CN117869331A - Linear speed compressor and high-pressure self-priming pump - Google Patents

Abstract

The invention discloses a general fluid mechanical scheme for a pump and a compressor, wherein fluid circumferentially enters and exits an impeller and a cavity thereof, the impeller is a large-inclination-angle blade closed hollow wheel, and the impeller is matched with a special runner, so that jet expansion, channel separation, backflow and ejection can all perform circumferential directional movement, multistage linear velocity pressurization is realized, and meanwhile, the expansion performance of a space in all directions is improved. The space expansibility of the invention has the advantages that the axial size is increased, the flow can be increased without affecting the efficiency, the number of the chambers or the linear speed is increased in the circumferential direction, the outlet pressure and the compression ratio can be directly improved, the edge of the impeller is an effective action part, the impeller can be hollow, and a motor or other power components can be directly filled, so that the dynamic seal is changed into the static seal, and the leakage is prevented. The impeller is the only moving part, has simple and firm structure and does not need tuning, so that the compressor or the pump can run at high speed, the whole range can obtain higher efficiency, and the impeller is suitable for microminiaturization and giant, and has great freedom and convenience in installation and use.

Description

Linear speed compressor and high-pressure self-priming pump

Technical Field

The invention belongs to the field of fluid machinery, and particularly relates to a speed impeller pump or a compressor, which mainly comprises a closed impeller and a cavity with a special structure.

Background

Impellers are common mechanical structures of pumps and compressors, and utilize high-speed motion to exchange energy with fluid, and the effective kinetic energy directions are usually from axial directions and radial directions, respectively representing an axial flow pump and a centrifugal pump, or two-direction mixing, such as a mixed flow pump and the like. The speed type machinery has the advantages of large flow, high rotating speed, continuity and stability, high efficiency and excellent comprehensive performance, and brings great convenience to industrial production and living.

However, it is easy to find that these machines have a large axial space, and it is necessary to install a fluid inlet or a transmission bearing, etc., and it is also necessary to save the radial dimensions, and the reduction of the power dimensions will not only lose the output pressure, but also the self-absorption capacity. The impellers or turbines generally can only realize compact structure in a single-dimensional direction, the space structure is limited, the miniaturization is not facilitated, the maximization is not facilitated, the notebook computer can not be plugged into the heat radiator, the multi-stage rotating structure can not be combined into a one-stage high-power structure, and the final stage is converged. In addition, the great degree of mechanical efficiency is ensured by blade profile adjustment, blades can be adjusted at any time in many high-power devices, the microstructure becomes extremely complex, and the fluid machinery is not simple, reliable and compact any more.

Disclosure of Invention

The invention discloses a general fluid mechanical scheme for a pump and a compressor, which comprehensively utilizes a hollow closed impeller to be matched with a special runner, realizes expansion, deceleration pressurization and jet adsorption, realizes fluid circumferential multistage linear velocity pressurization, and can improve the expansion performance of a space in all directions. The specific idea is to utilize the expansion and pressurization of the jet flow between the blades to try to bypass the closest point of the cavity wall impeller and the subsequent jet flow, and directly gush to the next stage. Briefly, the first interblade jet of each stage continues to expand forward, with subsequent interblade jets being shielded, blocked, and reflowed.

The impeller is a column body with blades embedded on a hub and sealed at two axial ends and similar to a side etched deep groove as a whole. The structure aims to solve the problem of different flow conditions among leaves and reduce mutual interference. When the jet flow between the first blades is centrifugally thrown out and enters the diffusion channel, the blades continue to move, a low-pressure area is formed between the second blades, the need of adsorption backflow exists, the pressurized jet flow can be partially supplemented by backflow, and then the jet flow can be split into cavities at the tail end of the expansion area of the jet flow between the first blades, so that the diffusion area is continuously enlarged, and a passageway is built for backflow. In general, full-speed omnidirectional flow of the first inter-leaf jet is ensured, the second inter-leaf jet is blocked, and the third inter-leaf backflow is left to supplement. Through measurement and experiment, the chamber structure of the first stage is better than 3.5 times of the impeller spacing, namely, the inter-blade opening angle can be recorded as a basic measurement unit of the invention, and represents the area occupied by the radial extension space angle of the invention.

The blade is inclined at a large angle, so that the inter-blade jet is ejected to be close to the tangent line of the impeller as much as possible, the first inter-blade jet straight-through expansion area can be enlarged to 1.5 units, then the chamber is divided at the position, and the outlet is increased. Whichever outlet chamber region expands, the proximal region is impacted by the second inter-leaf jet, creating a recirculation region, while the laminar flow in the distal region continues along the chamber wall toward the next stage chamber. The divided chambers preferably no longer meet, but the third vane is the closest point of the impeller and the chamber wall at about the 2.5 unit, and the backflow and spitting of the vane tips form turbulence to form periodic oscillating pressure, so that the turbulence is helped to be diverted in time and the backflow is helped. Therefore, each stage of chamber should have a diffusion chamber, two diversion chambers and sealing plugs for dividing the chamber, namely three diversion columns: the expansion plate is positioned at the 1 st unit, the flow dividing plate is positioned between the second blades and the third blades, the tail plug occupies the last 1 unit of the chamber, and the expansion plate plugs the upper and lower chambers and forms an interlobe adsorption chamber with the third blades.

Fig. 1 is a schematic diagram of a certain stage structure principle of the scheme of the invention, and arrows with lines in the dot-matrix coils represent streamline and direction. In order to draw the drawings, the forward tilting impeller is conveniently adopted, and the backward tilting impeller can be used in actual use, as follows.

In fig. 1, the 3.5 unit ear chamber at the outer edge of the impeller is called a wing cavity, not only because the shaft section is shaped like a wing of a skeleton skin, but also because a cavity type design like an airfoil is needed. The bending cavity wall is obtuse, the bending position is at about 1.5 units, two sides are approximately parallel to the tangential plane of the impeller, the inner wall surface of the bending cavity is called as the outer wing surface of the wing cavity, and the inner wing surface is the outer edge surface of the impeller. In the figure, three flow dividing columns are arranged, the widths of the pressure expansion plate and the flow dividing plate are equal to the thickness of the blade, the tail plug is wedge-shaped, and the front tip and the rear tip are wide. The diffuser plate is a natural extension of the forward leaning vane at unit 1, extending from the inner airfoil surface to about half the width of the airfoil cavity, and circumferentially occupying about 0.5 units, i.e., the first inter-vane straight diffuser cavity to about 1.5 units. The splitter plate is disposed between the distal end of the diffuser plate and the outer airfoil surface to substantially divide the obtuse angle formed by the splitter plate and the outer airfoil surface to a length of no more than 1 unit of circumferential projection. And a backflow cavity is formed between the proximal shaft edge of the flow distribution plate and the expansion plate and between the flow distribution plate and the impeller, and a diffusion channel is formed between the distal shaft edge of the flow distribution plate and the cavity wall. The tail plug occupies 1 more units at the tail of the wing cavity, the wedge tip is at about 2.5 units, the tail section is at 3.5 units, the paraxial surface has radian, the paraxial surface abuts against the inner wing surface, and a flow passage is arranged between the paraxial surface and the outer wing surface of the wing cavity. The outlet of the flow channel is a nozzle, and although the fluid contacting the wall of the cavity is greatly decelerated due to collision and friction, the flow channel opening is provided with a high-speed fluid directly injected into the cavity by the first blade, the internal pressure is small, an adsorption effect is formed on the flow channel, and meanwhile, the liquid in the flow channel can be pushed by convection extrusion in the middle of the wing cavity with the maximum pressure. The tail section of the natural tail plug passes through the front inclined line of the starting position of the first blade, and the edge angle of the cut tail plug flow passage opening is an acute angle and forms an acute angle with the edge fold of the outer wing surface.

All the wing cavities are connected end to end, the tail section of one wing cavity is the initial surface of the next wing cavity, the bent cavity walls are connected end to end in sequence, and the flow channel of the previous wing cavity is aligned with the bending of the next wing cavity. It is noted that the body shell to which the wing cavities are connected is shaped like a regular polyhedron, but obviously, it is not the only thing that the side equal structure is spliced in sequence around the axis, and the side central line is not perpendicular to the side. The suction inlet of the machine body is arranged before the tip of the first tail plug, the outlet of the machine body is arranged after the section of the last tail plug, and at least 1 unit of interval is arranged between the inlet and the outlet. The axial direction of the wing cavity structure and the axial direction of the blade must be kept straight or have the same inclination angle synchronously, the length is equal, and both ends must be closed. The size of each wing cavity is limited by basic units, but the number of the wing cavities can be configured as required, and the positions of the non-machine body inlet and outlet and the wing cavities on the wall of the impeller cavity are filled physically so as to ensure the tightness of the impeller cavity. In turn, the impeller is also constrained, i.e. at least 15 blades, and uniformly distributed circumferentially, since a circumferential four-chamber is not possible and the kinetic energy of the inter-blade jet will be lost completely, at least according to a 5-chamber design, the impeller is matched, the chambers are not all packed, leaving some additional structural space.

Fig. 2 is a schematic view of a local planing structure of the impeller, namely, a deep groove is formed on the side surface of a cylinder, and the impeller can be hollow. The reason why the impeller adopts the blades with large inclination angles is that the angle of the jet flow between the blades to strike the cavity wall is reduced, and the loss of too much energy is avoided.

FIG. 3 is a schematic cross-sectional view of a multi-chamber cascade shaft according to the present invention, wherein the outlet is designed to prevent reverse flow. Obviously, the number of chambers may increase as the number of vanes increases.

Obviously, the topological form of the wing cavity structure has huge relation to the energy efficiency and the flow of the engine body, the structural parameters and the shape position should be designed according to the optimization of specific environments, the edge treatment of different parts is different, and the relation with the constraint of the impeller can be slightly adjusted. The invention can increase the outlet pressure or compression ratio by increasing the number of the wing cavities and the linear speed of the impeller continuously, but the too many wing cavities can cause the cavity walls to be more and more parallel to the peripheral line of the impeller, and the included angle between the cavity walls and the inclination angle of the blades becomes larger, so that one angle edge of the wing cavity can be selected to be bent once in a small margin. Too many wing cavities can also bring the problem of too short flow channel, weakens the pressure isolation between the cavities, and needs the linkage optimization of the impeller and the cavities at the moment, such as enlarging the inclination angle of the blade, widening the wing cavities, optimizing the lengths and angles of the expansion plate and the flow distribution plate, prolonging the flow channel, adjusting the angle of the nozzle and the like. The wing cavity design can take the forward tilting impeller as a reference, and the backward tilting impeller is actually used, so that the positions of the pressure expansion plate and the flow distribution plate can be rapidly determined. In addition, the flow rate can be increased by increasing the axial dimensions of the impeller and the vane cavity, which is irrelevant to energy efficiency and does not cause any additional problems.

According to the scheme, fluid enters and exits the impeller from the edge of the impeller, is pressurized and flows in the wing cavity in a tangential mode, is basically kept to be basically parallel to the peripheral line of the impeller, can improve the body capacity by continuously increasing the cavity, and is excellent in circumferential linear expansion. In fact, one vane cavity is one-stage supercharging, the scheme of the invention is obviously circumferential multistage linear speed supercharging, so the vane cavity is a linear speed compressor, and the natural property is that the discharge pressure and the compression ratio can be increased by increasing the linear speed. The self-priming pump has good self-priming capability, so the self-priming pump is a linear speed high-pressure self-priming pump.

The axial expansibility of the invention is more excellent, and besides the increase of the axial size can increase the flow, more importantly, the machine body can be hollow, and the impeller can be hollow. The middle of the impeller can be provided with a rotating shaft to install a motor part or other power structures, so that the dynamic seal is changed into the static seal, and fluid leakage is avoided. Because the moving part of the scheme of the invention is only a rotary impeller, the impeller is still closed, the strength of the impeller is high, and the static sealing machine can obtain a long maintenance period. The axial through holes can be drilled in the shell and the tail plug to circulate cooling liquid. The heat dissipation device is extremely suitable for high-speed high-pressure working conditions, and greatly enhances heat dissipation performance. Layered intervals can be added in the sections of the impeller and the wing cavity shaft to help heat conduction and increase structural strength, and the axial expansion without acting has no influence on the machine body efficiency.

The invention has the advantages of excellent space expansibility, strong axial and circumferential expansibility and low radial requirements, so that the invention can bring great freedom and convenience for installation and use. For example, an ultrathin compressor can be obtained and plugged into a notebook computer to serve as a radiator, and hot air or cooling liquid is discharged in a specific direction; a high-pressure self-priming pump can be obtained, pipelines can be connected to two ends of the high-pressure self-priming pump, and the lift and the safe operation distance are increased; the multi-stage compressor can be obtained, and enough blades and enough wing cavities can output enough high pressure, so that the space is saved, the maintenance complexity is not increased, the multi-stage compressor can be used in giant industrial machines, particularly in the field of energy conversion, the multi-stage compressor can be used for storing water and storing energy and storing compressed air, and unstable energy is changed into stable and controllable energy. Other alternative industrial applications are not listed.

FIG. 3 shows a prototype of the inventor, wherein a prototype with the diameter of about 80mm, the impeller height of 40mm, the linear speed pump chamber width of about 6.5mm, the vane groove depth of about 11mm, the hollow hole diameter of the middle part of the impeller of 40mm, the 5-stage chamber, 22 vanes and 2mm flow channels are printed on resin, and the flow pump can pump 96ml/s of water flow by 5cm far by adopting a 370 micro motor with the diameter of 12V. This has exceeded most small micro compressors.

Finally, it should be pointed out that when the solution of the invention works, all the blades move from the outlet to the inlet and vice versa, the fluid always has two circulation paths between the inlet and the outlet, but one circuit function is amplified, and in extreme conditions, the other circuit side effect is also increased. For example, the solution of the present invention makes it impossible to directly obtain a high vacuum, and the efficiency inevitably decreases when the rotation speed is increased at a certain high speed, although the capacity is still improved. In particular, the blockage of the discharge port, not only reduces the efficiency, but also reduces the suction capacity, since the fluid can return from the outlet to the inlet, which can cause a vicious circle. Therefore, the scheme of the invention can be properly modified, the inlet and outlet circulating passages are directly built outside the impeller cavity, the impeller cavity is filled with working medium to extract other fluid, and high vacuum degree can be obtained, which is based on the fact that the working medium and the pumped substance are easy to separate. As for blocking or backflow prevention, a Tesla valve or other one-way valves can be additionally arranged at the outlet besides the design that the inlet and the outlet of the machine body are far enough apart and the outlet is backflow-preventing.

Claims (7)

1. The invention discloses a novel fluid mechanical structural design scheme for a pump or a compressor, which mainly comprises a closed impeller and an ear chamber structure on the chamber wall of the closed impeller: the impeller is a cylinder with radial large-inclination blades embedded on the hub, two ends are closed, and the whole impeller is a side etched deep groove; the blades can be tilted forwards or backwards but the inclination angle is not required to be zero, the number of the blades is at least 15, the blades are uniformly distributed in the circumferential direction, namely, the opening angles among the blades are equal and not more than 24 degrees, and the space size is recorded as a basic measurement unit of the invention; the ear chamber structure on the impeller chamber wall comprises a shell bending chamber wall and three flow guide columns, wherein the peripheral direction occupies 3.5 units of the impeller chamber wall, and the shaft section is similar to a wing of a framework skin, so the ear chamber structure can be called as a wing chamber; the bending cavity wall is an obtuse angle, the bending position is at about 1.5 units, two sides of the bending position are approximately parallel to the tangential plane of the impeller, the inner wall surface of the bending cavity is called as the outer wing surface of the wing cavity, and the inner wing surface is the outer edge surface of the impeller; the three flow guide columns in the wing cavity are respectively called a pressure expansion plate, a flow distribution plate and a tail plug, the widths of the pressure expansion plate and the flow distribution plate are equal to the thickness of the blade, the tail plug is wedge-shaped, and the front tip and the rear tip are wide; the expansion plate is a natural extension of the forward inclined blade at the 1 st unit, extends from the inner airfoil surface to about half of the width of the airfoil cavity, and occupies about 0.5 unit in the circumferential direction; the splitter plate is arranged between the far shaft end of the diffusion plate and the outer airfoil surface, and is used for dividing an obtuse angle formed by the splitter plate and the outer airfoil surface in a general way, and the length of the splitter plate is not more than 1 unit of circumferential projection; the tail plug occupies 1 more units at the tail part of the wing cavity, the wedge tip is at about 2.5 units, the tail section is at 3.5 units, the paraxial surface has radian, the paraxial surface abuts against the inner airfoil surface, a flow passage is arranged between the distal axial surface and the outer airfoil surface of the wing cavity, and the flow passage is approximately parallel to the impeller tangential surface; the tail section of the tail plug is an axial stretching surface of a vane rake angle extension line, an acute angle is formed between the tail section of the tail plug and the edge of the outer wing surface, and the edge angle of the cut tail plug flow passage opening is an acute angle; all the wing cavities are connected end to end, the tail section of one wing cavity is the initial surface of the next wing cavity, the bending cavity walls are connected end to end in sequence, and the flow channel of the previous wing cavity is aligned with the bending of the next wing cavity; the suction inlet of the machine body is arranged before the tip of the first tail plug, the outlet of the machine body is arranged after the section of the last tail plug, and at least 1 unit of interval is arranged between the inlet and the outlet; the axial direction of the wing cavity structure and the axial direction of the blade must be kept straight or have the same inclination angle synchronously, the length is equal, and both ends must be closed.

2. According to the scheme of the invention, the bent cavity wall of the wing cavity is bent outwards at a straight edge and an obtuse angle, and can be bent inwards once only by selecting a corner edge if necessary; edge treatments of different parts of the wing cavity are different, structural parameters and shape positions are designed optimally according to specific environments, and the constraint relation between the structural parameters and the shape positions and the impeller can be slightly adjusted; the design of the wing cavity can take the forward tilting impeller as a reference, and the backward tilting impeller is actually used; the positions of the non-machine body inlet and outlet and the wing cavity on the impeller cavity wall are filled with solids so as to ensure the tightness of the impeller cavity.

3. According to the solution of the invention according to claims 1 and 2, the flow can be increased by increasing the axial dimensions of the impeller and the wing cavities, and the outlet pressure or compression ratio can be increased by increasing the number of wing cavities and the linear speed of the impeller.

4. According to the solutions of the invention described in claims 1, 2 and 3, the machine body or the impeller can be hollow, and the center of the impeller can be directly provided with a rotating shaft, and also can be provided with a motor part or other power structures.

5. According to the scheme of the invention, as shown in claims 1, 2, 3 and 4, the inlet and outlet circulating passages can be directly built outside the impeller cavity, so that the impeller cavity is filled with working medium to extract other fluid.

6. According to the invention, axial through holes can be drilled in the shell and the guide posts to circulate cooling liquid, and layered intervals can be added in the axial sections of the impeller and the vane cavities to help heat conduction and increase structural strength.

7. According to the scheme of the invention, as shown in claims 1, 2, 3, 4, 5 and 6, in the high-speed and high-pressure working condition, the distance between fluid inlets and outlets is increased, the outlet adopts a flow-preventing design, and a Tesla valve or other one-way valves are added to prevent blockage.