Non-uniformly distributed and asymmetric swirling flow pressure reducing mechanism for gas pressure reducing valve

Abstract

The invention belongs to the technical field of pressure reducing valves, and particularly relates to a non-uniformly distributed and asymmetric vortex flow pressure reducing mechanism for a gas pressure reducing valve. According to the technical scheme, the nozzle comprises a nozzle body, a bearing handle, an ejector pin, a high-pressure spring, a positioning rivet and a sealing gasket. The angle difference delta is 8 degrees, namely, the angle a of the first central angle is 128 degrees, the angle b of the second angle is 120 degrees, and the angle c of the third angle is 112 degrees. The non-uniformly distributed and asymmetric nozzles are created for the first time, through non-uniform and asymmetric radial distribution of 112 degrees, 120 degrees and 128 degrees, moderately non-uniform enhanced vortex flow is formed in the low-pressure cavity through the nozzles, and the rotation stability effect is improved. Compared with turbulent flow caused by other designs (single nozzle, uniformly distributed nozzle and symmetrically distributed nozzle), the enhanced vortex flow generated by the design can eliminate uncertainty caused by the turbulent flow, and the output airflow can be more regular and more stable.

Description

Technical Field

[0001] This invention belongs to the field of pressure reducing valve technology, specifically relating to a non-uniformly distributed, asymmetric vortex flow pressure reducing mechanism used in a gas pressure reducing valve. Background Technology

[0002] In gas pressure reducing valve applications, maintaining a stable low-pressure gas output with consistent pressure and flow rate is crucial (whether for industrial, laboratory, or medical applications, flow stability is one of the most important performance indicators for pressure reducing valves). However, in production practice, achieving an extremely stable gas output from a pressure reducing valve is much more difficult. This is because the gas input pressure is very high (up to 20MPa or more), and the cross-sectional area of ​​the valve port (pressure reducing mechanism) connecting the high-pressure chamber to the low-pressure chamber is usually made very small (otherwise, the valve cannot be opened smoothly, requiring an opening force of 1960N / m²). (i.e., 19.6 MPa). However, the small cross-sectional area of ​​the pressure reducing valve port will generate an extremely high Reynolds number, causing turbulence and resulting in disordered and irregular fluctuations in the gas flow rate and velocity at the outlet.

[0003] According to the general engineering threshold definition, Reynolds number Re≤2000 is laminar flow (ordered airflow), 2000<Reynolds number Re<4000 is transitional flow, and Re≥4000 is turbulent flow (disordered turbulent flow).

[0004] Taking compressed air with a cylinder pressure of 20MPa as an example: The formula for calculating the Reynolds coefficient: , according to = ,in P For pressure, is the specific gas constant of air. T Thermodynamic temperature Assuming temperature T =300K, corresponding to If the density is 287 J / (kg·K), then... = , Assuming the valve orifice diameter is 1.8 mm and the flow rate is 25 L / min, Q is the mass flow rate. Given the valve cross-sectional area, converting 25 L / min to 4.167 × 10⁻⁴ m³ / s, we get T = 300 K. Flow rate , Air dynamic viscosity Pa s, Valve port Reynolds number .

[0005] Therefore, the Reynolds number Re at the valve orifice is... At that time, the pressure is much greater than that of Re4000, which causes turbulence. The disordered turbulence from the high-pressure output to the low-pressure chamber will cause disordered fluctuations in the airflow at the outlet, which will greatly affect the stability of the output airflow and thus reduce the overall performance of the pressure reducing valve. Summary of the Invention

[0006] To overcome the shortcomings of the prior art, the present invention provides a non-uniformly distributed, asymmetric vortex flow pressure reducing mechanism for gas pressure reducing valves.

[0007] The technical solution of the present invention includes a nozzle, a bearing handle, a ejector pin, a high-pressure spring, a positioning rivet, and a sealing gasket.

[0008] The nozzle has a pin hole in the middle, and the pin is installed in the pin hole and moves up and down in a straight line. One end of the pin can protrude above the pin hole, and the other end of the pin extends to the bottom of the pin hole. The sealing gasket is installed at one end of the bearing handle, and the high-pressure spring and the positioning rivet cooperate with each other to press against the other end of the bearing handle.

[0009] The nozzle and the ejector pin hole are perpendicular to each other and three non-uniformly distributed nozzles are provided. The three nozzles are connected to the ejector pin hole. The geometric center lines of the three nozzles form a first central angle, a second central angle, and a third central angle. The angle of the first central angle is greater than or equal to the angle of the second central angle and greater than or equal to the angle of the third central angle.

[0010] The nozzle is connected to the low-pressure chamber inside the pressure reducing valve, and the bearing handle is located inside the high-pressure chamber inside the pressure reducing valve.

[0011] Preferably, the first central angle, the second central angle, and the third central angle form an arithmetic sequence, that is, the angle of the first central angle is a, the angle of the second central angle is b, and the angle of the third central angle is c, and the angle difference Δ=ab=bc.

[0012] Preferably, the center lines of the three nozzles are offset by a certain distance relative to the radial line passing through the nozzle circle.

[0013] Preferably, the centerlines of the three nozzles are offset by the same eccentricity relative to the radial line passing through the nozzle circle in the same direction.

[0014] Preferably, the angular difference Δ is in the range of 5° to 15°.

[0015] Preferably, the angle difference Δ is 8°, that is, the angle a of the first central angle is 128°, the angle b of the second angle is 120°, and the angle c of the third angle is 112°.

[0016] Preferably, the three nozzles are circular holes of the same diameter.

[0017] Preferably, the three nozzles 12 are circular holes with different diameters.

[0018] This invention addresses existing problems in the pressure reducing valve industry by pioneering a non-uniformly distributed, asymmetrical, and non-radial nozzle. Through a non-uniform, asymmetrical, and non-radial distribution of 112°, 120°, and 128°, the nozzle generates a moderately non-uniform enhanced vortex flow within the low-pressure chamber, increasing rotational stability. Compared to the turbulence generated by other designs (single nozzle, uniformly distributed, and symmetrically distributed nozzles), the enhanced vortex flow generated by this design eliminates the risks and uncertainties associated with the mutual shearing and interference of multiple disordered turbulences introduced by radial nozzles. This results in more regular and stable output (outlet) airflow pressure and flow rate. Attached Figure Description

[0019] Figure 1 This is an exploded view of the present invention.

[0020] Figures 2-3 This is a schematic diagram of the structure of the present invention.

[0021] Figure 4 This is a schematic diagram of the structure of a specific embodiment 1 of the present invention.

[0022] Figure 5 for Figure 4 A cross-sectional view at point AA.

[0023] Figure 6 This is a schematic diagram of the structure of a specific embodiment 2 of the present invention.

[0024] Figure 7 for Figure 6 The sectional view of BB.

[0025] Figure 8 This is a schematic diagram of the structure of the present invention installed on a pressure reducing valve.

[0026] Figure 9 This is a screenshot of a single radial nozzle simulation.

[0027] Figure 10 This is a screenshot of a simulation of a bidirectional symmetrical radial nozzle.

[0028] Figure 11 This is a screenshot of a simulated radial nozzle divided into three equal parts.

[0029] Figure 12 This is a screenshot of a simulation of a symmetrical radial nozzle divided into four equal parts.

[0030] Figure 13 Simulation screenshots of nozzles distributed at 112°, 120°, and 128° with a radial angle of 10°.

[0031] Figure 14This is a screenshot from a simulation with an installation angle of 12°.

[0032] Figure 15 This is a screenshot from a simulation with an installation angle of 51°.

[0033] Figure 16 This is a screenshot from a simulation with an installation angle of 86°.

[0034] Figure 17 This is a screenshot from a simulation with an installation angle of 103°.

[0035] Figure 18 The pressure and flow rate fluctuation curves for a single nozzle at a flow rate of 25 L / min for 120 seconds are shown.

[0036] Figure 19 The pressure and flow rate fluctuation curves for a continuous 120 seconds at a flow rate of 25 L / min with 180° symmetrical radial dual nozzles.

[0037] Figure 20 The pressure and flow rate fluctuation curves for a three-nozzle nozzle with equal diameter and a flow rate of 25 L / min for 120 seconds are shown.

[0038] Figure 21 The pressure and flow rate fluctuation curves for a continuous 120s at a flow rate of 25L / min with four nozzles of equal diameter.

[0039] Figure 22 This is a flow rate fluctuation curve for 120 seconds at a flow rate of 25 L / min using three nozzles with a non-radial 10° included angle of 112°, 120°, and 128° according to the present invention.

[0040] Figure 23 This is a schematic diagram of the mounting angle measuring structure of the present invention installed on the pressure reducing valve.

[0041] Figures 1-23 In the middle, 1. Nozzle, 11. Ejector pin hole, 12. Nozzle, 2. Bearing handle, 3. Ejector pin, 4. High pressure spring, 5. Positioning rivet, 6. Sealing gasket, 7. Low pressure chamber, 8. High pressure chamber, 9. Air outlet, e. Eccentricity, f. Radial angle, g. Installation angle. Detailed Implementation

[0042] The embodiments of the present invention will be further described below with reference to the accompanying drawings: like Figures 1-23 As shown, this embodiment provides a non-uniformly distributed, asymmetric vortex flow pressure reducing mechanism for a gas pressure reducing valve, including a nozzle 1, a bearing shank 2, a ejector pin 3, a high-pressure spring 4, a positioning rivet 5, and a sealing gasket 6.

[0043] The nozzle 1 has a pin hole 11 in the middle. The pin 3 is installed in the pin hole 11 and moves up and down in a straight line. One end of the pin 3 can protrude above the pin hole 11, and the other end of the pin 3 extends to the bottom of the pin hole 11. The sealing gasket 6 is installed at one end of the bearing handle 2. The high pressure spring 4 and the positioning rivet 5 cooperate with each other to press against the other end of the bearing handle 2.

[0044] The nozzle 1 and the pin hole 11 are provided with three non-uniformly distributed nozzles 12 at a position perpendicular to each other. The three nozzles 12 are connected to the pin hole 11. The geometric center lines of the three nozzles 12 form a first central angle, a second central angle, and a third central angle, wherein the angle of the first central angle is greater than or equal to the angle of the second central angle and the angle of the third central angle.

[0045] The nozzle 12 is connected to the low-pressure chamber 7 inside the pressure reducing valve, and the bearing handle 2 is located inside the high-pressure chamber inside the pressure reducing valve.

[0046] Since most nozzles on the market are either single nozzles or symmetrical dual nozzles, from Figures 18-19 It can be seen that the flow curves of single nozzle and symmetrical two nozzles fluctuate violently. During the research and development process, the applicant also designed and manufactured pressure-reducing mechanisms for three-part and four-part distributed nozzles, and conducted experimental tests. Their respective flow fluctuation curves are shown in the figure below. Figures 20-21 As shown in the graph, there are numerous traffic peaks and troughs, indicating significant traffic fluctuations that fail to meet the high demand in the market.

[0047] To solve the existing problems in the pressure reducing valve industry, such as Figures 1-8 As shown, we have pioneered a non-uniformly distributed, asymmetric, and non-radial nozzle. Through its non-uniform and asymmetric radial distribution, the nozzle generates a moderately non-uniform enhanced vortex flow within the low-pressure chamber, increasing the rotational stabilization effect. Compared to the turbulence generated by other designs (single nozzle, uniformly distributed, and symmetrically distributed nozzles), the enhanced vortex flow generated by this design can eliminate the uncertainties caused by turbulence, making the output airflow more regular and stable.

[0048] Preferably, the first central angle, the second central angle, and the third central angle form an arithmetic sequence, that is, the angle of the first central angle is a, the angle of the second central angle is b, and the angle of the third central angle is c, and the angle difference Δ=ab=bc.

[0049] Using the same angle difference Δ helps to achieve stable enhanced vortex flow and reduce flow fluctuations.

[0050] Preferably, the centerlines of the three nozzles 12 are offset by a certain distance relative to the radial line passing through the circle of the nozzle 12. This eccentricity introduces a rotational force into the gas flowing from the nozzles 12, creating a strong rotational effect in the confluence zone, which in turn generates a more pronounced vortex flow and significantly reduces flow fluctuations.

[0051] Preferably, the centerlines of the three nozzles 12 are offset by the same eccentricity e relative to the radial line passing through the circle of the nozzle 12. Using the same eccentricity e facilitates processing.

[0052] Preferably, the angular difference Δ is in the range of 5° to 15°.

[0053] Preferably, the angle difference Δ is 8°, that is, the first central angle a is 128°, the second angle b is 120°, and the third angle c is 112°. This angle Δ of 8° is the optimal solution for minimizing flow fluctuation in this invention, and its flow curve is as follows: Figure 22 As shown.

[0054] Preferably, the three nozzles 12 are circular holes of the same diameter. Using circular holes facilitates machining and drilling, and circular holes exhibit less flow fluctuation compared to other hole shapes.

[0055] Preferably, the three nozzles 12 are circular holes with different diameters.

[0056] The structure of specific implementation method 1 is as follows: Figures 4-5 As shown, the three nozzles are not eccentric, with angle a being 128 degrees, angle b being 120 degrees, and angle c being 112 degrees.

[0057] The structural diagram of specific implementation method 2 is shown below. Figures 6-7 As shown, the geometric center lines of the three nozzles are at angles a = 128 degrees, b = 120 degrees, and c = 112 degrees with respect to the nozzle tip.

[0058] This invention enhances the formation of vortex flow: 1. The non-uniform angle (8° deviation) causes the tangential velocity components of the three airflows to be incompletely balanced, enhancing the rotational effect in the confluence zone and generating a more pronounced vortex flow.

[0059] 2. The intensity of vortex flow depends on the angular deviation and the flow velocity. A moderate 8° deviation can generate moderate vortex flow without causing strong instability (such as vortex shedding).

[0060] 3. Assuming an outlet flow rate of 25 L / min and three nozzles with a diameter of 3 mm, the Reynolds number of the radial airflow through the nozzles is: According to = ,in P For pressure, is the specific gas constant of air. T Thermodynamic temperature Assuming temperature T =300K, corresponding to If the density is 287 J / (kg·K), then... = , Assuming the valve orifice diameter is three 3.0mm nozzles and the flow rate is 25L / min, 25L / min is converted to 4.167×10⁻⁴m³ / s. Q is the mass flow rate. Given the valve's cross-sectional area, we can obtain... Flow rate , but , The three nozzles, with a Reynolds number of Re3780, form a transitional flow. These three laminar flows create enhanced vortex flows in the low-pressure chamber, continuously providing a stable air supply to the outlet. The enhanced vortex flow of this invention effectively suppresses shear flow and prevents vortex shearing; it also maintains the presence of vortices continuously and stably, preventing the transitional flow field from transforming into turbulence due to shear flow interference. Its actual Reynolds number will be lower than that calculated using empirical formulas. .

[0061] 4. Enhanced vortex flow: Distributions at 112°, 120°, and 128° increase the tangential velocity component. Vortex flow can stabilize the flow field through radial pressure gradients, similar to the vortex stabilizer effect. At low Reynolds numbers, vortex flow helps suppress shear layer instability and reduces the probability of turbulence.

[0062] 5. Low Reynolds number: The low Reynolds number of the radial orifice and outlet makes disturbances easily dissipated by viscosity. Even if a slight asymmetric disturbance is introduced by the non-uniform distribution, it is difficult for it to develop into turbulence.

[0063] 6. Dispersed disturbance: The three airflows will still disperse the disturbance energy, and the additional disturbance caused by the 8° deviation is small, and viscous dissipation can be effectively controlled.

[0064] The outlet can be designed with different diameters depending on the needs, with Reynolds numbers generally between 300 and 700, and the airflow is laminar. As long as vortex flow can be continuously generated in the low-pressure chamber, the outlet can continuously output laminar flow with stable velocity and no significant fluctuations in flow rate.

[0065] The following are simulation and experimental data: I. Simulation Data 1. Single radial nozzle like Figure 9As shown, since the low-pressure chamber is usually cylindrical, when the radial single-nozzle airflow encounters the inner wall of the cylinder, it is equivalent to the airflow being perpendicular to the inner wall. It will split into two bidirectional vortices (one rotating left and one rotating right), and the two airflows will shear and interfere with each other, resulting in a serious impact on the stability of the output airflow.

[0066] 2. Bidirectional symmetrical radial nozzle like Figure 10 As shown, a bidirectional symmetrical radial nozzle will generate four mutually shearing and interfering vortices, which will also seriously affect the stability of the output flow.

[0067] 3. Tripartite radial nozzle like Figure 11 As shown, the three-part radial nozzle, similar to the bidirectional symmetrical radial nozzle, will also form six mutually shearing and interfering vortices, which will also seriously affect the stability of the output flow.

[0068] 4. Four-part symmetrical radial nozzle like Figure 12 As shown, the four-part symmetrical radial nozzle is similar to the three-part nozzle, and it will also form eight mutually shearing and interfering vortices, which will also seriously affect the stability of the output airflow.

[0069] 5. Nozzles distributed at 112°, 120°, and 128°, with a radial angle of 10°. like Figure 13 As shown, the 112°, 120°, and 128° distribution, when the eccentricity e is adjusted, creates a radial angle f of 10° instead of being perpendicular to the inner wall of the low-pressure cavity. This effectively suppresses the generation of symmetrical vortices, forming only a relatively stable enhanced vortex near the outlet. Because in addition to this stable enhanced vortex near the outlet, the remaining gas continuously replenishes this enhanced vortex within the low-pressure cavity, making the flow field inside the low-pressure cavity exceptionally ordered and stable. This ensures a continuous supply of gas with stable pressure and velocity to the outlet.

[0070] The eccentricity e can be adjusted according to the structure of different pressure reducing valves, thereby adjusting the radial angle f, so that the radial angle f is within the range of 10°~15°.

[0071] Because the nozzle in the pressure-reducing mechanism of the pressure-reducing valve varies in angle between the nozzle and the pressure-reducing valve outlet in different individual products due to differences in machining and assembly precision during actual production and assembly, an angle difference of approximately 8° between the three outlet holes of the nozzle can largely offset the errors caused by machining and assembly precision without affecting the generation of enhanced vortex flow near the outlet (even random installation angles can generate enhanced vortex flow near the outlet). Figure 14The image shown is a simulation screenshot with an installation angle g of 12°. Figure 15 The image shown is a simulation screenshot with an installation angle g of 51°; as shown Figure 16 The image shown is a simulation screenshot with an installation angle g of 86°; as shown Figure 17 The image shown is a simulation screenshot with an installation angle g of 108°. The installation angle g is measured as follows: Figure 23 As shown, the installation angle g is the angle between the nozzle 12 and the outlet gas 9 between the second angle b and the third angle c. The installation angle g can be adjusted by adjusting the angle between the hole of the nozzle 12 and the starting point of the thread of the nozzle 1. An internal threaded part can be made, the nozzle 1 can be tightened on the internal threaded part, and then the hole of the nozzle 12 can be drilled to make the desired installation angle g in batches.

[0072] Pressure reducing valves with different structures can also be designed with the three outlet orifices of the nozzle having equal or unequal diameters, depending on the requirements.

[0073] II. Measured Data Under the same test conditions and methods, the curves showing the influence of different numbers and distributions of nozzles on the stability of output (outflow) flow are as follows: Figures 18-22 As shown.

[0074] This embodiment should not be considered as a limitation of the invention, but any improvements made based on the spirit of the invention should be within the protection scope of the invention.

Claims

1. A non-uniformly distributed, asymmetric vortex flow pressure reducing mechanism for a gas pressure reducing valve, characterized in that: Includes nozzle (1), bearing handle (2), ejector pin (3), high pressure spring (4), positioning rivet (5), and sealing gasket (6); The nozzle (1) has a pin hole (11) in the middle. The pin (3) is installed in the pin hole (11) and moves up and down in a straight line. One end of the pin (3) can protrude above the pin hole (11), and the other end of the pin (3) extends to the bottom of the pin hole (11). The sealing gasket (6) is installed at one end of the bearing handle (2). The high pressure spring (4) and the positioning rivet (5) cooperate with each other to press against the other end of the bearing handle (2). The nozzle (1) is provided with three non-uniformly distributed nozzles (12) at a position perpendicular to the pin hole (11). The three nozzles (12) are connected to the pin hole (11). The geometric center lines of the three nozzles (12) form a first central angle, a second central angle, and a third central angle. The angle of the first central angle is greater than or equal to the angle of the second central angle and greater than or equal to the angle of the third central angle. The nozzle (12) is connected to the low-pressure chamber (7) inside the pressure reducing valve, and the bearing handle (2) is located in the high-pressure chamber inside the pressure reducing valve.

2. The non-uniformly distributed, asymmetric vortex flow pressure reducing mechanism for a gas pressure reducing valve according to claim 1, characterized in that: The first central angle, the second central angle, and the third central angle form an arithmetic sequence, that is, the angle of the first central angle is a, the angle of the second central angle is b, and the angle of the third central angle is c, and the angle difference Δ = ab = bc, wherein the angle difference Δ is greater than 0.

3. The non-uniformly distributed, asymmetric vortex flow pressure reducing mechanism for a gas pressure reducing valve according to claim 2, characterized in that: The center lines of the three nozzles (12) are offset by a certain distance relative to the radial line of the nozzle (12) circle.

4. The non-uniformly distributed, asymmetric vortex flow pressure reducing mechanism for a gas pressure reducing valve according to claim 3, characterized in that: The centerlines of the three nozzles (12) are offset by the same eccentricity (e) relative to the radial line of the nozzle (12) circle.

5. A non-uniformly distributed, asymmetric vortex flow pressure reducing mechanism for a gas pressure reducing valve according to any one of claims 2-4, characterized in that: The angle difference Δ is in the range of 5° to 15°.

6. The non-uniformly distributed, asymmetric vortex flow pressure reducing mechanism for a gas pressure reducing valve according to claim 5, characterized in that: The angle difference Δ is 8°, that is, the angle a of the first central angle is 128°, the angle b of the second angle is 120°, and the angle c of the third angle is 112°.

7. A non-uniformly distributed, asymmetric vortex flow pressure reducing mechanism for a gas pressure reducing valve according to claim 6, characterized in that: The three nozzles (12) are circular holes of the same diameter.

8. A non-uniformly distributed, asymmetric vortex flow pressure reducing mechanism for a gas pressure reducing valve according to claim 6, characterized in that: The three nozzles (12) are circular holes of different diameters.

Images