163results about How to "Reduced flow separation" patented technology

A rotor hub fairing system includes an upper hub fairing, a lower hub fairing and a shaft fairing therebetween. The rotor hub fairing system is sized and configured to reduce the overall drag on a dual, counter-rotating, coaxial rotor system. Preferably, the rotor hub fairing is fully integrated. The shaft fairing preferably includes a minimal thickness at the midsection to reduce drag with an increasing thickness adjacent the upper and lower hub fairings to reduce the flow separation on the hub fairing surfaces without overly excessive drag. Other aerodynamic structures, such as a horizontal splitter and/or a plurality of turning vanes may be mounted to the shaft fairing to facilitate flow around the upper and lower hub fairings to reduce flow separation and drag.

A compressed gas cooling apparatus in which gas from an upstream compression stage enters an inlet section from an inlet opening and flows to a heat exchanger that cools the gas. The cooled gas then flows from the heat exchanger to the outlet section where the gas is discharged from an outlet opening. Pressure drop within the apparatus is decreased by providing the inlet and outlet sections with ever increasing and decreasing cross-sectional flow areas. In order to further decrease pressure drop due to a swirl within the gas flow imparted from the upstream compression stage, the inlet section is provided with first and second subsections wherein the cross-sectional flow area of the first subsection increases at lesser rate than the second subjection. Alternatively, or in addition, the inlet section can be provided with partitions to divide the gas flow into subflows in order to lessen pressure drop from swirl.

A flow channel with a branch channel perpendicular to a main channel including an edge defining an inlet opening of the branch channel is provided. A chamfer is disposed at the upstream edge of the inlet opening and a straight edge is disposed at the downstream edge of the inlet opening, perpendicular to the main channel.

Lift produced by an airfoil of an aircraft is increased by suppressing fluid detachment from the surface of the airfoil. An engine cowling extends outwardly from the surface of the airfoil that has an exit plane configured for directing exhaust gases toward a rear of the aircraft. Fences extending outwardly from the surface and proximate to the exit plane of the engine cowling are configured to guide the exhaust gases along at least a portion of the airfoil surface, thereby restricting spanwise movement of the gases and increasing the Coanda Effect exhibited by the gases, thereby increasing the amount of lift produced along the surface of the airfoil. Such techniques may be used in short take-off and landing (STOL) aircraft.

An exhaust hood for a turbine includes a shell casing, an external support structure, conical corner plates, and a butterfly plate. The shell casing includes an inner surface and an outer surface. The external support structure is coupled to the shell casing outer surface, and provides structural support to said shell casing. The butterfly plate is coupled to the shell casing inner surface for channeling flow into the exhaust hood and subsequently into the condenser. The butterfly plate has a substantially elliptically-shaped cross-sectional profile that facilitates reducing flow separation losses of steam flowing therethrough into the exhaust hood.

A section of a gas turbine engine including a radial spoke is provided. The spoke includes an aerodynamic shape with a leading side and a trailing side and, extending from the leading side to the trailing side, a first side and a second side, opposite the first side. The spoke also includes at least one flow guiding element arranged on at least the first side.

A thermo-electro sub-assembly comprises a gas supply, a first duct, a first heatsink adjacent a first device, a second duct, and a second heat sink adjacent a second device. The gas supply may be realized as a fan, a blower, or a compressed gas source. The first duct provides a passageway for delivering pressurized gas from the gas supply to the first heat sink. The duct may include a plurality of vanes for reducing the turbulence and air boundary separation within the duct. The first heatsink is in thermal communication with a first heat-producing device such as a microprocessor. In a preferred embodiment the heatsink comprises an axial shaped folded fin heatsink. The second duct is used to provide a pathway for the air leaving the first heatsink and delivers the air to the second heatsink. The second duct may also include a plurality of vanes for reducing turbulence and boundary flow separation within the second duct.

The invention provides a casing based on self-circulation oscillation jet, a compressor and a stability enhancing method thereof. A fluid oscillator flow channel is arranged in the casing, and air flow enters the fluid oscillator flow channel from an oscillation jet air entraining inlet between (n+m) stage stators or rotors of the casing; the pressure of the oscillation jet air entraining inlet is greater than the pressure of an oscillation jet outlet between n stage stators or rotors, the air flow forms oscillation jet on the oscillation jet outlet between the stators after flowing through the fluid oscillator flow channel, and angle area flow separation and suction surface flow separation corresponding to the top ends of stator blade grids are reduced; or, the oscillation jet isformed on the oscillation jet outlet of the rotors, tip clearance secondary flow corresponding to rotor blades is reduced, and the stable work margin of the compressor is improved; and due to a pressure difference, when the oscillation jet air entraining inlet is located between the (n+m) stage stators or rotors, the fluid oscillator flow channel generate suction action on a top end boundary layer and the secondary flow of the (n+m) stage stators or rotors, the flow separation is reduced, and the stability enhancing effect is generated.

The invention discloses a noise-reducing method for an electric fan based on blade modification and an improved blade structure of the electric fan. The method comprises the following steps of: (1) establishing a hydromechanic calculating model of an original blade structure of the electric fan; (2) performing kinetic analysis on the original blade structure of the electric fan to obtain fluid field data and monitoring the sound pressure level of noise of a preset measuring point, wherein the fluid field data comprises a blade surrounding vorticity value and vortex structure distribution; (3) performing a modified design on the fan blade structure of the electric fan continuously and performing kinetic analysis on the modified blade structure of the electric fan to obtain fluid field data and measured point noise data, and reducing the blade surrounding vorticity value and crushing large vortexes into small vortexes till the sound pressure level of noise of the preset measuring point is reduced on the premise that the blast capacity is invariable at same input power; and (4) manufacturing a fan model, measuring the blast capacity and the sound pressure level through experiments, and verifying the reducing effect of the sound pressure level of the noise of the measured point. By modified noise reduction on the blade of the fan by means of computational fluid mechanics, the method is high in pertinence and high in operability.

A centrifugal fluid pump has an impeller having a hub with vanes that may be airfoil shaped and may be twisted along their lengths. A shroud having an inlet is connected to the vanes to define with the impeller flow chambers between the vanes, at least a portion of each flow chamber having a substantially constant flow area to increase pump efficiency. An entrance feature may also be provided to improve entrance flow into the impeller, further enhancing pump efficiency.

Active flow control devices and methods are disclosed for improving the aerodynamic efficiency of airfoils. The devices and methods pertain to applying intermittent suction or intake of low-energy boundary layer fluid into airfoils in a manner delaying or eliminating boundary layer separation.