48results about How to "Delayed air separation" patented technology

An aerodynamic drag reducing apparatus for use with vehicles having downstream surfaces that are not streamlined. The apparatus consists of folding panels that extend rearward for use in a drag reducing configuration and collapse for use in a space saving configuration.

An aircraft includes a surface over which an airflow passes. A plasma actuator is configured to generate a plasma above the surface, the plasma coupling a directed momentum into the air surrounding the surface to reduce separation of the airflow from the surface. A method of reducing separation of an airflow from a surface of an aircraft includes generating a plasma in air surrounding the surface at a position where the airflow would separate from the surface in the absence of the plasma.

The invention discloses a vertical takeoff and landing unmanned aerial vehicle with foldable fixed wings based on a dual-duct fan power system. A dual-duct fan power system which is horizontally arranged at the tail of the body of the unmanned aerial vehicle in a tail-driving arrangement is adopted, so that lifting force for vertical takeoff and landing and thrust for horizontal flying are provided for an aircraft; a control surface which is arranged at the exit of each duct in a deflected manner is used for providing vector thrust, so that quick attitude change is realized; wings adopt a folding wing configuration, when the aircraft vertically takes off and lands / flies at a low speed, the wings are folded to decrease the frontal area of cross wind, and when the aircraft flies horizontally, the wings are unfolded to obtain large lifting force; and combined optimization of ducts and the wings is adopted, the wings are arranged in a specific duct air flow region, the duct suction generates a Coanda effect at a wing edge, so that the properties of the wings are improved. Multi-mold flight tasks such as vertical takeoff and landing, high-speed cruise, and the like of the aircraft are realized; the vertical takeoff and landing aircraft is high in aerodynamic efficiency during hanging in the air / flying at a low speed; and the vertical takeoff and landing unmanned aerial vehicle is high in anti-disturbance capacity during takeoff and landing / hanging in the air. The vertical takeoff and landing unmanned aerial vehicle is low in energy consumption, small in noise and high in safe reliability.

A variable geometry inlet guide vane assembly that reduces stress placed on downstream compressor blades in gas turbine engines. The invention circumferential leans upstream guide vanes, pushing engine core air flow radially. This allows for aerodynamic stresses on the downstream blades to be reduced. The invention overcomes the difference in movement between a unison ring and a vane arm by providing a hinge in conjunction with a spherical bearing that couples to the unison ring.

A fan-turbine rotor assembly (24) includes a multitude of turbine blades (34) which each define a turbine blade passage which bleed air from a diffuser section (74) to provide for regenerative cooling. Regenerative cooling airflow is communicated from the radial core airflow passage (80) through the diffuser passages (144), through diffuser aspiration passages (146A, 146B) and into the turbine blade passages (150a). The regenerative cooling airflow exits from the turbine blade passage (150a) and transfers received thermal energy into an annular combustor (30). The received thermal energy is recovered at the highest temperature in the cycle.

A fan-turbine rotor assembly (24) includes a multitude of turbine blades (34) which each define a turbine blade passage which bleed air from a diffuser section (74) to provide for regenerative cooling. Regenerative cooling airflow is communicated from the radial core airflow passage (80) through the diffuser passages (144), through diffuser aspiration passages (146A, 146B) and into the turbine blade passages (150a). The regenerative cooling airflow exits from the turbine blade passage (150a) and transfers received thermal energy into an annular combustor (30). The received thermal energy is recovered at the highest temperature in the cycle.

A dynamoelectric device cooling air flow baffle is given a shape that increases its heat transfer and cooling efficiency by providing the baffle with an annular concave surface around its outer perimeter edge that redirects air flow radially inwardly around stator winding end turns while reducing separation of the air flow and also directs the cooling air flow around an inner edge of a center hole of the baffle while reducing separation of the air flow and increasing air flow velocity, thereby efficiently cooling the stator assembly of the dynamoelectric device.

The invention discloses a volute, a fan and an air conditioner. The volute is provided with an air outlet, an air inlet and an air passage communicating with the air outlet and the air inlet. The volute is characterized in that the volute is provided with a volute tongue; a groove is formed in the surface, making contact with airflow, of the volute tongue; and a sound absorbing structure coupled with the groove to form a noise reduction portion is arranged in the groove. According to the technical scheme, the sound absorbing structure and the groove are coupled to form the noise reduction portion used for silencing and noise reduction. When airflow inside the volute flows through the volute tongue, the noise reduction portion can relieve impact of the airflow to the volute tongue and airflow separation on the surface of the volute tongue, flowing of the airflow is more uniform, meanwhile, the pressure pulsation degree is lowered, and the noise inside the volute is further reduced.

The invention discloses a centrifugal fan and an air conditioner, relates to the field of air conditioning and aims to lower fluid flow loss and the noise of the centrifugal fan. The centrifugal fan comprises a first plate, a second plate and vanes arranged between the first plate and the second plate, and a flow deflection channel is formed between every two adjacent vanes; flow deflectors are arranged in the flow deflection channels; the flow deflectors and the vanes are identical in shape but different in size. According to the technical scheme, the flow deflectors are arranged in the flow deflection channels additionally, channels at the front edges of original vanes are narrowed, fluid in the flow deflection channels is accelerated, the kinetic energy of the fluid on the suction surfaces is effectively increased, low-energy fluid is effectively prevented from gathering, growth of the boundary layer thickness is restrained, the airflow separation phenomenon on the suction surfaces of the vanes is reduced, and finally the fluid flow loss and the aerodynamic noise of the centrifugal fan can be lowered.

The invention discloses a cabinet air conditioner which comprises a casing, an air outlet mechanism and a heat exchanger. The cabinet air conditioner further comprises an axial flow wind wheel arranged above the heat exchanger and a wind wheel motor for driving the axial flow wind wheel to rotate. The air outlet mechanism is arranged above the axial flow wind wheel and comprises an air guide ring with an arc-shaped air outlet face, and the top end of the side wall of the air guide ring is provided with an air guide ring air outlet. According to the cabinet air conditioner, the axial flow wind wheel is adopted and is large in air volume, high in efficiency and simple in structure. Since airflow flowing out of the axial flow wind wheel flows along the arc-shaped air outlet face, airflow deviation is reduced, airflow is gathered, air volume loss and an airflow separation phenomenon of an air outlet are reduced, wake loss is reduced to reduce airflow kinetic energy loss, and noise caused by gas turbulence is reduced. Therefore, according to the cabinet air conditioner, factors such as air volume, air pressure and noise of the indoor cabinet air conditioner are all considered, and comprehensive performances are effectively improved.

A centrifugal blower includes an outer rotor, and a turbo fan. The turbo fan includes blades, an other end plate, and a cylinder portion. The cylinder portion is located inside the other end plate, and is fixed to the outer rotor. A surface of the outer rotor configures a rotor guide surface that guides an air flow toward a channel provided between adjacent blades. Each blade has a leading edge side portion located radially inside the cylinder portion. An outer end portion of the rotor guide surface in the radial direction is located at the same position in the axial direction as a one side cylinder end portion of the cylinder portion in the axial direction, in a state where a rotor contact portion of the outer rotor and a blade contact portion of the leading edge side portion are in contact with each other.

The invention provides a vortex generator and a method for delaying stall attack angle of a wing with a high aspect ratio, the vortex generator is mounted on a sweepback wing with a high aspect ratio,the vortex generator is a panel with the thickness of w, and comprises a rectangular panel part CDBI and an arc fan-shaped right-angle panel part ACI which are integrally connected; through the arrangement, the effects of delaying air flow separation, delaying stall and improving the maximum available lift coefficient are achieved.

The invention provides a deformable flap with enhanced blowing-suction synergistic high lift force. The deformable flap comprises a wing composed of a leading edge flap, a wing body and a trailing edge deformable flap, wherein a jet flow cabin is arranged in the leading edge flap, and jet flow holes connected with the jet flow cabin are formed in the upper surface of the leading edge flap; a flow suction cabin is arranged in the trailing edge deformation flap, and flow suction holes connected with the flow suction cabin are formed in the upper surface of the trailing edge deformation flap; and a micro compressor is embedded in the wing body, is respectively connected with the jet flow cabin and the flow suction cabin through rubber pipes, and sucks air flow from the flow suction holes, pressurizes the air flow and then ejects the air flow from the jet flow holes. According to the invention, a blowing-suction synergistic active flow control technology is combined with the deformation flap, and the flap is used for a large fixed-wing aircraft, so a high lift enhancement effect is generated, take-off and landing aerodynamic characteristics are improved, short-distance take-off and landing are realized, airport pressure is relieved, cruising efficiency can be improved, and voyage can be increased.

The invention discloses a novel configuration vertical take-off and landing unmanned aerial vehicle belonging to the field of aircraft transmission system and lifting rotor, which comprises a fuselage, a rolling wing system, a vertical tail, a rudder, an aileron, a flap, a detection pod and an take-off and landing actuating cylinder. A rolling wing system is installed in the duct of the wing, andthe rolling wing system is composed of two groups of rolling wings with the same size and opposite rotating directions. The propeller shaft of each roller section is coaxial, and the full vector propulsion system of cycloidal propeller is composed of two sections of each group. The invention discloses a novel configuration vertical take-off and landing unmanned aerial vehicle, which can realize vertical take-off and landing on land-based platform and sea-based platform, and has better flying quality. The invention combines the characteristics of a rotor aircraft and a fixed-wing aircraft, andhas low dependence on take-off and landing site and strong environmental adaptability. At the same time, the whole structure of cycloidal propeller system is light and simple, which has broad militaryand civilian prospects.

The invention relates to a compound type aircraft, which belongs to the technical field of aircrafts and comprises an airframe, a left composite wing, a right composite wing, a composite empennage and an undercarriage. A control system and an airborne device are arranged in the airframe. The composite empennage is located at the tail part of the airframe, and comprises a vertical empennage, a left power-driven propeller and a right power-driven propeller. The left power-driven propeller and the right power-driven propeller have the same structure and opposite rotation directions, and are symmetrically arranged on the left side and the right side of the vertical empennage. The undercarriage adopts a wheel type structure or a jumper and wheel type composite structure. The left composite wing and the right composite wing have the same structure and are symmetrically arranged on the left side and the right side of the airframe. The left composite wing is provided with two or three rotor wings internally, and each rotor wing is driven by an engine. Vanes of the left composite wing comprises front fixed vanes and rear vanes capable of deflecting around a wing axis. The rotor wings are all located under the wing axis. The compound type aircraft can be lifted vertically by only a small take-off and land zone. The compound type aircraft generates larger lifting force, and is safe, stable and flexible.

The invention discloses a compound type rotorcraft, which belongs to the technical field of aircrafts. The compound type rotorcraft comprises a fuselage, a left wing, a left rotor wing, a left shaft, a right wing, a right rotor wing, a right shaft, a thruster, an empennage and an undercarriage, wherein the left wing is identical with the right wing in structure; the left wing and the right wing are symmetrically arranged on the left side and the right side of the fuselage; the left rotor wing and the right rotor wing are identical in size and are opposite in rotating direction; the left rotor wing is arranged below the middle part of the left wing through a bearing and the left shaft; the right rotor wing is arranged below the middle part of the right wing through a bearing and the right shaft; the leading edge of the left wing is higher than the trailing edge of the left wing; an included angle between the rotating plane of the left rotor wing and the plane of the left wing is greater than 10 degrees; an included angle between the left wing and a horizontal plane is between 15 degrees and 30 degrees; an included angle between the rotating plane of the left rotor wing and the horizontal plane is 5 degrees and 15 degrees; the leading edge of the left wing is before the most front end of a rotating circle of the tip of the left rotor wing; the trailing edge of the left wing is behind the rearmost end of the rotating circle of the tip of the left rotor wing; the compound type rotorcraft is relatively stable and safe in flying.

The invention relates to an aircraft with a skylight on a wing, which belongs to the technical field of aircrafts. The aircraft with the skylight on the wing comprises an aircraft body, a left composite wing, a right composite wing, a tail wing and a landing gear. An operation system and airborne equipment are mounted in the aircraft body. The tail wing is positioned at the tail part of the aircraft body; and the tail wing comprises a horizontal tail wing and a vertical tail wing. The landing gear uses a wheel type structure or a skid and wheel combined structure. The left composite wing and the right composite wing have same structures and are symmetrically mounted on the left and right sides of the aircraft body. The left composite wing comprises a main wing, a movable wing, a rotor wing, an engine and a bracket. The front edge of the main wing is higher than the back edge of the main wing; the right end of the main wing is connected with the aircraft body; a push-and-pull skylight is arranged at the middle part, close to the aircraft body, of the main wing; the movable wing can cover the window of the skylight under the pushing and pulling of external forces; and the skylight is opened when the movable wing is inserted into the left section of the main wing. The rotor wing and the engine are mounted right under the window through the bracket. The rotating plane of the rotor wing is horizontally placed. The aircraft can vertically take off and land and is safe, energy-saving and efficient.

The invention discloses an angle-adjustable energy-saving manger board comprising a lower wall board fixedly arranged on a deck, and an upper wall board hinged to the upper end of the lower wall board; a first reinforcing girder is fixedly arranged on the rear end face of the lower wall plate, and a second reinforcing girder is fixedly arranged on the rear end face of the upper wall plate. The angle-adjustable energy-saving manger board further comprises a telescopic mechanism capable of enabling the upper wall board to rotate around the top of the lower wall board, and the two ends of the telescopic mechanism are hinged to the rear end face of the lower wall board and the second reinforcing girder correspondingly. Transverse reinforcing ribs are fixedly arranged on the rear end face of the upper wall plate and the rear end face of the lower wall plate, and a transversely-distributed top plate is fixedly arranged at the top of the upper wall plate. The upper end of the second reinforcing girder is fixedly connected to the top plate. Air resistance can be reduced, and energy consumption of the ship is saved.

The invention provides a cross-flow fan blade, a cross-flow fan, an indoor unit and an air conditioner. The cross-flow fan blade comprises a blade body (1); the blade body (1) comprises a blade back (2); and the blade back (2) is provided with a rectification projection (3) projected on the blade back (2). The cross-flow fan blade can reduce the airflow separation phenomenon at the back part of the blade when the fan is rotated, and reduces the airflow separation loss.

The invention discloses a multi-propeller flying car. The multi-propeller flying car comprises a car body, a power device, a foldable wing, a retractable propeller, an empennage and direction-changeable air jetting devices. The car body is of a streamlined design. The power device is internally arranged in the front portion of the car body. The foldable wing is fixed to the middle portion of the car body, and a foldable propeller is mounted at the top end of the foldable wing. The retractable propeller is mounted at the top of the car body. The retractable propeller is provided with a telescopic device, and a foldable propeller is mounted at the top end of the telescopic device. The empennage is mounted on the tail portion of the car body. The direction-changeable air jetting devices are mounted on a chassis of the car body. The power device provides power for the multi-propeller flying car. The multi-propeller flying car ensures the flexibility and driving performance of the car on the land, and can take off vertically.

The invention discloses a radiator of an engine compartment of an automobile. The automobile comprises a body and the engine compartment. When the outside airflow flows through the engine compartment,a recirculation zone is formed in the engine compartment. The radiator comprises a radiating channel. The radiating channel is provided with inlets and outlets. The inlets are located in the engine compartment and are close to the recirculation zone. The outlets are located at the tail of the body. The radiator further comprises a radiating fan arranged at the inlets. The radiator of the engine compartment of the automobile has a simple structure, through the radiating fan in the radiating channel, the hot air which is not easy to be exhausted in the engine compartment can be sucked out in time, thereby improving the radiating performance of the engine compartment; the hot air sucked out passes through the radiating channel and is exhausted from the outlets in the tail of the body, whichcan delay the separation phenomenon of the airflow at the tail of the body, thereby weakening the tailing vortex strength and size of the tail of the body, and further reducing the wind resistance ofthe vehicle.

The invention relates to the field of gas turbines and provides a compressor blade and a compressor. The compressor blade comprises a blade tip, a blade root and a blade middle which axially extends from the blade root to the blade tip; the cross section of each of the blade root, the blade middle and the blade tip is parallel to XY planes, X-direction represents the axial direction, Y-direction represents the tangential direction, and the Z-direction represents the radial direction; the tailing edge of the blade tip and the tailing edge of the blade root respectively twist toward the suctionside, the tailing edge of the blade middle twists toward the pressure side, and the trailing edges on the cross sections of the blade root, the blade middle and the blade tip are sequentially arrangedaround the leading edge point in the direction of the suction side. The leading edge of the entire compressor blade remains unchanged assuredly, and airflow separation of the blade root and the bladetip can be reduced by allowing the tailing edges of the blade tip and the blade root to twist along the suction side respectively and the tailing edge of the blade middle to twist along the pressureside.

The invention relates to a multi-axle aircraft, which belongs to the technical field of aircrafts. The multi-axle aircraft comprises an aircraft body, a left composite wing, a right composite wing, brackets, a front rotor and a rear rotor and a landing gear. An operating system and airborne equipment are mounted in the aircraft body. The left composite wing and the right composite wing have same structures and are symmetrically mounted on the left and right sides of the aircraft body. The front rotor and the rear rotor have same structures and are respectively mounted at the front and rear ends of the aircraft body through the brackets. The landing gear adopts a wheel type structure or a skid and wheel combined structure. The left composite wing and the right composite wing have same structures and symmetrically mounted on the left and right sides of the aircraft body. Two rows of rotors are mounted in the left composite wing and the right composite wing; and all rotors are driven by a motor. A wing of the left composite wing comprises a front wing and a rear wing, which both can deflect around a wing shaft. The multi-axle aircraft provided by the invention does not need a big landing site and can vertically take off and land. The multi-axle aircraft provided by the invention has the advantages of great lift force, safety, stability and flexibility.

The invention relates to a composite wing aircraft with a dihedral angle, which belongs to the technical field of aircrafts. The composite wing aircraft with the dihedral angle comprises an aircraft body, a left composite wing, a right composite wing, a tail wing and a landing gear. An operation system and airbore equipment are mounted in the aircraft body. The left composite wing and the right composite wing have same structures and are symmetrically mounted on the left side and the right side of the aircraft body. The tail wing comprises a horizontal tail wing and a vertical tail wing. The landing gear uses a wheel type structure or a skid and wheel combined structure. A dihedral wing exerts an effect of stabilizingthe aircraft. The left composite wing comprises a wing axle, a front wing sheet, a rear outer wing sheet, a rear inner wing sheet, a dihedral wing sheet, a rotor wing and an engine. The rear outer wing sheet and the rear inner wing sheet both can rotate and swing around the wing axle. The rotating plane of the rotor wing is in a horizontal position. During the rotation of the rotor wing, flow fields of the upper and lower surfaces of the wing sheets can be improved to increase downwash airflow and delay airflow separations on the upper surfaces of the wing sheets. The composite wing aircraft with the dihedral angle, provided by the invention, has the advantages of safety, high efficiency and high mobility.

The invention relates to a four-engine aircraft, which belongs to the technical field of aircrafts. The four-engine aircraft comprises an aircraft body, a left composite wing, a right composite wing, a tail wing and a landing gear. An operating system and airborne equipment are mounted in the aircraft body. The left composite wing and the right composite wing have same structures and are symmetrically mounted on the left and right sides of the aircraft body. The tail wing is positioned at the tail part of the aircraft body; and the tail wing comprises a horizontal tail wing and a vertical tail wing. The landing gear adopts a wheel type structure. The left composite wing comprises a front wing, a wing shaft, a rear outer wing, a rear inner wing, an outer rotor, an inner rotor, an outer engine and an inner engine. As four rotors are independently controlled and matched with four movable wings, the aircraft is flexible; and as all rotors are mounted under the wings, flow fields of the upper and lower surfaces of the wings can be improved during the rotating of the rotors; therefore, downwash airflow is increased, airflow separation of the upper surfaces of the wings is delayed, the efficiency is increased and the lift coefficient is greatly increased.

The invention relates to a composite-wing aircraft with a tail rotor, which belongs to the technical field of aircrafts. The composite-wing aircraft with the tail rotor comprises an aircraft body, a left composite wing, a right composite wing, a coaxial double-blade tail rotor and a landing gear. An operating system and airborne equipment are mounted in the aircraft body. The left composite wing and the right composite wing have same structures and are symmetrically mounted on the left and right sides of the aircraft body. The coaxial double-blade tail rotor comprises two electric propellers with same parameters and reverse rotation directions; and the two electric propellers are horizontally arranged with one under the other and independently controlled. The landing gear adopts a wheel type structure or a skid and wheel combined structure. The left composite wing comprises a wing shaft, a front wing, a rear outer wing, a rear inner wing, a rotor and an engine. The rear outer wing and the rear inner wing can both swing around the wing shaft. The rotating plane of the rotor is in a horizontal position. Flow fields of the upper and lower surfaces of the wing can be improved during the rotating of the rotor; therefore, downwash airflow is increased and airflow separation of the upper surface of the wing is delayed. The composite-wing aircraft with the tail rotor, provided by the invention, has the advantages of safety, high efficiency and good flexibility.

The invention provides wind deflector blades, cross-flow fan blades and an air conditioner. The blades (1) are used for the cross-flow fan blades, each blade (1) includes two ends oppositely arrangedin a first direction, and the first direction is the length direction of the cross-flow fan blades. The surfaces of the blades located between the two ends form alternately arranged concave portions and convex portions along with the width direction of the blades. Through the concave portions and the convex portions, the airflow distribution on the surface of the blades (1) can be changed, eddy current generation can be avoided, the noise caused by the airflow separation on the surfaces of the blades (1) and the interaction between the blades (1) and a casing can be reduced, thereby effectively improving the comfort of the air conditioner.