156 results about "Stagnation point" patented technology

A device for confining an object to a region proximate to a fluid flow stagnation point includes one or more inlets for carrying the fluid into the region, one or more outlets for carrying the fluid out of the region, and a controller, in fluidic communication with the inlets and outlets, for adjusting the motion of the fluid to produce a stagnation point in the region, thereby confining the object to the region. Applications include, for example, prolonged observation of the object, manipulation of the object, etc. The device optionally may employ a feedback control mechanism, a sensing apparatus (e.g., for imaging), and a storage medium for storing, and a computer for analyzing and manipulating, data acquired from observing the object. The invention further provides methods of using such a device and system in a number of fields, including biology, chemistry, physics, material science, and medical science.

Methods and apparatus for preventing patient bloodstream infection by microorganisms during administration of various medications or fluids through IV lines. In particular, the invention reduces contamination of IV lines, connecters, stopcock valves, manifolds, ports, etc. by means of irradiation by violet and/or blue light. Each embodiment comprises a source of violet and/or blue light and an optical element optically coupled to that light source for shaping the radiation pattern of the light emitted by the light source. Preferably, a light-emitting diode or a laser diode that emits light in the desired wavelength can be used. The optical element, optically coupled to the light source, is embedded or installed in or attached to a component of an IV set, the emitted light being directed to a “point of entry” or any other stagnation point of an IV set.

A method and apparatus for converting single multiphase fluid flow into plural multiphase fluid flows having substantially uniform composition and flow properties. A manifold comprises an enclosure having an inlet and an inner surface perpendicular to the inlet such that the incident angle of input flow impacts the surface to form a stagnation point whereby an intermediate flow is deflected along the surface substantially symmetrically outward from the stagnation point and channeled to a plurality of parallel fluid outlets connected to the enclosure. The distance between the stagnation point and the plurality of outlets is selected to maintain substantially equivalent fluid pressures and uniform flow rates at the outlets. A preferred embodiment of the manifold channels the intermediate flow between two walls forming a triangular shaped nozzle directing the flow from the stagnation point to the base of the triangle for communication of electrolyte to a metal-based fuel cell through the plurality of outlets.

A method is provided for calculating flow performance characteristics of a body immersed in a fluid under a set of fluid flow conditions. The method comprises providing a geometrical description of a surface of the body and determining the set of fluid flow conditions. The set of fluid flow conditions includes a combination selected from the combination set consisting of angle of attack and leading edge stagnation point location, angle of attack and flow separation point location, and leading edge stagnation point location and flow separation point location. The method further comprises calculating a velocity flow field for the body using a critical point potential flow methodology and calculating flow performance characteristics.

The invention discloses a series-parallel movable heavy load casting robot. The series-parallel movable heavy load casting robot comprises a four-wheel drive type moving platform, a rotation device, a stand column assembly, a lifting drive device, a parallel work arm, a tail end executor and a binocular visual system. Four-wheel omnidirectional wheel drive is adopted in the four-wheel drive type moving platform to achieve long-distance flexible stable walking, a rear hydraulic supporting leg and an adjustable hydraulic supporting leg are used for achieving stagnation point self-balance support, work supporting stability is improved, a robot body has five space motion freedom degrees, the rotation device and the lifting drive device can achieve rotation and lifting adjustment, the four-freedom-degree parallel work arm can carry out posture adjustment on the tail end executor, different tail end executors can be replaced according to work needs, different work needs of core assembling, core discharging, casting, carrying and the like of a large casting can be met, the casting core assembling and discharging and casting work efficiency, quality and safety can be improved, and labor intensity and production cost of operators can be reduced.

A separation wake zone behind a heat transfer tube in a heat transfer device of a heat exchanger or the like is reduced, whereby a heat transfer action of the heat transfer device can be augmented and a pressure loss thereof can be reduced. The heat transfer device of the heat exchanger has a linear or tubular heat transfer object (T) in heat transfer contact with a heat carrier fluid (A), and a heat transfer fin (F) integrally formed with the heat transfer object for heat transmission therebetween. The heat transfer fin is provided with a guide fin (10) positioned in vicinity of the heat transfer object, and the guide fin conducts the fluid to the rear of the heat transfer object, thereby reducing the separation wake zone behind the heat transfer object. A position (B) of separation point of the fluid is set to be at an angular position (β) equal to or greater than 90° from a stagnation point (E) on the heat transfer object by setting of an attack angle, configuration, position and dimensional proportion of the guide fin.

The invention discloses an experimental facility and an experimental method for the fire suppression effectiveness evaluation of additive-containing water mists. The experimental facility comprises an oxidizing agent flow quantitative supplying and conveying system, a combustible gas quantitative supplying and conveying system, a representation system, and a data acquisition and remote control system, wherein the oxidizing agent flow quantitative supplying and conveying system is composed of a frequency conversion vortex fan, a vortex shedding flowmeter, a small wind tunnel, an atomization device and a sprayer support; the combustible gas quantitative supplying and conveying system is composed of a columnar porous burner and an automatic gas distributing system; the representation system is composed of a water mist and flame action observation device, a flame temperature measurement device and a condensed phase grain size and speed measurement device. The experimental facility can realize quantitative supplying of air and combustible gas, the adjustability of the particle size distribution and the release amount of the liquid phase fire extinguishing agent and the adjustability of the concentration of additive, and the representation of the temperature of a position nearby a stagnation point, the particle diameter and the speed. The experimental facility can be used for screening high-efficiency water mist additives, quantitatively evaluating the fire suppression effectiveness for specific flames in the aspects of the variety and the concentration of the additive, and researching the physical and chemical mechanism of the action of the condensed phase fire extinguishing agent and the flame.

The invention discloses a layout method for an embedded air data sensing system pressure hole based on a genetic algorithm, comprising the following steps: taking an initial supposition position (xi, yi and zi) as the input of a value function; converting coordinates xi, yi and zi into a circumferential angle phi i of and a conical angle lambda i; simulating to obtain the pressure value Pi of the point on the surface of an aircraft by the computational fluid mechanics according to a real angle of attack alpha r, a sideslip angle beta r and a given mach number, wherein the pressure value of a stagnation point is real total pressure Ptr; adding generally distributed random noise epsilon N on the pressure value Pi to simulate pressure measuring inaccuracy; calculating the angle of attack, the sideslip angle and the pressure of the stagnation point by the values with 'noise'; comparing the angle and the pressure of the stagnation point which are obtained by estimation, with a reference value under each simulation situation; and calculating the value function by the weighted sum of an error ( which is the difference of an estimation value and the reference value) mean square root.

An airfoil article including a composite skin having a first surface and a second surface opposite first surface, forming a leading edge. The leading edge is during use subjected to an airflow meeting the leading edge at stagnation points. The leading edge includes an elongated member. The outer surface of the elongated member is arranged flush with the first surface of the composite skin such that an essentially smooth aerodynamic surface of the leading edge is formed. The elongated member is adapted to serve as an erosion protection of the leading edge and to function as an electrode of a plasma generating system.

A method and apparatus for converting single multiphase fluid flow into plural multiphase fluid flows having substantially uniform composition and flow properties. A manifold comprises an enclosure having an inlet and an inner surface perpendicular to the inlet such that the incident angle of input flow impacts the surface to form a stagnation point whereby an intermediate flow is deflected along the surface substantially symmetrically outward from the stagnation point and channeled to a plurality of parallel fluid outlets connected to the enclosure. The distance between the stagnation point and the plurality of outlets is selected to maintain substantially equivalent fluid pressures and uniform flow rates at the outlets. A preferred embodiment of the manifold channels the intermediate flow between two walls forming a triangular shaped nozzle directing the flow from the stagnation point to the base of the triangle for communication of electrolyte to a metal-based fuel cell through the plurality of outlets.

The invention discloses a hypersonic velocity wing robust optimization design method considering machining errors and belongs to the technical field of optimization design. The method comprises the following steps: fully considering geometric machining errors existing in hypersonic velocity wing design, and realizing quantitative characterization of a machining error coefficient by utilizing an interval vector under the condition that a probability density function of machining error parameters is unknown; establishing aerodynamic configuration of the hypersonic velocity wing through a parametrization method, and performing nonstructured surface mesh division; combining an interval parameter vertex method with an aerodynamic/thermal engineering algorithm, and calculating upper and lower bound of intervals of total stagnation point heating capacity and lift-drag ratio of the wings; and on the basis, establishing a multi-target interval robust optimization model, and performing optimization design on the wing shape by using a genetic algorithm. The numerical result shows that according to the method, the total stagnation point heating capacity of the designed wing is reduced under the precondition that lift-drag ratio constraint of the wing is maintained; meanwhile, a fluctuation range of the total stagnation point heating capacity is narrowed, and a new thought is provided for shape design of the hypersonic velocity wing.

There is provided an anti-icing system that has a simple structure and makes it possible to exert anti-icing performance by dealing with displacement of a stagnation point without increasing air resistance. The anti-icing system according to the present invention blows heated gas to an inner surface of a wing of an aircraft, and includes: a piccolo tube that includes a flow path through which the heated gas flows in a longitudinal direction from a rear end to a front end, and a plurality of ejection holes provided along the longitudinal direction to make the flow path communicate with an outside; and a supply source that supplies the heated gas toward the piccolo tube. The piccolo tube is held to cause positions of the respective ejection holes to be fixed in a gravity direction.

The invention discloses a staggered opposite jetting air film hole row structure used for turbine blade leading edge air film cooling. Air film cooling hole rows are processed in a turbine blade leading edge area. The suction surface staggered opposite jetting air film hole row and the pressure surface staggered opposite jetting air film hole row are arranged at the two sides of the blade leading edge stagnation point staggered opposite jetting air film hole row. The cross section shape of each air film hole is changed from the cross section shape of the air film hole inlet to that of the air film hole outlet, and the air film holes are communicated with the cold channels the turbine blades. The radial inclination angle of the air film holes is 25-60 degrees; the aperture of the air film holes is 0.3-0.8mm; the radial hole spacing of the inclination holes in the same direction in the air film hole rows is 3d-9d; the flow direction distance between the center lines of the staggered air film holes in the air film hole rows is 0.5d-d; and the radial distance between the two adjacent staggered air film holes is 3d-9d. According to the staggered opposite jetting air film hole row structure, a relatively stable air film coverage area is enabled to be formed on the wall surface of the blade leading edge by the jetted cold air so that the air film cooling effect is improved; besides, the staggered opposite jetting air film hole row structure has the characteristics of being easy and convenient to process and low in cost.

An aircraft engine includes an afterburner which has a flame stabilizer. The flame stabilizer maintains a flame generated from a mixed gas of a combustion gas and air. The flame stabilizer includes multiple gutters each configured to generate a flame stabilization area for the flame on its downstream side. Each gutter is formed from: a curved apex section having a stagnation point; and flat plate-shaped side surface sections integrally formed on the respective two sides of the apex section. Each gutter has a V-shaped cross-sectional shape which is opened to the downstream side. At least one through-hole is formed only in each side surface section of each gutter.

The invention relates to an unmanned aerial vehicle icing protection device comprising wings, a heat conduction device and a heating device. The outer walls of the wings are covered with skins, and anti-icing cavities are formed in the wings. The heat conduction device comprises an engine compressor, a flow limiter, a one-way valve and anti-icing valves, and the anti-icing valves are arranged on the wings. The heating device comprises icing sensors, electric heating layers and pulse devices which are connected sequentially. According to the unmanned aerial vehicle icing protection device, heatof an engine and the electric heating and pulse devices are mixed for deicing, the advantages of the heat of the engine and the electric heating and pulse devices are combined, a good icing protection effect is formed, namely it is guaranteed that no ice layer exists nearby important parts such as stagnation points at the front edges of the wings, damage of icing to the aerodynamic shape of a vehicle is also reduced, and the power consumption of the vehicle is reduced.

The invention provides an aerodynamic heat measuring method suitable for a blunt body reentry vehicle. The aerodynamic heat measuring method is used for measuring of surface heat flow distribution ofthe side walls, the large bottom, the stagnation point area and the boundary layer transition area of the blunt body reentry vehicle and measuring of total heating capacity of the windward side and the leeward side. The aerodynamic heat measuring method comprises the following steps that according to the appearance and a reentry trajectory of the blunt body reentry vehicle, simulation analysis onaerodynamic heat load on the surface of the blunt body reentry vehicle is conducted; according to the sizes and distribution of aerodynamic heating heat flows, sensor selecting and measuring range determining are conducted; according to the aerodynamic heat measuring task requirement of the blunt body reentry vehicle, configuration demand analysis of sensors is conducted; sensor layout design is conducted; and sensor calibration and mounting are conducted. According to the aerodynamic heat measuring method, the real reentry heat flow load can be obtained, particularly, real-time data of transition of the boundary layer on the surface of the vehicle can be provided, and guiding significance is achieved on a current calculating analysis model and the ground test technical scheme.

A soiling shield (80) affixed to a blade airfoil (22) of a wind turbine generator (20). The soiling shield (80) includes a portion extending along and spaced apart from a pressure side surface (88) of the blade airfoil (22). The soiling shield (80) is positioned not to impede an air flow stream (98) flowing to a stagnation point (130) on the pressure side surface (88) during operation of the wind turbine generator (20) at or below rated power.