CN113882904A

CN113882904A - Unsteady surface layer flow channel composite blade type turbine

Info

Publication number: CN113882904A
Application number: CN202111244977.4A
Authority: CN
Inventors: 范家铭
Original assignee: Individual
Current assignee: Individual
Priority date: 2021-10-26
Filing date: 2021-10-26
Publication date: 2022-01-04
Anticipated expiration: 2041-10-26
Also published as: CN113882904B

Abstract

The invention belongs to the technical field of turbine equipment, and provides an unsteady surface layer flow channel composite blade type turbine, which comprises a rotor assembly, a shell assembly arranged outside the rotor assembly and a power output shaft in transmission connection with the rotor assembly, wherein the rotor assembly comprises: the flywheel, two flywheel relative settings, and be formed with the runner in the relative one side of two flywheel, the casing subassembly includes: the middle shell is coaxially sleeved on the periphery of the rotor assembly, an annular nozzle chamber is coaxially arranged on the middle shell, a plurality of spray holes are formed in the inner side of the annular nozzle chamber in a circular ring array mode, and an air inlet is formed in the outer side of the annular nozzle chamber; and the two cover bodies are respectively arranged at two sides of the middle shell, one opposite sides of the two cover bodies are sealed with the two inertia wheels, and the two cover bodies are provided with air outlets which are communicated with the flow channel. The unsteady surface layer flow channel composite blade type turbine provided by the invention has the advantages of higher power and efficiency and simple structure.

Description

Unsteady surface layer flow channel composite blade type turbine

Technical Field

The invention relates to the technical field of turbine equipment, in particular to an unsteady surface layer flow channel composite blade type turbine.

Background

The working principle of impulse turbine (the working medium mainly expands in the spray hole blade grid) and reaction turbine (the working medium expands in the static blade grid and the movable blade grid) is that the kinetic energy of the working medium (steam or gas) directly impacts the turbine rotor blade to obtain the reaction force to obtain the mechanical energy, and the energy conversion efficiency of the single-stage turbine cannot exceed 45% under the special conditions of non-combined cycle and the like by utilizing the working mode, so that the energy waste is caused. The power and efficiency of the single-stage turbine and the miniaturization cannot be further improved on the technical level, and only two modes are needed to obtain higher power and efficiency under the condition that the working medium input condition is unchanged: one is to increase power and efficiency with a single turbine of larger diameter, and the other is to increase power and efficiency with multiple turbines, both of which make the mechanical structure more and more complex, costly and bulky.

Disclosure of Invention

In view of the defects in the prior art, the invention aims to provide an unsteady surface layer flow channel composite vane type turbine, so as to improve the power and the efficiency thereof and have a simple structure.

In order to achieve the above object, the present invention provides an unsteady surface layer flow channel composite vane turbine, including a rotor assembly, a casing assembly disposed outside the rotor assembly, and a power output shaft drivingly connected to the rotor assembly, wherein the rotor assembly includes:

the two inertia wheels are oppositely arranged and fixedly connected with each other, and a flow channel is formed on one opposite side of the two inertia wheels;

the housing assembly includes:

the middle shell is coaxially sleeved on the periphery of the rotor assembly, an annular nozzle chamber is coaxially arranged on the middle shell, a plurality of spray holes are formed in the inner side of the annular nozzle chamber in a circular ring array mode, and an air inlet is formed in the outer side of the annular nozzle chamber; and

the cover bodies are respectively arranged on two sides of the middle shell and fixedly connected with the middle shell, one opposite side of each cover body and the two inertia wheels are kept sealed through a sealing assembly, and air outlets are formed in the two cover bodies and communicated with the flow channel.

Further, the rotor assembly further comprises impellers, and at least one impeller is coaxially arranged between the two inertia wheels;

when the number of the impellers is one, the flow channel is formed between the impeller and the inertia wheel;

when the number of the impellers is larger than or equal to two, the flow passages are formed between the impellers and the inertia wheel and between two adjacent impellers.

Further, the rotor subassembly still includes the blade, and a plurality of the blade is the annular array setting two between the flywheel, the both ends of blade with two flywheel fixed connection.

Further, the orifice includes smooth connection's section of admitting air and the section of giving vent to anger each other, the section of admitting air is the loudspeaker form and is close to the one end of annular nozzle room is great end, the section of admitting air to the interior working medium fluidic of annular nozzle comes to the slope, the section of giving vent to anger is the loudspeaker form and keeps away from the one end of annular nozzle room and is great end, the section of giving vent to anger to the direction of rotation slope of rotor subassembly.

Furthermore, a plurality of spacing pieces are fixedly arranged in the flow channel and distributed in a circular ring array around the rotating center line of the rotor assembly.

Further, the surface of the rotor assembly, which is in contact with the working fluid, comprises a plurality of peaks and/or valleys.

Further, the distance between two adjacent peaks or two adjacent valleys for controlling the roughness of the inner surface of the runner of the rotor assembly is L₁Wherein 10mm > L₁≥0.01mm。

Furthermore, the thickness of an interface layer formed on the surface of the rotor assembly, which is in contact with working medium fluid, is delta, and the distance between the flow channels is L₂Wherein δ > L₂≥0.1δ，50mm＞δ≥0.1mm。

Further, the flow channel is wavy or planar.

The invention has the beneficial effects that:

the unsteady boundary layer flow channel composite blade type turbine provided by the invention utilizes the boundary layer formed on the solid surface of the flow channel in the process of flowing fluid in the flow channel, and utilizes the viscous shear stress of the boundary layer to drive the rotor assembly to rotate, so that the kinetic energy of the working medium fluid is converted into the mechanical energy of the rotor assembly, the power and the conversion efficiency are improved, and the structure is simple.

Drawings

In order to more clearly illustrate the detailed description of the invention or the technical solutions in the prior art, the drawings that are needed in the detailed description of the invention or the prior art will be briefly described below. Throughout the drawings, like elements or portions are generally identified by like reference numerals. In the drawings, elements or portions are not necessarily drawn to scale.

FIG. 1 is a perspective view of an unsteady facing flow path composite blade turbine provided in accordance with an embodiment of the present invention;

FIG. 2 is a front view of the unsteady facing flow path composite vane turbine shown in FIG. 1;

FIG. 3 is a cross-sectional view taken along line A-A of FIG. 2;

FIG. 4 is a cross-sectional view taken along line B-B of FIG. 3;

FIG. 5 is an enlarged view at C shown in FIG. 3;

FIG. 6 is a perspective view of the rotor assembly of the unsteady facing flow channel composite vane turbine shown in FIG. 1;

FIG. 7 is a cross-sectional view of FIG. 6;

FIG. 8 is an enlarged view at D of FIG. 7;

FIG. 9 is an enlarged view at E shown in FIG. 7;

FIG. 10 is a perspective view of an unsteady facing flow channel composite blade turbine according to a second embodiment of the present invention;

FIG. 11 is a perspective view of the rotor assembly of the unsteady facing flow channel composite vane turbine shown in FIG. 10;

FIG. 12 is a cross-sectional view of FIG. 11;

FIG. 13 is a perspective view of an unsteady facing flow channel composite blade turbine provided in accordance with a third embodiment of the present invention;

FIG. 14 is a perspective view of the rotor assembly of the unsteady facing flow channel composite vane turbine shown in FIG. 13;

FIG. 15 is a cross-sectional view of FIG. 14;

FIG. 16 is a perspective view of an unsteady facing flow channel composite blade turbine provided in accordance with a third embodiment of the present invention;

FIG. 17 is a perspective view of the rotor assembly of the unsteady facing flow channel composite vane turbine shown in FIG. 16;

fig. 18 is a cross-sectional view of fig. 17.

Reference numerals:

100-rotor component, 110-inertia wheel, 120-impeller, 130-blade, 140-spacing piece, 101-flow channel, 102-air outlet hole, 103-first blade positioning groove, 200-shell component, 210-middle shell, 211-annular nozzle chamber, 212-spray hole, 213-air inlet, 220-cover body, 221-air outlet, 222-mounting groove, 201-air inlet section, 202-air outlet section, 300-power output shaft, 400-sealing component, 410-sealing ring and 420-sealing spring.

Detailed Description

Embodiments of the present invention will be described in detail below with reference to the accompanying drawings. The following examples are only for illustrating the technical solutions of the present invention more clearly, and therefore are only examples, and the protection scope of the present invention is not limited thereby.

It is to be noted that, unless otherwise specified, technical or scientific terms used herein shall have the ordinary meaning as understood by those skilled in the art to which the invention pertains.

In the description of the present application, it is to be understood that the terms "central," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "front," "rear," "left," "right," "vertical," "horizontal," "top," "bottom," "inner," "outer," "clockwise," "counterclockwise," "axial," "radial," "circumferential," and the like are used in the orientations and positional relationships indicated in the drawings for convenience in describing the invention and to simplify the description, and are not intended to indicate or imply that the referenced device or element must have a particular orientation, be constructed and operated in a particular orientation, and are therefore not to be considered limiting of the invention.

Furthermore, the terms "first", "second", etc. are used for descriptive purposes only and are not to be construed as indicating or implying relative importance or implicitly indicating the number of technical features indicated. In the description of the present invention, "a plurality" means two or more unless specifically defined otherwise.

In this application, unless expressly stated or limited otherwise, the terms "mounted," "connected," "secured," and the like are to be construed broadly and can include, for example, fixed connections as well as removable connections or integral parts; can be mechanically or electrically connected; either directly or indirectly through intervening media, either internally or in any other relationship. The specific meanings of the above terms in the present invention can be understood by those skilled in the art according to specific situations.

In this application, unless expressly stated or limited otherwise, the first feature "on" or "under" the second feature may be directly contacting the first and second features or indirectly contacting the first and second features through intervening media. Also, a first feature "on," "over," and "above" a second feature may be directly or diagonally above the second feature, or may simply indicate that the first feature is at a higher level than the second feature. A first feature being "under," "below," and "beneath" a second feature may be directly under or obliquely under the first feature, or may simply mean that the first feature is at a lesser elevation than the second feature.

As shown in fig. 1 to 18, the present invention provides an unsteady surface layer flow channel composite vane turbine, which includes a rotor assembly 100, a casing assembly 200 disposed outside the rotor assembly 100, and a power output shaft 300 drivingly connected to the rotor assembly 100.

Wherein the rotor assembly 100 includes a flywheel 110. Specifically, the number of the inertia wheels 110 is two, the two inertia wheels 110 are oppositely disposed and fixedly connected to each other, and the flow passage 101 is formed at an opposite side of the two inertia wheels 110. Specifically, the two inertia wheels 110 are positioned by the power output shaft 300 and fixedly connected by bolts, and the two inertia wheels 110 are spaced apart by a certain distance, thereby forming the flow passage 101 between the two inertia wheels 110. Of course, the inertia wheel 110 further has a plurality of air outlets 102 along the axial line thereof, the air outlets 102 communicating with the flow channel 101, and the air outlets 102 are arranged on the inertia wheel 110 in a circular array around the axial line of the inertia wheel 110. When the rotor assembly is used, working medium fluid enters the flow channel 101, an adhesive layer is formed on the solid surface of the rotor assembly 100, which is in contact with the working medium fluid, and the fluid drives the rotor assembly 100 to rotate under the action of viscous shear stress of the adhesive layer, so that energy conversion is performed in the flow channel 101 to improve the conversion efficiency.

The housing assembly 200 includes a middle housing 210 and a cover 220.

The middle housing 210 is annular and coaxially sleeved on the periphery of the rotor assembly 100, the middle housing 210 is coaxially provided with an annular nozzle chamber 211, the inner side of the annular nozzle chamber 211 is provided with a plurality of nozzle holes 212 in a circular array, and the outer side of the annular nozzle chamber is provided with an air inlet 213. The annular nozzle chamber 211 is formed in the middle shell 210, so that all the spray holes 212 can uniformly supply air, the arrangement of air inlet pipes is reduced, and the structure is simple. Meanwhile, the plurality of spray holes 212 are arranged in a circular ring array, so that the working fluid can uniformly enter the flow channel 101 and form torque in the same direction of the flow channel 101, and the conversion efficiency is improved.

The number of the covers 220 is two, and the two covers 220 are respectively disposed at two sides of the middle case 210 and fixedly connected to the middle case 210. Specifically, the cover 220 is fixedly coupled to the middle case 210 by coupling bolts through a sealing assembly and maintains a seal. The two opposite sides of the two covers 220 are sealed with the two inertia wheels 110 through the sealing assembly 400, the two covers 220 are both provided with air outlets 221, and the air outlets 221 are communicated with the flow channel 101.

Specifically, the power output shaft 300 is in transmission connection with the rotor assembly 100 through a spline, and is also in rotational connection with the two covers 220 through bearings.

Specifically, seal assembly 400 includes a seal ring 410 and a seal spring 420. Wherein, a mounting groove 222 is coaxially formed on one side of the cover 220 facing the inertia wheel 110 or one side of the inertia wheel facing the cover, and the sealing ring 410 is slidably mounted in the mounting groove 222. The number of the sealing springs 420 is plural, the plurality of sealing springs 420 are disposed in the mounting groove 222 in a circular array, both ends of each of the plurality of sealing springs 420 are abutted against the sealing ring 410 and the mounting groove 222, and the sealing springs 420 tend to move the sealing ring 410 in a direction approaching the flywheel 110 or the cover 220 in a natural state. Specifically, when the mounting groove 222 is formed on the cover 220, the sealing spring 420 has a tendency to move the sealing ring 410 toward the flywheel; when the mounting groove is formed on the flywheel 110, the sealing spring 420 has a tendency to move the sealing ring 410 in a direction to approach the cover 220.

When the rotor assembly is used, the working fluid sprayed from the spray holes 212 flows into the flow channel 101, in the process that the working fluid flows in the flow channel 101, an attached layer is formed on the solid surface of the rotor assembly 100, which is in contact with the working fluid, and under the action of viscous shear stress of the attached layer, the fluid drives the rotor assembly 100 to rotate, so that energy conversion is carried out in the flow channel 101.

Specifically, fluid is a general term for gas and liquid in nature, and is a medium with continuous fluidity, and such fluid with actual viscosity action is also called newtonian fluid. This is because the fluid is composed of a large number of molecules, and the molecules in each part are easy to move relatively, and the intensity of the movement between molecules varies with the physical conditions of fluid speed, pressure and temperature. When two adjacent layers of fluid slide or deform in shearing mode, the interaction between the fluid molecules can generate shearing stress in opposite directions to prevent the fluid from sliding or deforming in shearing mode, which is called viscous shearing stress. Experiments prove that the viscous shear stress is related to physical environments such as viscosity coefficients, relative sliding speeds and temperatures of different fluids.

Thus, if the working fluid (steam or gas) is in contact with the solid surface at a high reynolds number and has relative motion, the thin fluid layer near the solid surface reduces the velocity of the working fluid due to viscous shear stress; the fluid clinging to the solid surface is adhered to the object surface, and the relative speed with the object surface is equal to zero; a very thin shear layer, the boundary layer, exists on the solid surface in the flow field. The flow outside the boundary layer can be essentially regarded as a non-viscous ideal fluid, the flow velocity being the main flow zone velocity. And the fluid molecules next to the solid surface are adsorbed on the object plane, and the flow velocity is zero. Thus, near the surface of the solid, there must be a region of large normal velocity gradient, which is the boundary layer.

Because the viscous shear stress and the inertia force in the boundary layer are in the same order of magnitude, compared with the conventional turbine, the blade is impacted by the fluid energy of the working medium (steam or gas), and the fluid energy of the working medium (steam or gas) can transmit more kinetic energy to the rotor assembly through the boundary layer, so that the utilization efficiency of the rotor assembly on the energy of the working medium is improved, the output power is improved, the vibration phenomenon of the rotor assembly is reduced, and the stable work of the rotor assembly is realized.

Meanwhile, according to the flow state of working medium fluid, the boundary layer is divided into a laminar boundary layer and a turbulent boundary layer, and different layered flows (generally divided into an inner layer and an outer layer) exist in the two boundary layers. The inner layer comprises a viscous bottom layer close to the wall surface, and the inner layer accounts for about 20% of the whole layer of the boundary layer, wherein the viscous shear stress is maximum and consists of a plurality of small vortexes; the buffer layer is arranged upwards, and then the buffer layer is arranged upwards until the outer layer of the boundary layer is a turbulent layer which is formed by large-size vortexes and has large momentum exchange. The outer layer is from this turbulent layer up to where the velocity is very similar to the outflow. For the rotor assembly, it is the turbulent boundary layer that is primarily responsible for its actual operation.

When the fluid with high Reynolds number is converted into mechanical function by the rotor assembly, the fluid flow in the rotor assembly is firstly transited from the laminar boundary layer to the turbulent boundary layer, and the viscous shear stress of the turbulent boundary layer is far greater than that of the laminar boundary layer, so that the transmission of turbulent energy in the turbulent boundary layer is also greater. This is because the turbulent kinetic energy is generated by the strong shear at the bottom of the turbulent boundary layer, i.e., at the transition layer of the inner layer. Inside the turbulent boundary layer, the turbulent kinetic energy is transferred gradually from inside to outside and from small vortex to large vortex to form the mixture of high turbulent kinetic energy fluid and low turbulent kinetic energy fluid. The mixing is continuously generated in the whole boundary layer, the difference turbulence between turbulence pulsation and the random motion of fluid molecules is random, abnormal and three-dimensional rotational flow, and a pseudo-sequence structure is also arranged behind the random. The turbulent pulsations grow, break up and disappear and the turbulent micelles and vortices are fissioned to form a transfer of energy. Especially, when the Reynolds number of the fluid is increased and the roughness of the solid wall surface is larger, the granularity of the flow structure in the turbulent boundary layer is smaller, the shearing action is stronger, the transferred kinetic energy is larger, and the efficiency is higher.

Therefore, the efficiency of the conversion and utilization of the fluid energy of the working medium (steam or gas) by utilizing the physical characteristics of the turbulent unsteady boundary layer is far higher than that of the prior art in which the kinetic energy of the fluid energy of the working medium (steam or gas) directly impacts the turbine blade to obtain the form of rotating mechanical work, and the turbine rotor assembly has the advantages of high power, high efficiency, smaller vibration and quieter vibration of the rotor assembly, simple structure and better economical efficiency.

Regarding the macrostructure of the three-dimensional unsteady turbulent boundary layer in the rotor assembly, the following mathematical model can be used for expression:

velocity profile: u. of⁺＝U/v^*，y⁺＝yv^*/v，

Wherein u is₊Is dimensionless speed, y⁺Is a dimensionless distance.

In particular, the velocity in the viscous bottom layer

Changes linearly with y, and is also called linear underlayer (u)⁺＝y⁺) (ii) a The transition layer is the transition from a viscous bottom layer to a completely turbulent layer, and the molecular viscous shear stress is as important as the turbulent shear stress (u)⁺≈-3.05+5ln y⁺) (ii) a The flow of the logarithmic law layer is in a completely turbulent state, and the molecular viscous stress can be ignored (

Wherein k is 0.40 and B is 5.5); trail rule layer: still completely turbulent, but with significantly reduced turbulence intensity, small velocity gradients and reduced molecular viscosity effects(ii) a Adhesive top layer: in the transition from the boundary turbulent layer to the external non-turbulent layer, turbulent pulsation causes external non-turbulent flow to be involved in the boundary layer to generate mixing, so that the turbulent flow strength is weakened continuously, and the speed is influenced by the external non-turbulent flow.

Wherein,

wherein δ is the boundary layer thickness.

It should be noted here that the three-dimensional unsteady turbulence boundary layer mathematical model in the rotor assembly is only a simple expression of the macroscopic structure of the turbulence boundary layer in the flow channel 101, but in reality, the boundary layer structure is complex, and the turbulent mathematical model cannot be used to accurately solve the problem, so these data cannot be used to limit the protection scope of the present invention.

In one embodiment, the rotor assembly 100 further includes impellers 120, at least one impeller 120 being coaxially disposed between the two inertia wheels 110. Specifically, the impeller 120 and the flywheel 110 are connected to be one body by a connection bolt.

When the number of the impellers 120 is one, the flow passage 101 is formed between the impeller 120 and the inertia wheel 110, that is, two flow passages 101 are formed in the rotor assembly 100.

When the number of the impellers 120 is greater than or equal to two, the impellers 120 are sequentially arranged between two inertia wheels 110 at intervals, and the flow passages 101 are formed between the impellers 120 and the inertia wheels 110 and between two adjacent impellers 120, that is, no less than three flow passages 101 are formed on the rotor assembly 100. Of course, the impeller is also provided with an air outlet 102.

The impeller 120 is disposed between the two inertia wheels 110 to increase the number of the flow paths 101. By increasing the number of the flow channels 101, the number of boundary layers formed in the rotor assembly 100 is increased, that is, the contact area between the working fluid and the rotor assembly 100 is increased, so that more working fluid can be subjected to energy conversion through the boundary layers formed on the surface of the rotor assembly 100, the purpose of obtaining higher high turbulence energy is achieved, and the conversion efficiency is further improved.

In one embodiment, rotor assembly 100 further includes blades 130. The number of the blades 130 is plural, the plural blades 130 are disposed between the two inertia wheels 110 in an annular array, and both ends of the blades are respectively fixedly connected with the two inertia wheels 110. Specifically, the opposite sides of the two inertia wheels 110 are provided with first blade positioning slots 103 matched with the blades 130, the blades 130 are fixedly clamped between the two inertia wheels 110 through the first blade positioning slots 103, and after the working fluid is sprayed from the spray holes 212, the working fluid impacts the blades 130, so that the kinetic energy of the working fluid is converted into the mechanical energy of the blades 130 to drive the blades 130 to rotate, and further the whole rotor assembly 100 is driven to rotate. When the blade 130 needs to be replaced or repaired, the blade 130 needing to be replaced or repaired can be taken out by detaching one flywheel 110, so that the replacement and repair of the blade 130 are facilitated, and meanwhile, because the blade 130 is a single independent part, when the blade 130 needs to be replaced or repaired, only the damaged blade 130 needs to be repaired, so that the repair cost is low.

When the impeller 120 is disposed between the two inertia wheels 110, the impeller 120 may be located inside the blade 130 and fixedly connected to the inertia wheels 110, so as to drive the impeller 120 to rotate together, or a second blade positioning slot may be disposed on the impeller 120, and the impeller 120 is clamped with the blade 130 through the second blade positioning slot, so as to drive the impeller 120 to rotate by the blade 110.

When the turbine rotor assembly is used, the working fluid sprayed from the spray holes 212 firstly impacts the blades 130, so that the kinetic energy of the working fluid is converted into the mechanical energy for rotating the rotor assembly 100, the instant torque is improved when the turbine is started, the starting kinetic energy of the turbine is improved, the turbine rotor assembly is convenient to start, the energy loss in the starting process is reduced, and the energy conversion efficiency is further improved.

In one embodiment, the nozzle hole 212 includes an inlet section 201 and an outlet section 202 that are smoothly connected to each other. The gas inlet section 201 is trumpet-shaped, one end close to the annular nozzle chamber 211 is a larger end, and the gas inlet section 201 inclines towards the incoming direction of the working medium fluid in the annular nozzle chamber 211. When the annular nozzle chamber 211 is used, working fluid enters the annular nozzle chamber 211 from the air inlet 213 of the annular nozzle chamber 211 and can enter the spray hole 212 along the inlet of the air inlet section 201 of the spray hole 212 in the flowing process of the annular nozzle chamber 211, so that the resistance of the gas entering the spray hole 212 from the annular nozzle chamber 211 is reduced, the energy loss is reduced, and the energy conversion efficiency is improved. And the air inlet section 201 of the spray hole 212 is arranged in a horn shape, so that the speed of the working fluid sprayed out of the spray hole 212 can be increased by increasing the air inlet amount of the spray hole 212.

The gas outlet section 202 is flared and the end away from the annular nozzle chamber 211 is the larger end, and the gas outlet section 202 is inclined toward the rotation direction of the rotor assembly 100. The air outlet section 202 of the jet hole 212 is arranged in a horn shape, so that the working fluid sprayed out of the jet hole 212 is dispersed, the working fluid can impact the blade 130 to the maximum extent, and the energy conversion efficiency is improved. By arranging the air outlet section 202 of the nozzle hole 212 to be inclined towards the rotation direction of the rotor assembly 100, the working fluid sprayed from the nozzle hole 212 can impact the blade 130 to drive the rotor assembly 100 to rotate.

In one embodiment, a plurality of spacers 140 are fixedly disposed within the flow channel 101, and the plurality of spacers 140 are distributed in a circular array around the rotation centerline of the rotor assembly 100.

The spacing pieces 140 are fixedly arranged in the flow channel 101 to control the spacing of the flow channel 101, and meanwhile, the spacing pieces 140 can also play a role in supporting the impeller 120 and/or the inertia wheel 110, so that the flow of working medium fluid is stabilized, the vibration of the rotor assembly 100 is reduced, and the energy conversion efficiency is further improved.

In one embodiment, the surface of rotor assembly 100 that contacts the working fluid includes a plurality of peaks and/or valleys. Specifically, the surfaces of the vane 130, the impeller 120, and the inertia wheel 110, which are in contact with the working fluid, are rough surfaces consisting of many minute peaks and valleys. When the fluid in the boundary layer is in contact with the solid surface and moves relatively, if the solid surface is provided with a rough surface consisting of a plurality of tiny peaks and valleys, the viscous shear stress is increased in the process of exchanging energy with the fluid, and therefore the energy conversion efficiency is improved.

By increasing the surface roughness in the runner of the rotor assembly 100, the viscous shear stress of the working fluid acting on the rotor assembly 100 is increased, and the energy conversion efficiency is improved.

In one embodiment, the distance between two adjacent peaks or two adjacent valleys for controlling the roughness of the inner surface of the runner of the rotor assembly is L₁Wherein 10mm > L₁Not less than 0.01 mm. By controlling the surface roughness in the runner of the rotor assembly 100, the purpose of controlling the viscous shear stress of the boundary layer is achieved, and the energy conversion efficiency is improved.

In one embodiment, the boundary layer formed on the surface of the rotor assembly 100 contacting the working fluid has a thickness δ and the channels 101 have a spacing L₂Wherein δ > L₂Is more than or equal to 0.1 delta, and the delta is more than 50mm and more than or equal to 0.1 mm. By controlling the distance between the runners 101 and the thickness of the boundary layer, more working fluid forms the boundary layer on the surface of the rotor assembly 100, so that the kinetic energy of the working fluid is converted into the mechanical energy of the rotor assembly 100 through the boundary layer.

In one embodiment, the flow channel 101 is wavy or planar. Specifically, when the surface of the flow channel 101 is wavy, the surfaces of the impeller 120 and the flywheel 110 constituting the flow channel 101 are wavy; when the flow path 101 is planar, the surfaces of the impeller 120 and the flywheel 110 constituting the flow path 101 are planar. Preferably, the flow channel 101 is wavy, and the wavy flow channel 101 can improve the energy conversion efficiency by increasing the acting time of the working fluid acting on the rotor assembly 100, and can also increase the contact area between the fluid and the rotor assembly 100 under the condition that the radius of the rotor assembly 100 is the same, so as to improve the energy conversion efficiency.

In one embodiment, the number of vanes and orifices is equal. Specifically, each blade corresponds to one jet hole, and the plurality of jet holes are formed, so that the impact thrust of working medium fluid to the blades is improved, and the energy conversion efficiency is improved.

In the description of the present invention, numerous specific details are set forth. It is understood, however, that embodiments of the invention may be practiced without these specific details. In some instances, well-known methods, structures and techniques have not been shown in detail in order not to obscure an understanding of this description.

Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; such modifications and substitutions do not depart from the spirit and scope of the present invention, and they should be construed as being included in the following claims and description.

Claims

1. The utility model provides an unsteady constant boundary layer runner composite vane type turbine, includes rotor subassembly, sets up the housing assembly outside the rotor subassembly and with the power take off shaft of rotor subassembly transmission connection which characterized in that: the rotor assembly includes:

the housing assembly includes:

2. The unsteady surface layer flow path composite vane turbine as claimed in claim 1, wherein: the rotor assembly further comprises impellers, and at least one impeller is coaxially arranged between the two inertia wheels;

3. The unsteady surface flow path composite vane turbine as claimed in any one of claims 1 or 2, wherein: the rotor subassembly still includes the blade, and is a plurality of the blade is the annular array setting two between the flywheel, the both ends of blade with two flywheel fixed connection.

4. The unsteady surface layer flow path composite vane turbine as claimed in claim 3, wherein: the orifice includes smooth connection's section of admitting air and the section of giving vent to anger each other, the section of admitting air is the loudspeaker form and is close to the one end of annular nozzle room is great end, the section of admitting air to the interior working medium fluidic of annular nozzle comes to the slope, the section of giving vent to anger is the loudspeaker form and keeps away from the one end of annular nozzle room and is great end, the section of giving vent to anger to the direction of rotation slope of rotor subassembly.

5. The unsteady surface flow path composite vane turbine as claimed in any one of claims 1 or 2, wherein: a plurality of spacing pieces are fixedly arranged in the flow channel and distributed in a circular ring array around the rotating center line of the rotor assembly.

6. The unsteady surface layer flow path composite vane turbine as claimed in claim 3, wherein: the rough surface of the rotor component, which is contacted with the working fluid, comprises a plurality of convex peaks and/or concave valleys.

7. The unsteady surface layer flow channel compounding of claim 6A vane turbine characterized by: the distance between two adjacent convex peaks or two adjacent concave valleys for controlling the roughness of the inner surface of the runner of the rotor assembly is L₁Wherein 10mm > L₁≥0.01mm。

8. The unsteady surface flow path composite vane turbine as claimed in any one of claims 6, wherein: the thickness of a boundary layer formed on the surface of the rotor assembly, which is in contact with working medium fluid, is delta, and the distance between the flow channels is L₂Wherein δ > L₂≥0.1δ，50mm＞δ≥0.1mm。

9. The unsteady surface layer flow path composite vane turbine as claimed in claim 8, wherein: the flow passage is wavy or planar.