159results about How to "Reduce impact loss" patented technology

A single stage high pressure turbine vane includes an airfoil having a profile substantially in accordance with at least an intermediate portion of the Cartesian coordinate values of X, Y and Z set forth in Table 2. The X and Y values are distances, which when smoothly connected by an appropriate continuing curve, define airfoil profile sections at each distance Z. The profile sections at each distance Z are joined smoothly to one another to form a complete airfoil shape.

The invention discloses a pressure expander of a centrifugal compressor. The structure of the pressure expander is improved, and high application value is achieved for further improving working performance of the pressure expander. A short blade is arranged in runners of every two adjacent long blades; the front edges of the long blades are curved surfaces and are arranged obliquely, and the included angles between front edge lines and the central axis of a wheel disc are 6 degrees to 8 degrees; the radius of curvature of the front edges of the long blades is gradually increased from the wheel disc to a wheel cover; each long blade is provided with three broken-line-shaped channels penetrating through a corresponding pressure surface and a corresponding suction surface; tail edge wing tips are arranged on the portions, located on the pressure surfaces, of the rear edges of the long blades. Occurrence of separation of airflow on the surfaces of the blades is restrained through the short blades in the runners of the adjacent long blades; the pressure differences between the pressure surfaces and the suction surfaces are reduced through the broken-line-shaped channels, the adverse pressure gradient is reduced, and separate airflow on boundary layers of the suction surfaces at the tails of part of the blades is effectively blown away; increase of wing tip vortexes generated by the pressure differences between the suction surfaces and the pressure surfaces on the rear edges of traditional wing-type blades can be restrained through parabola-shaped winglets on the tail edges.

The invention discloses an axial flow wind wheel with improved blades, which comprises a wheel hub and a blade, and the blade and the wheel hub are formed as a whole. The invention is characterized in that the external circumferential part of the blade is bent from a windward side to a leeward side, and the bent width is gradually decreased from a front edge to a tailing edge; by adopting the structure, the leakage vortex at the external circumferential front edge and the air stream disturbance at the apex of the blade can be controlled. When the axial flow wind wheel rotates, the leeward side at the front edge of the blade has lower pressure, so as to cause large pressure difference between the windward side and the leeward side at the front edge of the blade, and turns up the apex of the blade towards the windward side, thus the pressure difference at the two sides of the apex of a blade can be reduced, and the leakage vortex at the external circumference of the blade can be inhibited. The angle that the air stream enters the front edge of the blade is greatly changed from the wheel hub to the external circumference, which can effectively reduce air-inlet impact loss, achieve the purpose of promoting the efficiency of the wind wheel; and meanwhile, when an impeller rotates, as the angle of attach of the air current i is smaller, the cutting air stream without impact at the front edge of the blade can generate lower pressure disturbance, thus playing an obvious role in reducing noise.

The invention discloses a 1/2 type tandem-blade type transonic speed centrifugal impeller, which comprises an inducer consisting of a front row of blades and a guide wheel consisting of a back row of blades, wherein the front and the back rows of the blades have three-dimensional distorted shapes and are divided, staggered and overlapped with one another. The centrifugal impeller is characterized in that the number ratio of the front row of the blades to the back row of the blades is 1:2. In the centrifugal impeller, the front row of the blades are arranged with low consistency and the back row of the blades are arranged with high consistency so that the effective through-flow area is enlarged and the blockage flow is increased; and the evenness of the flow at the outlet of the impeller is improved so that the wake losses and the shock losses between the impeller and a diffuser are reduced, the efficiency of the whole stage is improved, and the surge margin is enlarged.

The invention discloses an impeller structure of a rotary shell type pump, which comprises impeller blades positioned between a front cover plate and a back cover plate. The adjoining impeller blades are formed into impeller flow passageways. The impeller structure is characterized in that each impeller flow passageway consists of an impeller inlet flow passageway and an impeller outlet flow passageway; each impeller inlet flow passageway is an arc flow passageway, wherein the length of the arc flow passageway is 60-70% of that of the impeller flow passageway, and an inclined angle beta1 arranged between the midline of each impeller inlet flow passageway and an inlet distribution circle is from 20 to 40 degrees; and each impeller outlet flow passageway is provided with two outlet radial branch flow passageways. The impeller flow passageways of the impeller structure effectively restrains the generation of axial whirlpool and flow separation; a smaller inlet angle can lead the impact loss of the inlet to be reduced; the branch of the outlet flow passageway leads the liquid which flows into a shell to be more even; and the milling machine of the flow passageways can obtain small surface roughness to achieve the aim for improving the waterpower efficiency of the impeller.

The invention discloses a centrifugal impeller geometry optimization designing method which is capable of improving pump efficiency. The method includes establishing a optimizing model of the centrifugal impeller geometry with efficiency iterations, calculating volumetric efficiency eta v and mechanical efficiency eta m of a pump at a design point, and performing efficiency iterations during the process of impeller geometry optimization. The beta 2, namely the sum of two losses of the impeller to allow h to be minimum, and a corresponding R2 are the final solution of the design. The centrifugal impeller geometry optimization designing method is capable of improving efficiency of the centrifugal pump, performances of the pump are improved in a wider range, and minimum sum of impeller outlet impact loss and friction loss of the impeller disc can be acquired by calculating the efficiency iterations of the centrifugal impeller geometry; computer software program can be written to implement accurate calculation of the centrifugal impeller geometry, design is facilitated, speed is high, design and produce accuracy of the centrifugal impeller can be improved effectively, and the method is adaptable to industrial design and production.

The invention provides a low-denseness blade diffuser and a production method thereof. The low-denseness blade diffuser is arranged between an outlet of vane wheels and an inlet of volutes of a compressor, and comprises a non-blade inlet section, a low-denseness blade section and a non-blade outlet section. The inlet of the non-blade entrance section is communicated with the outlet of the vane wheels, blades are arranged inside the low-denseness blade section, and the inlet of the low-denseness blade section is communicated with the outlet of the non-blade inlet section, the inlet of the non-blade outlet section is communicated with the outlet of the low-denseness blade section and the outlet of the same is communicated with the inlet of the volutes. The low-denseness blade diffuser has the advantages that diffusion degree of the diffuser is improved, wasted works of the compressor is reduced and efficiency is improved by adopting the low-denseness blade; and the non-blade sections are addedly arranged on the front and back of the blade section to overcome defects of regular poor adaptability of variable working conditions of the blade diffuser, impact losses under variable working conditions are reduced, and working ranges of the compressor are widened.

[Problem] To provide a radial turbine rotor blade whereby, even if a variable nozzle mechanism in a variable-geometry turbocharger is closed down, resulting in a flow field with a low turbine velocity ratio (U/C0), inflowing-gas impact losses at the leading edge of the rotor blade are reduced, improving turbine efficiency. [Solution] This radial turbine rotor blade is characterized in that: with respect to the direction of rotation (R) of the rotor blade (50), the hub-side corner (Pa) of the leading edge (51) of the rotor blade (50) is behind the shroud-side corner (Sc) of said leading edge (51); and in a radial view of the rotor blade (50), a line that connects the aforementioned shroud-side corner (Sc) to the hub-side corner (Pa) forms a 30-70° angle with a line that extends in the direction of the axis of rotation from the shroud-side corner (Sc) of the leading edge (51) to the surface of the hub (17).

A hydrodynamic tool for the cleaning of pipes and channels exhibits a pressurized water-entry inlet opening (2) connected to pressurized water-discharge outlet openings (4) through water guide channels (3). The water guide channels (3) are continuously connected to the pressurized water-entry inlet opening (2) with a hose connection (2a). The water guide channels (3) exhibit a largest possible deflection radius (r) and partially converge into one another. At least two water guide channels (3) rest with the innermost point of the diameter (dW1) at the center point (M) and with their outermost point of the diameter (dW1) at the outer diameter (dE) of the pressurized water-entry inlet opening (2). The water guide channels (3), corresponding to the arrangement of the pressurized water-discharge outlet openings (4), are either merging into the end of the deflection radius (r) or into the straight line region (3.G) and in an angle ( alpha ) to the respective pressurized water-discharge outlet openings (4).

The invention relates to a centrifugal blower volute of a range hood. A molded line of the volute (1) consists of a first curve AB, a second curve BC, a log spiral CD and a straight line DE which are in smooth transition connection with each other, and the first curve AB and the second curve BC which form a volute tongue are front edge parts of a wing profile molded line, wherein the first curve AB is the front edge part of a wing profile upper airfoil molded line BAF, the second curve BC is the front edge part of a wing profile lower airfoil molded line BCF, and the upper airfoil molded line BAF and the lower airfoil molded line BCF form the wing profile molded line. The centrifugal blower volute uses the wing profile front edge parts with good streamline forms as the molded lines of the centrifugal blower volute tongue. The volute adopting the wing profile volute tongue can greatly reduce the probability of generating flow separations and back flows at the volute tongue and reduce impact losses, and is favorable for improving the wind quantity, the wind pressure and the efficiency of a centrifugal blower and reducing aerodynamic noises.

The invention discloses a volute type centrifugal pump with a movable guide vane. According to the volute type centrifugal pump with the movable guide vane, a rectifying grid is arranged at an outletof a suction elbow pipe, so that the energy loss of fluid at an inlet of a flow channel is reduced, the cavitation performance is improved, and vibration and noise are reduced. The movable guide vanestructure of the volute type centrifugal pump with the movable guide vane is arranged between an impeller outlet and a volute inlet, the angle of the guide vane can be adjusted according to differentworking conditions, and the flow at the impeller outlet can be rectified under different working conditions, so that the influence of unbalanced force is reduced, and the operation stability of a large unit is improved. Moreover, the structure is beneficial to reducing the impact loss caused by the fact that the water flow impacts the guide vane when the liquid flow at the impeller outlet enters the guide vane, so that the efficiency of the large centrifugal pump is improved.

A centrifugal turbomachinery in accordance with the present invention can lower a fluid loss in a return flow path. In the centrifugal turbomachinery, a plurality of centrifugal impellers is attached to a rotating shaft, and the centrifugal turbomachinery is provided with a diffuser having a plurality of blades introducing a fluid boosted by a front stage impeller to a rear stage impeller, and a return flow path means. The return flow path means has a side plate arranged in a back surface side of the front stage impeller, a plate opposing the side plate and arranged in a front surface side of the rear stage impeller, and a plurality of blades arranged between the side plate and the plate so as to be spaced in a peripheral direction. A maximum diameter portion of the side plate is changed in the peripheral direction.

The invention discloses a two-channel variable-section volute device with flow-guiding blades, which comprises a volute. A volute air inlet, a volute air outlet, a volute air inlet flow channel and a volute diffusing channel are arranged in the volute, a pneumatic partition plate is arranged in the volute air inlet flow channel and divides the volute air inlet flow channel into a volute air inlet inner flow channel and a volute air inlet outer flow channel, the volute air inlet outer flow channel is located on the outer side of the circumference of the volute air inlet inner flow channel, and the position of the volute air inlet outer flow channel and the position of the volute air inlet inner flow channel which are close to the volute diffusing channel are respectively provided with a no-blade nozzle. A plurality of wing-shaped pneumatic flow-guiding blades are annularly evenly arranged at the position inside the volute air inlet outer flow channel close to the no-blade nozzle. For a pulse pressurizing system, the inner flow channel works at an engine low-speed area, and the pulse energy can be utilized better. When at a high speed, the outer flow channel does not need to be divided into two flow channels, enough energy can be obtained through one flow channel, a product structure is further simplified, and the product weight is reduced.

The invention discloses a centripetal impeller for a gas turbine engine, which comprises an impeller disk (1) and blades (2). The blades (2) are arranged on the surface of the impeller disk (1), and extend to a rim (3) outside the impeller disk (1); the impeller disk (1) at the backs of the blades (2) is provided with a pocket (4); at least two circular arc surfaces are formed in the pocket (4). The pocket is processed at the position at the back of the impeller to reduce a centrifugal load borne by an impeller center so as to reduce stress. Due to the structural characteristics of the centripetal impeller, the pocket cannot be excessively deep dug and the fillet radius also cannot be excessively large; the adoption of a multi-section circular arc structure of the pocket can effectively solve the problem of limitation of the fillet radius; aiming at the pocket, the multi-section circular arc structure is adopted, a large circular arc radius is adopted in a region with a large stress and a small circular arc radius is adopted in a region with a small stress. According to the novel structure, the stress can be greatly reduced in a small space range and service life is prolonged.

The invention relates to a high-flow cross-draining water-sealing floor drain, belongs to the technical field of floor drains and provides a cross-draining floor drain small in size, high in flow capacity and compatible with washing machine drainage; according to the technical scheme, a floor drain body is a container with a top opening, a water-sealing cover is in the shape of a ring having the inner cylindrical face extended down to form a barrel, the water-sealing cover is arranged inside the floor drain body, the bottom of the barrel hangs in the air, the ring of the upper portion of the water-sealing cover adapts to the upper portion of the floor drain body in shape and is locked to the upper portion of the floor drain body, a water seal is formed between the water-sealing cover and the floor drain body, a frame is mounted above the water-sealing cover and the floor drain body, and a grate is mounted in the frame; the outer side of the floor drain body is connected with a water outgoing pipe, the water outgoing pipe includes a square tube segment, a transition segment and a circular tube segment, the square tube segment is connected to the outer wall of the floor drain body, and the upper portion of the sidewall of the floor drain body inside the square tube segment is provided with a horizontal water outlet; the high-flow cross-draining water-sealing floor drain is suitable for cross-draining pipelines.

The invention relates to the technical field of water pumps, in particular to a fixed guide vane body inlet angle adjustable axial flow pump which comprises an impeller chamber (9), a water inlet horn mouth (8), an impeller body (10), a guide vane body (1) and a pump shaft (2). The guide vane body (1) comprises a plurality of guide vanes (3) and a dispersing pipe. The axial flow pump further comprises an adjusting system which comprises a control unit, a middle unit and an executing unit. According to different working conditions, a proper guide vane inlet angle is adjusted, so that the guide vane inlet angle is matched with an impeller flow-out angle, the circular rector of the fixed guide vane body is changed, accordingly, stress is improved, then, hydraulic loss such as impact and streaming around is lowered, energy loss is lowered, the operation stability of the pump is improved, and finally the purpose of axial flow pump performance improving is achieved.