43results about How to "Avoid flow loss" patented technology

The invention provides a combustion chamber based on high-repetition-frequency laser and a scramjet engine. Stable flame is realized through a method of continuous breakdown of gas in supersonic-velocity gas currents through high-repetition-frequency laser pulse, so that the problems of flowing loss and heat protection caused by a mechanical flame stabilizer are effectively prevented.

The invention provides a gas introducing device before a gas turbine. The gas introducing device before the gas turbine comprises a volute and a bypass gas introducing slot part; the volute comprises junction surfaces and a gas introducing opening; the bypass gas introducing slot part is located at the upper part of a turbine flow passage section along an axial direction, is connected with the turbine flow passage section and is circumferentially connected with the junction surfaces of the volute; a part, within a connection position of the junction surfaces of the volute, of the outer peripheral face of the bypass gas introducing slot part and the volute together form a drainage flow passage circumferentially encircling the bypass gas introducing slot part; gas introducing slot openings which are arranged along a circumferential direction and penetrate through the bypass gas introducing slot part are formed in the part of the outer peripheral face of the bypass gas introducing slot part; the gas introducing slot openings, the drainage flow passage and an inner cavity of the turbine flow passage section communicate. According to the gas introducing device before the gas turbine, provided by the invention, gas discharged from an engine is evenly introduced into the volute, so that flow losses are avoided, power of the gas turbine is increased, an overall expansion ratio of a two-stage turbine is increased, and moreover, influence of gas introducing inlet pressure and gas introducing mixing on performance of the gas turbine and a power turbine is reduced.

The invention discloses a method used for annular-nozzle straight-line-arc-line blade profile line design of a radial-axial-flow-type turboexpander. The method includes: dividing a blade into two parts of a suction surface and a pressure surface, also dividing a blade profile line of each part into a straight-line segment and an arc-line segment, and utilizing mathematical expressions to carry outcoordinate solving on the straight-line segment and the arc-line segment through programming. According to the method, a Bezier curve is adopted for solving for arc-line segment coordinates to realize smooth transition of the straight-line segment and the arc-line segment, thus geometric curvature continuity of the nozzle blade profile line can be well guaranteed, and more flow losses can be avoided; and in addition, the blade profile line is divided into the straight-line segment and the arc-line segment through programming, the mathematical expressions are respectively used for representation, a design process is simpler, more convenient and faster, and subsequent work processes of machining manufacturing, numerical simulation, optimization design and the like on the nozzle blade profile line are facilitated.

The invention relates to a cylinder head for a self-igniting internal combustion engine, specifically, the cylinder head (10) has at least one exhaust channel (12) capable of being closed by an exhaust valve (30), and comprises a cooling air duct assembly having at least one cooling air duct (41, 42) for loading the cold air to the exhaust valve. The cooling air duct of the cooling air duct assembly in the cylinder head is configured to have approximately linear and / or approximately constant or continuously increased cross section.

The invention discloses a flexible casing treatment centrifugal compressor. The flexible casing treatment centrifugal compressor comprises a volute and an impeller, air outlet channels are formed in the two side ends in the volute, an air inlet is formed in the position, on an air inlet channel, of the front side surface of the volute, air outlets are formed in the positions, on the air outlet channels, of the two side ends in the volute, an impeller mounting cavity communicates with the air inlet channel and the air outlet channels, casing grooves are formed in the two side walls of the air inlet channel, partition boards are transversely and fixedly arranged in the casing grooves, flexible baffles are arranged on the side surfaces of the partition boards, and gaps are formed between theouter side ends of the flexible baffles and the bottom surfaces of the casing grooves. The compressor carries out operation on the basis of not changing an original centrifugal compressor volute casing treatment mechanism, the compressor is simple and convenient, flowing losses are avoided to a certain degree while the stable work range of the centrifugal compressor is further widened, and the reduction of the efficiency of the centrifugal compressor is effectively prevented.

The invention relates to an axial-flow type double-duct water-jet propeller, and belongs to the field of fluid mechanical engineering and ship propulsion. The invention aims to solve the problem that an existing axial flow type water-jet propeller is low in lift. The propeller is composed of a support, an outer duct transmission shaft, a water inlet runner, an outer duct impeller chamber, an outer duct guide vane chamber, a nozzle, an outer ducted impeller hub, outer ducted impeller blades, outer ducted guide vane blades, an inner ducted transmission shaft, an inner ducted impeller hub, an inner ducted guide vane hub, an inner ducted impeller chamber, an inner ducted guide vane chamber, inner ducted impeller blades, inner ducted guide vane blades and a flange plate. According to the axial-flow type double-duct water-jet propeller, on the premise that large flow is guaranteed, the lift of the water-jet propeller can be improved, the cavitation resistance is improved, the axial-flow type water-jet propeller can be applied to propelling of a high-speed navigation body, and meanwhile the defects that a multi-stage water-jet propeller is large in weight, large in space size and the like are overcome through the axial-flow type double-duct water-jet propeller.

A large engine with a charge air container (6) which can be operated by means of an exhaust gas turbocharger (1) and / or by means of at least one blower with a motor (9) The auxiliary blower (10) of the impeller (13) is supplied with charge air, which can be conditioned by means of a charge air cooler with a downstream droplet separator and with a Regulating housing (8) behind the device (1), which has at least one compartment (19) for a charge air cooler and at least one compartment (11) for a droplet separator, an auxiliary At least one blower chamber (12) of the blower (10) is connected to it on the inlet side, in such a large engine a very compact and vibration-resistant construction can be achieved in such a way that each blower chamber (12 ) and corresponding adjacent compartments (11) have at least one common wall (15) containing the inlet of the blower chamber (12).

The result of the invention is: to maintain low driving energy loss of the funnel spinning apparatus caused by flow resistance as much as possible and enabling approach a spinning site of the funnel spinning apparatus as simply as possible, especially for starting spinning, doffing or on the breakage of a yarn.

Systems for removing exhaust gas samples from internal combustion engines are know, said systems comprising: an exhaust gas duct (12) having fluid communication with an exhaust gas source (14) via an exhaust gas inlet (10); an air duct (20) into which ambient air can be suctioned via an air filter (28); a fusion zone (36) arranged downstream of an outflow cross section (18) of the exhaust gas duct (12); and a dilution tunnel (38), through which the exhaust gas / air mixture flows, wherein the outflow cross section (18) of the exhaust gas duct (12) is arranged substantially concentric in the air duct (20) and an annular orifice (34) is arranged downstream of the outflow cross section (18) of the exhaust gas duct (12) in the dilution tunnel (38). However, the two gas flows are often inadequately mixed. In order to ensure good mixing and representative sampling, the invention therefore proposes that means (32, 44, 50) are arranged upstream of the orifice (34) and downstream of the outflow cross section (18) of the exhaust gas channel (12), via which means the exhaust gas flow is deflected in such a manner that the exhaust gas flow is removed directly upstream of the means (32, 44, 50) and asymmetrically from the centre axis of the dilution tunnel (38).

The invention provides a method and device for determining an outlet metal angle of a guide vane blade. The method and device are used for power equipment with a gas turbine and a free turbine. The free turbine is provided with the guide vane blade. The method comprises the steps that the target power coefficient of the free turbine is determined based on a power matching relation of the gas turbine and the free turbine; and the outlet metal angle of the guide vane blade is determined based on the target power coefficient of the free turbine. Compared with a traditional scheme of adjusting a mounting angle, the internal flow loss of the free turbine can be prevented from being greatly improved, and therefore, efficient matching of the output power of the gas turbine and the output power of the free turbine can be achieved under the condition that the aerodynamic efficiency of the whole-stage turbine is kept.

The invention relates to a non-return valve, in particular for a refrigeration or heat circuit, which valve can be inserted into a connection opening (26, 27, 28, 29) of a connection device (21) or ofa pipe (39) and comprises: - a one-part or multi-part housing (42) which comprises at least one main housing (44), a feed opening (48) being provided on the inlet side and a discharge opening (51) being provided on the outlet side of the main housing (44), the feed opening and the discharge opening being interconnected by a flow channel (49); - a guide element (53) which is provided on the main housing (44) and by means of which a valve closing element (61) is guided slidably relative to the main housing (44), the valve closing element (61) being arranged in a starting position (42) by meansof an energy accumulator (71) and the valve closing element (61) being slidable toward the discharge opening (51) against an actuating force of the energy accumulator (71) in order to be transferred into a working position (63), and the energy accumulator (71) being provided between the valve closing element (75) and the main housing (44), the guide element (53) of the main housing (44) having atleast one through-hole (57) and at least one guide rod (59) being guided in said at least one through-hole (57), which rod at least extends from the valve closing element (61) through the at least onethrough-hole (57) and is secured against release from the through-hole (57), or the guide element (53) being designed as a sleeve (54) having a bottom (55), which is associated with the discharge opening (51), and the valve closing element (61) having a guide portion (66) which acts on the sleeve (54).

The invention discloses a high-performance two-way full cross flow turbine, which comprises an inlet pipe and a draft pipe connected in sequence, wherein a movable guide vane and a runner are sequentially arranged along a water flow direction on a central axis in the inlet pipe; the draft pipe comprises a first diffusion section, a second diffusion section, a third diffusion section and a fourth diffusion section, which are connected in sequence; a first deflector and a second deflector are connected along the circumference of the inner wall of the second diffusion section, and are equally spaced; the length of the first deflector is equal to that of the second diffusion section, and is greater than that of the second deflector; one end of the second deflector is located at the exit section of the second diffusion section. Unnecessary flow loss is avoided; the second deflector is away from the exit side of the runner, thus preventing from affecting stable operation caused by strong dynamic and static interference between the deflector and an impeller.

The present invention relates to one kind of air exchange device. In the space exhausting outdoor air or indoor air from the heat exchanger inside the casing, one flow stabilizer is set to change the flow of the outdoor air or indoor air from the heat exchanger into laminar flow so as to homogenize the flow of outdoor air or indoor air in the heat exchanger and to raise heat exchange efficiency.

A multi-way valve for controlling a fluid flow in a fluid circuit, such as a cooling fluid circuit of a motor vehicle, may include a valve housing having at least three fluid connections and a rotary slide for setting the fluid flow. The rotary slide includes at least two fluid channels and is configured to connect two respective fluid connections fluidly via one fluid channel dependent upon its rotary position in relation to its rotational axis. The at least three fluid connections and the at least two fluid channels overlap in relation to a crosswise direction oriented crosswise relative to the rotational axis.

The invention relates to a hydraulic spool valve comprising a valve housing (9) which comprises a valve bore (10) having two control chambers (25), which directly follow one after the other axially ata distance and extend beyond the diameter of the valve bore. The valve housing also has, in a connection surface, a pump connection opening (27), which is connected by means of a first fluid channel(26) to a first of the two control chambers, and a consumer connection opening, which is connected by means of a second fluid channel to a second of the two control chambers. The hydraulic spool valvealso comprises a control piston (12), which is guided so as to be moveable back and forth in the valve bore to fluidically connect the two control chambers with each other and separate said control chambers from each other. A radial web (55) of the valve housing projects into each control chamber, the extension of said web being delimited in the circumferential direction. To particularly effectively avoid annular flows in the control chambers and flow losses associated therewith, the second web in the second control chamber is longer in the circumferential direction than the first web in thefirst control chamber.

The invention provides a device for igniting detonation waves at low energies. The device comprises a pre-detonation chamber, a main detonation chamber and a piston spring actuation system. The pre-explosion chamber is composed of a cavity, an oxygen and explosive fuel injection device and a low-energy pulse igniter. Two drainage holes are formed in the wall face of the pre-explosion chamber. Themain detonation chamber surrounds the pre-detonation chamber, and two piston actuating holes are formed in the wall face of the main detonation chamber, corresponding to the positions of the drainageholes and having the same aperture; and the piston spring actuation system is arranged on the outside of the drainage holes and consists of a piston, a spring, a connecting post, a limit block and a protective sleeve, and the piston moves up and down in translation by clinging to the hole walls of the drainage holes and the piston actuation holes. According to the invention, the communication andisolation between the pre-detonation chamber and the main detonation chamber are controlled by adjusting the relative magnitude of the pressure difference between the inner and outer sides of the piston and the spring force. The detonation waves generated by low energy ignition of pure oxygen and explosive fuel in the pre-detonation chamber are transmitted into the main detonation chamber throughthe drainage holes which are opened after the piston moves upward, so as to initiate the detonation waves in the explosive mixture of the main detonation chamber.

The invention discloses a high-performance two-way full cross flow turbine, which comprises an inlet pipe and a draft pipe connected in sequence, wherein a movable guide vane and a runner are sequentially arranged along a water flow direction on a central axis in the inlet pipe; the draft pipe comprises a first diffusion section, a second diffusion section, a third diffusion section and a fourth diffusion section, which are connected in sequence; a first deflector and a second deflector are connected along the circumference of the inner wall of the second diffusion section, and are equally spaced; the length of the first deflector is equal to that of the second diffusion section, and is greater than that of the second deflector; one end of the second deflector is located at the exit section of the second diffusion section. Unnecessary flow loss is avoided; the second deflector is away from the exit side of the runner, thus preventing from affecting stable operation caused by strong dynamic and static interference between the deflector and an impeller.

A hybrid electric vehicle comprising an engine (2) together with a drive shaft (4) for driving wheels of at least one axle (7) and at least one electric motor (11, 12) for driving the vehicle A wheel of an axle or a wheel of at least one further axle (10), wherein the at least one electric machine can operate as a generator during braking and as a motor during acceleration, the hybrid vehicle also includes and A further electric machine (18) coupled to the at least one electric machine, comprising a flywheel accumulator with a rotor (14), which can be charged during braking and can be charged during acceleration is unloaded, wherein the rotor (14) can be mechanically coupled to the drive shaft (4) of the at least one axle (7) that can be driven by the engine via at least one switchable coupling device (23).

The invention provides a construction method of a gas compressor / turbine transition runner with a support plate. The construction method includes the steps: determining inlet and outlet arcs of the transition runner expansion surface profile according to the runner inlet and outlet states, and finding out an inscribed line of a circle where the two arcs are located to serve as a straight line section of the expansion surface profile, wherein the inlet and outlet arcs and the middle straight line section jointly form the expansion surface profile of the runner; giving normal height distributionof the runner through the height of an inlet and an outlet, then solving coordinates of corresponding points on a shrinkage surface profile till convergence is achieved, and obtaining an initial shrinkage surface profile of the runner; and finally, considering the blocking effect of the support plate, calculating the blocking area of the support plate, increasing the height of the runner to compensate the blocking of the support plate, and obtaining the corrected runner shrinkage surface line. The gas compressor / turbine transition runner with the support plate solves the problems that a construction method in the prior art is poor in practicability and not suitable for a sudden expansion type runner with an overlarge expansion angle.