodynamic drag forces. The post apex attachment promoting region is on the surface of the crown section at an elevation above a maximum face height and begins at the crown apex and extends toward the back of the club head. The post apex attachment promoting region is a relatively flat portion of the crown section that is behind the crown apex, yet above the maximum top edge plane, and aides in keeping airflow attached to the club head once it flows past the crown apex.

A pattern for improving aerodynamic performance of a turbine includes a material disposed in a pattern at a base surface of a turbine shroud such that the material is capable of abradable contact with a tip portion of a turbine bucket. The pattern includes a first plurality of ridges disposed at the base surface such that a first portion of the first plurality of ridges corresponding to a back portion of the turbine bucket is oriented at a first angle with respect to an axis of rotation of the turbine bucket. Each ridge of the first plurality of ridges has a first sidewall and a second sidewall having a first end and a second end. The first ends of the first and second sidewalls extend from the base surface. The first and second sidewalls slope toward each other with substantially equal but opposite slopes until meeting at the second ends of respective first and second sidewalls defining a centerline and a top portion of the ridge.

The present invention relates to a fairing for a trailer having a wheel assembly. The fairing is positioned on the underside of the trailer to cover a frontal area of the wheel assembly. More specifically, the fairing includes a shell and an anchoring mechanism. First, the shell is designed to cover the frontal part of the wheel assembly. Secondly, the anchoring mechanism allows attaching the shell to the wheel assembly.

The invention relates to an optimized design method for modelling of an end wall of a high load fan/compressor. The method comprises eleven steps. As the stage pneumatic load is improved, internal flow of the fan/compressor is more severe, massive secondary flow is easily generated in an area close to the end wall, and a risk of flow stall exists. The modelling of the end wall has important influence on control over the secondary flow in an end area of the high load compressor, and becomes an important research direction. Firstly, an end wall modelling parameter defining method is researched; secondarily, based on an adaptive genetic algorithm and an artificial neural network response surface model, which are developed by the research group, an orthogonal experimental design, end wall parameter definition and a flow field value simulating technology are combined to realize automatic global optimization of the end wall of the compressor; thirdly, the effectiveness of the optimizing method is verified through different test functions; finally, a blade grid of the compressor is subjected to nonaxisymmetrical optimization based on the method. A result shows that the blade grid after modelling has good pneumatic performance.

Systems and/or methods for forming a multiple-articulated flying system (skybase) having a high aspect ratio wing platform, operable to loiter over an area of interest at a high altitude are provided. In certain exemplary embodiments, autonomous modular flyers join together in a wingtip-to-wingtip manner. Such modular flyers may derive their power from insolation. The autonomous flyers may include sensors which operate individually, or collectively after a skybase is formed. The skybase preferably may be aggregated, disaggregated, and/or re-aggregated as called for by the prevailing conditions. Thus, it may be possible to provide a “forever-on-station” aircraft.

An active front deflector assembly having a deployable deflector panel, linkage assemblies, and an actuator. The system deploys and retracts based on vehicle requirements, and, when deployed, interrupts air flow thereby improving the vehicle aerodynamics, reducing emissions and improving fuel economy. The deflector panel is retractable so the vehicle meets ground clearances, ramp angles, off-road requirements, etc. The deflector panel is also both rigid and semi-rigid to absorb impact energy. The linkage assemblies are coupled to the deflector panel and a drive shaft connected to the actuator. The drive shaft transmits the drive from the actuator coupled to one linkage assembly to the other linkage assembly for moving the deflector panel between the deployed/retracted positions. The actuator is clutched to prevent damage to the system. The active front deflector assembly provides a fully deployable system with object detection, declutching of the actuator, and communication with the vehicle.

A system of aerodynamic skirt fairings designed to minimize aerodynamic drag and maintain smoother air flow over highway-operated long-haul tractor-trailer vehicles.

A wind turbine blade having an aerodynamic profile (5) with a leading edge (11), a trailing edge (13) and suction and pressure sides (17, 19) between the leading edge (11) and the trailing edge (13) which has, on at least one part of the wind turbine blade, a Trailing Edge Region (TER), the transversal section of which increases in the direction of the trailing edge (13). Said trailing edge region (TER) preferably has a divergent form with a curved concave surface on its lower part.

Engineered particles are provided may be used for the delivery of a bioactive agent to the respiratory tract of a patient. The particles may be used in the form of dry powders or in the form of stabilized dispersions comprising a nonaqueous continuous phase. In particularly preferred embodiments the particles may be used in conjunction with an inhalation device such as a dry powder inhaler, metered dose inhaler or a nebulizer.

The Umbrella Semi-Trailer Drag Reducer is a device that reduces tractor-trailer aerodynamic drag, saving energy and reducing fuel consumption. The design includes a number of features similar to an umbrella, including flexible skin, metal ribs, quick-acting deployment, and compact stowage. The Umbrella Semi-Trailer Drag Reducer is designed to minimize installed cost, be robust and vandal resistant, and reduce the time needed for deployment to only a few seconds. The design includes two independent, paraboloid, mirrored halves, one mounted to each door. The bottom of each mirrored half is open, with a profile similar to one quadrant of an umbrella. Wide-throw hinges accommodate the collapsed stowed drag reducer. Turnbuckles maintain taught skin. The design allows easy retrofit for most existing semi-trailers. The drag reducer is mounted high above the road surface, with no part protruding beyond the top or sides of the semi-trailer.

A vehicle body floor structure includes: a floor panel; a floor cross member provided on the floor panel and joined to left and side sills provided on left and right sides of the floor panel; and left and right front floor frames provided on the floor panel and extending from a dashboard cross member to a substantial middle region of the floor panel through a recessed portion of the floor cross member. The left and right front floor frames each have a rear section located rearwardly of the floor cross member, and these rear sections are bent outwardly to be joined to the left and right side sills, respectively. Each of the front floor frames may be provided on the upper surface of a downwardly concaved floor section of the floor panel and extend between the concaved floor section and the floor cross member.

A turbine airfoil with a relatively thick TBC applied over the airfoil surface. The airfoil has a surface contour on the trailing edge region with a forward end having a large amount of taper and a rearward end with less taper such that a substantially constant wall thickness is formed in the rearward end. The TBC is applied over the airfoil surface and tapers off at the trailing edge ends on the pressure side and the suction side walls to produce an ideal surface contour on the airfoil. In another embodiment, the airfoil surface includes a tapered section at the trailing edge region, and the TBC is applied over the taper so that an over-coating is formed. The TBC over-coating is then removed and a smooth and ideal surface contour is produced along the airfoil surface. Small raised bumps each having a height of the desired thickness of the TBC to be applied over the respective bump is used to control the finished thickness of the TBC.

This invention discloses a stator internal gas-inducing efficient anti-surge steady expansion device of a multi-stage axial compressor composed of a stator, a gas-suction groove, a gas-inducing pipe and a gas-collecting chamber, in which the stator is stator blade in the multi-stage axial compressor, the groove, one or many, is placed in a region adjacent to flow separation existing on the surface of the stator suction face, the gas inducing pipe is in the stator blade and a ventilation pipe connecting suction pipes, the collecting chamber is set outside of the runner box and collects gas flows induced by the gas-inducing pipe after the suction groove absorbs small low energy gas flows, and the suction groove absorbs fluids of low energy on the surface of the stator suction side and transports them to the chamber and discharges them out of the system after mixed press.