Supersonic nozzle structure capable of realizing continuous flow adjustment

Abstract

A supersonic nozzle structure capable of achieving continuous flow adjustment is characterized in that the supersonic nozzle structure is arranged in a nozzle shell, and a linear bearing positioning mounting hole is formed in the inner wall of the air inlet side of a nozzle; two linear bearings and a spring seat are mounted in the mounting hole at the same time, and the spring seat is mounted between the two linear bearings; the valve element assembly comprises a valve element, a permanent magnet and a compression spring. The valve element assembly is installed in the nozzle shell through the two linear bearings, a compression spring on the valve element assembly makes contact with the inner end face of the spring seat, the compression spring is in a compressed state, and meanwhile the rotating molded surface of the valve element makes contact with the nozzle throat in the nozzle shell. The magnet exciting coil is arranged on the outermost circle of the nozzle shell in a sleeving mode, positioning is conducted through a limiting step on the nozzle shell, axial magnetic lines are generated after the magnet exciting coil is electrified, and the permanent magnet drives the valve element to move rightwards in the axial direction under the comprehensive acting force of a magnetic field, the compression spring and air pressure. The through-flow area of the throat part of the nozzle is changed by adjusting the size of a variable annular circulation cross section between the rotating molded surface of the valve core and the throat part of the nozzle.

Description

Technical Field

[0001] The invention relates to a supersonic nozzle structure, in particular to a supersonic nozzle structure capable of realizing continuous flow regulation for turbine power equipment. Background Art

[0002] At present, in turbine power equipment with high pressure drop ratio (≥20) (including turbine generators and turbine pumps), the general structure of the gas energy conversion device before the turbine is in the form of a Rafale nozzle. In order to achieve adjustable output power of the turbine power device, it is generally adopted to change the total gas pressure before the nozzle or intermittently switch the intake channel before the nozzle. Changing the total intake pressure before the nozzle can achieve continuous adjustment, but the total intake pressure before the nozzle generally involves upstream devices, so it is difficult to change the total intake pressure and is not easy to achieve. The patent involved is [A hydrogen turbine pump, ZL201410592881.0]. The intermittent switching intake channel involves the patent [A super-high-speed turbine load adaptive speed control system and method, ZL202210307097.5], which is relatively easy to achieve power control, but the disadvantage is that the intermittent switching will cause the driving torque of the turbine shaft system to fluctuate, and the final working speed will fluctuate, and the output performance will also fluctuate. Summary of the invention

[0003] The technical problem solved by the invention is to provide a supersonic nozzle structure capable of realizing continuous flow regulation.

[0004] The technical solution of the present invention is: a supersonic nozzle structure capable of realizing continuous flow regulation, comprising: a nozzle housing, an excitation coil and a valve core assembly;

[0005] A supersonic nozzle structure is arranged inside the nozzle housing, and a linear bearing positioning installation hole is arranged on the inner wall of the nozzle air inlet side; two linear bearings and a spring seat are installed in the installation hole at the same time, and the spring seat is installed between the two linear bearings;

[0006] The valve core assembly includes a valve core, a permanent magnet and a compression spring; the left end of the valve core is a profile formed by rotating a spline curve, the right end of the valve core is a stepped hollow cylindrical structure, the middle part of the hollow cylindrical structure is fixed with a permanent magnet, both sides of the permanent magnet are radial through holes evenly distributed along the circumferential direction, and a limited position step is arranged on the outer cylindrical surface on the left side of the radial through hole on the left side of the permanent magnet; the compression spring is sleeved on the outer cylindrical surface of the valve core, and is limited by the limited position step;

[0007] The valve core assembly is installed in the nozzle housing through the two linear bearings, the compression spring on the valve core assembly contacts the inner end surface of the spring seat, the compression spring is in a compressed state, and the rotating profile of the valve core contacts the nozzle throat in the nozzle housing;

[0008] The excitation coil is sleeved on the outermost circle of the nozzle housing and is positioned by the limit step on the nozzle housing. When the excitation coil is energized, magnetic lines of force along the axial direction are generated. Under the combined force of the magnetic field, compression spring and air pressure, the permanent magnet drives the valve core to move rightward in the axial direction. The flow area of ​​the nozzle throat can be changed by adjusting the size of the annular flow section between the rotating surface of the valve core and the nozzle throat.

[0009] Preferably, the maximum diameter of the valve core profile is is the nozzle throat diameter The axial length L of the valve core profile is greater than 5 times the axial width L1 of the nozzle throat.

[0010] Optimum diameter of valve core profile is the nozzle throat diameter 1.1 times of the relationship.

[0011] Preferably, the flow area S achieved by the nozzle has an adjustment range of 0 to in The diameter of the flow-guiding cylinder at the leftmost end of the valve core, usually Take 0.1-0.2 times of.

[0012] Preferably, the form of the spline curve is selected according to the requirement for continuous adjustment of the flow area of ​​the valve core and the variation law of the axial displacement.

[0013] Preferably, the valve core as a whole has a cylindrical structure on the right side, with a limited step on the outer surface of the cylinder, and an arc transition plus a cylinder and a rotating surface on the left side. The internal air path is a large and small stepped cylindrical hole, and each stepped cylindrical hole has a radial vent. Among them, the large cylindrical hole has multiple vents evenly opened radially on both sides of the permanent magnet, multiple vents are opened radially near the inner bottom surface of the large cylinder, and multiple vents are evenly opened radially in the small cylindrical blind hole, and the axial position of the opening must be on the left cylindrical position.

[0014] Preferably, the permanent magnet is cylindrical in shape, and the magnetization method is required to be axial magnetization.

[0015] Preferably, the excitation coil is fixed to the nozzle housing by adhesive or other forms of mechanical limitation.

[0016] Preferably, the supersonic nozzle structure is suitable for gas types such as air, nitrogen, helium and hydrogen, the applicable gas temperature does not exceed 150°C, the applicable gas pressure before the nozzle does not exceed 12MPa, and the maximum diameter of the nozzle throat does not exceed

[0017] The beneficial effects of the present invention compared with the prior art are: the present invention can continuously adjust the flow rate of the gas working medium in front of the nozzle according to the output power demand, and finally realize continuous and smooth adjustment of the power output of equipment such as turbine generators and turbine pumps, avoiding the gas impact force, speed fluctuation and output performance fluctuation caused by intermittent switching adjustment. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 A cross-sectional view of a supersonic nozzle structure capable of achieving continuous flow regulation;

[0019] Figure 2 A cross-sectional view of the nozzle housing;

[0020] Figure 3 Valve core cross-section view;

[0021] Figure 4 Schematic diagram of valve core gas flow. DETAILED DESCRIPTION

[0022] The present invention will be further described below in conjunction with the embodiments.

[0023] The present invention provides an embodiment. Figure 1 is a cross-sectional view of the present invention, Figure 2 is a cross-sectional view of the nozzle housing in the present invention, Figure 3 is a cross-sectional view of the valve core in the present invention, Figure 4 It is a schematic diagram of the flow of the valve core gas path in the present invention.

[0024] The present invention is mainly composed of a nozzle housing 1, an excitation coil 2 and a valve core component 3.

[0025] The excitation coil 2 is sleeved on the outermost circle of the nozzle housing 1 and is positioned by the limiting step 4 on the nozzle housing 1. It can be fixed to the nozzle housing 1 by adhesive or other forms of mechanical limiting. When current is passed through the excitation coil 2, magnetic lines of force along the axial direction can be generated.

[0026] A supersonic nozzle structure 5 is arranged inside the nozzle housing 1, and a linear bearing positioning mounting hole 6 is arranged on the inner wall of the nozzle intake side. Two linear bearings 7 and a spring seat 8 can be installed in the mounting hole at the same time, and the spring seat 8 is installed between the two linear bearings 7.

[0027] The valve core assembly 3 is mainly composed of a valve core 9, a permanent magnet 10 and a compression spring 11. The left end of the valve core 9 is a profile 12 formed by rotating a spline curve, and the right end of the valve core is a cylindrical structure. There are large and small stepped cylindrical holes inside the cylinder. The cylindrical hole part 13 is fixed with the permanent magnet 10. Four radial through holes 14 are evenly distributed along the circumferential direction on both sides of the cylinder. Four radial through holes are also opened at the bottom of the cylindrical hole 13, and four radial through holes are also opened at the bottom of the small cylindrical blind hole. The through hole position must be on the left cylindrical end face. A limited step 15 is set on the outer cylindrical surface of the right end of the valve core 9. The compression spring 11 is sleeved on the outer cylindrical surface of the valve core 9, and the limit step 15 thereon is used for limiting. The permanent magnet 10 is cylindrical in shape, and the magnetization method is required to be axial magnetization.

[0028] After the valve core assembly 3 is assembled, it is installed in the nozzle housing 1 through two linear bearings 7, and the other end surface of the compression spring 11 on the valve core assembly 3 contacts the inner end surface of the spring seat 8 installed in the nozzle housing 1. After the assembly is completed, the compression spring 11 is in a compressed state, and the rotating profile 12 of the valve core assembly 3 contacts the nozzle throat 16 in the nozzle housing 1. In addition, the permanent magnet 10 in the valve core assembly 3 should be located in the middle of the external excitation coil 2 of the nozzle housing 1 in the axial position.

[0029] In the structural design, the valve core profile diameter is also required is the nozzle throat diameter The axial length L of the valve core profile is 1-1.2 times (preferably 1.1 times) greater than 5 times the axial width L1 of the nozzle throat.

[0030] The diameter of the guide cylinder at the leftmost end of the valve core is generally It is advisable to The nozzle can adjust the flow area S from 0 to 0.1-0.2 times.

[0031] The form of the spline curve forming the rotating profile at the left end of the valve core can be arbitrarily selected according to the continuous adjustment requirements of the flow area of ​​the valve core and the variation law of the axial displacement.

[0032] This supersonic nozzle structure that can achieve continuous flow adjustment is suitable for gas types such as air, nitrogen, helium and hydrogen. The applicable gas temperature does not exceed 150°C, the applicable gas pressure before the nozzle does not exceed 12MPa, and the maximum diameter of the nozzle throat does not exceed

[0033] Its working principle is as follows: when the excitation coil 2 is not energized, due to the action of the compression spring 11, the valve core 9 abuts against the nozzle throat 16, and the nozzle throat 16 is in a completely closed state. After the excitation coil 2 is energized, according to the direction and magnitude of the current, the excitation coil 2 generates an axial magnetic pole, and the permanent magnet 10 drives the valve core 9 to produce an axial displacement to the right under the combined force of the magnetic field, the compression spring 11 and the air pressure. The magnitude of the displacement is controlled by the balance of the magnetic force, the spring force and the air pressure, thereby realizing the change control of the flow area of ​​the nozzle throat 16. The airflow passes through the valve core 9 in turn through the cylindrical hole channel inside the valve core 9 and the radial through hole 14 to reach the throat, and finally flows through the throat adjustment area to realize the nozzle flow regulation.

[0034] The above is only a specific embodiment of the present invention, but the protection scope of the present invention is not limited thereto, and any changes or substitutions that can be easily thought of by a person skilled in the art within the technical scope disclosed by the present invention should be included in the protection scope of the present invention.

[0035] Although the present invention has been disclosed as above in the form of a preferred embodiment, it is not intended to limit the present invention. Any person skilled in the art may make possible changes and modifications to the technical solution of the present invention by using the methods and technical contents disclosed above without departing from the spirit and scope of the present invention. Therefore, any simple modifications, equivalent changes and modifications made to the above embodiments based on the technical essence of the present invention without departing from the content of the technical solution of the present invention shall fall within the protection scope of the technical solution of the present invention.

Claims

1. A supersonic nozzle structure capable of realizing continuous flow regulation, characterized in that include: Nozzle housing, excitation coil and valve core assembly; A supersonic nozzle structure is arranged inside the nozzle housing, and a linear bearing positioning installation hole is arranged on the inner wall of the nozzle air inlet side; two linear bearings and a spring seat are installed in the installation hole at the same time, and the spring seat is installed between the two linear bearings; The valve core assembly includes a valve core, a permanent magnet and a compression spring; the left end of the valve core is a profile formed by rotating a spline curve, the right end of the valve core is a stepped hollow cylindrical structure, the middle part of the hollow cylindrical structure is fixed with a permanent magnet, both sides of the permanent magnet are radial through holes evenly distributed along the circumferential direction, and a limited position step is arranged on the outer cylindrical surface on the left side of the radial through hole on the left side of the permanent magnet; the compression spring is sleeved on the outer cylindrical surface of the valve core, and is limited by the limited position step; The valve core assembly is installed in the nozzle housing through the two linear bearings, the compression spring on the valve core assembly contacts the inner end surface of the spring seat, the compression spring is in a compressed state, and the rotating profile of the valve core contacts the nozzle throat in the nozzle housing; The excitation coil is sleeved on the outermost circle of the nozzle housing and is positioned by the limit step on the nozzle housing. When the excitation coil is energized, magnetic lines of force along the axial direction are generated. Under the combined force of the magnetic field, compression spring and air pressure, the permanent magnet drives the valve core to move rightward in the axial direction. The flow area of ​​the nozzle throat can be changed by adjusting the size of the annular flow section between the rotating surface of the valve core and the nozzle throat.

2. A supersonic nozzle structure capable of realizing continuous flow regulation according to claim 1, characterized in that: Maximum diameter of valve core profile is the nozzle throat diameter The axial length L of the valve core profile is greater than 5 times the axial width L1 of the nozzle throat.

3. A supersonic nozzle structure capable of realizing continuous flow regulation according to claim 2, characterized in that: Optimal diameter of valve core profile is the nozzle throat diameter 1.1 times of the relationship.

4. A supersonic nozzle structure capable of realizing continuous flow regulation according to claim 2, characterized in that: The flow area S of the nozzle can be adjusted from 0 to in The diameter of the flow-guiding cylinder at the leftmost end of the valve core, usually Take 0.1-0.2 times of.

5. The supersonic nozzle structure capable of realizing continuous flow regulation according to claim 1, characterized in that: The form of the spline curve is selected according to the continuous adjustment requirement of the flow area of ​​the valve core and the variation law of the axial displacement.

6. The supersonic nozzle structure capable of realizing continuous flow regulation according to claim 1, characterized in that: The valve core as a whole is in the form of a cylindrical structure on the right side, with a limited step on the outer surface of the cylinder, and an arc transition plus a cylinder and a rotating surface on the left side. The internal air path is a stepped cylindrical hole of different sizes, and vents are radially opened on each stepped cylindrical hole. Among them, multiple vents are radially evenly opened on both sides of the permanent magnet in the large cylindrical hole, multiple vents are radially opened near the inner bottom surface of the large cylinder, and multiple vents are radially evenly opened in the small cylindrical blind hole, and the axial position of the opening must be on the left cylindrical position.

7. The supersonic nozzle structure capable of realizing continuous flow regulation according to claim 1, characterized in that: The permanent magnet is cylindrical in shape and the magnetization method is required to be axial magnetization.

8. The supersonic nozzle structure capable of realizing continuous flow regulation according to claim 1, characterized in that: The excitation coil is fixed to the nozzle housing by adhesive or other forms of mechanical limitation.

9. The supersonic nozzle structure capable of realizing continuous flow regulation according to claim 1, characterized in that: The supersonic nozzle structure is suitable for gas types such as air, nitrogen, helium and hydrogen, the applicable gas temperature does not exceed 150°C, the applicable gas pressure before the nozzle does not exceed 12MPa, and the maximum diameter of the nozzle throat does not exceed

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