Rotor type gas energy engine and working method thereof

Abstract

The invention discloses a rotor type gas energy engine and a working method thereof, and the rotor type gas energy engine comprises a rotor shell which is internally provided with a cylindrical rotor chamber; the rotor is arranged in the rotor chamber and comprises a rotor shaft and at least one rotor wing arranged on the rotor shaft, and the rotor chamber is divided into rotor cavities with the same number as the rotor wings by the rotor; the airflow inlet and outlet channel comprises at least one air inlet channel and at least one air outlet channel which are arranged on the rotor shell and are equal in number; the compressed air source mechanism is connected with the air inlet channel; and the electric control system is used for controlling start and stop of the air inlet valve and the exhaust valve and the air flow provided by the compressed air source mechanism so as to be matched with rotation of the rotor to complete a working cycle through the three processes of air inlet, acting and exhaust. The rotor type gas energy engine is small in vibration, low in noise, selectable in low speed, medium speed and high speed, fast in stepless speed regulation response, and capable of effectively improving work efficiency, meeting the requirements of low rotating speed, high torque and other different rotating speeds and torques, and achieving stable operation of the engine.

Description

Technical Field

[0001] The present invention relates to the technical field of engines, and in particular to a rotor-type gas energy engine and a working method thereof. Background Art

[0002] An engine is a power output device that converts other forms of energy into mechanical energy. It is primarily used in vehicles, aircraft, ships, and other fields. Common engine types in the prior art include triangular rotor internal combustion engines and reciprocating piston internal combustion engines. In triangular rotor internal combustion engines, the rotor and eccentric rotor shaft must be equipped with internal gears to transmit kinetic energy, resulting in energy conversion losses. Furthermore, triangular rotor internal combustion engines have low low-speed torque, making them difficult to power high-torque equipment such as large ships, limiting their application.

[0003] Regarding engines that use gas energy as a driving force, taking the current four-stroke piston engine as an example, its working process is divided into four steps: intake, compression, work and exhaust. The expansion pressure of the compressed gas is used to push the piston, converting the piston's reciprocating linear motion into the rotational motion of the crankshaft to output power. However, this type of engine has the following problems: (1) The engine structure is complex, including reciprocating parts such as the piston, crankshaft, and connecting rod. Its own weight is large, resulting in high energy consumption; (2) When the crankshaft and connecting rod in the engine output power, the effective lever arm of the piston is very small when it approaches the upper and lower dead centers, so the energy conversion rate is low; (3) The compression process requires a lot of power to compress the gas, which causes a lot of vibration and noise.

[0004] In view of this, it is necessary to design a rotor type gas energy engine and a working method thereof to solve the above problems. Summary of the Invention

[0005] The purpose of the present invention is to provide a rotor-type gas energy engine and its working method that can effectively improve the work efficiency while maximizing the utilization of compressed gas energy, meet the requirements of low speed and high torque and other different speeds and torques, achieve smooth operation of the engine and effectively reduce operating noise.

[0006] To achieve the above-mentioned object, the present invention provides a rotor-type gas energy engine, comprising: a rotor housing having a cylindrical rotor chamber formed therein; a rotor disposed in the rotor chamber, comprising a rotor shaft coaxially disposed with the rotor chamber and at least one rotor wing disposed on the rotor shaft, wherein the rotor divides the rotor chamber into rotor cavities equal in number to the number of the rotor wings; The air inlet and outlet channels include at least one air inlet channel and at least one exhaust channel, which are provided on the side surfaces of two opposite ends of the rotor housing. The air inlet channel and the exhaust channel are provided with an air inlet valve and an exhaust valve respectively. a compressed gas source mechanism connected to the air inlet duct and configured to provide compressed gas into the rotor chamber; The electronic control system is used to control the start and stop of the intake valve and the exhaust valve and the gas flow rate provided by the compressed gas source mechanism to cooperate with the rotation of the rotor so that a working cycle is completed through the three processes of intake, power generation and exhaust.

[0007] As a further improvement of the present invention, the rotor gas energy engine is classified according to the number of inlet ducts and rotor cavities, including a single-inlet duct single-cavity rotor gas energy engine, a single-inlet duct multi-cavity rotor gas energy engine and a multi-inlet duct multi-cavity rotor gas energy engine, wherein the single-inlet duct single-cavity rotor gas energy engine and the single-inlet duct multi-cavity rotor gas energy engine are both provided with an inlet duct and an exhaust duct, and the multi-inlet duct multi-cavity rotor gas energy engine is provided with a plurality of equal inlet ducts and exhaust ducts, and the number of inlet ducts and exhaust ducts is equal to the number of rotor wings.

[0008] As a further improvement of the present invention, the value of the central angle corresponding to the normal lines of adjacent rotor blades is set to ω, where ω is the value that divides 360° by the number of rotor blades; The central angle of the rotor cavity of the single-inlet single-cavity rotor-type gas energy engine is ω / 8 to ω / 4, and the central angle of the rotor wing is (ω-ω / 8) to (ω-ω / 4); the central angle of the rotor cavity of the single-inlet multi-cavity rotor-type gas energy engine is ω / 4 to ω / 2, and the central angle of the rotor wing is (ω-ω / 4) to (ω-ω / 2); The central angle of the rotor cavity of the multi-inlet multi-cavity rotor type gas energy engine is ω / 4 to ω / 2, and the central angle of the rotor wing is (ω-ω / 4) to (ω-ω / 2).

[0009] As a further improvement of the present invention, preferably, the central angle corresponding to the rotor cavity of the single-inlet single-cavity rotor type gas energy engine is ω / 8, and the central angle corresponding to the rotor wing is (ω-ω / 8); the central angle corresponding to the rotor cavity of the single-inlet multi-cavity rotor type gas energy engine is ω / 4, and the central angle corresponding to the rotor wing is (ω-ω / 4); the central angle corresponding to the rotor cavity of the multi-inlet multi-cavity rotor type gas energy engine is ω / 4, and the central angle corresponding to the rotor wing is (ω-ω / 4).

[0010] As a further improvement of the present invention, the single-inlet single-cavity rotor gas energy engine and the single-inlet multi-cavity rotor gas energy engine are provided with only one set of airflow inlet and outlet channels, while the multi-inlet multi-cavity rotor gas engine is provided with multiple sets of airflow inlet and outlet channels corresponding to the number of rotor cavities, respectively. In the direction opposite to the rotation of the rotor, the corresponding central angle between the inlet and exhaust channels of one set of airflow inlet and outlet channels is set to θ; Among them, θ of the single-inlet single-cavity rotor gas energy engine is ω / 8 to ω / 4; θ of the single-inlet multi-cavity rotor gas energy engine is ω / 4 to ω / 2; θ of the multi-inlet multi-cavity rotor gas energy engine is ω / 8 to ω / 4.

[0011] As a further improvement of the present invention, the central angle of rotation of the rotor during intake and exhaust is equal to θ, and the central angle of rotation of the rotor during power generation is Q=360° / α-θ-θ, where α is the number of groups of airflow inlet and outlet channels.

[0012] As a further improvement of the present invention, according to the classification of the number of rotors, the rotor-type gas energy engine includes a single-rotor rotor-type gas energy engine and a multi-rotor rotor-type gas energy engine, wherein the multiple rotor shafts in the multi-rotor rotor-type gas energy engine are parallel and the head and tail of adjacent rotors are set in opposite directions, and the relative positions of the end faces of two adjacent rotors are mirror-symmetrical. At the same time, the multiple rotor shafts are connected in sequence through a linkage mechanism, and the two adjacent rotors rotate synchronously in opposite directions to achieve torque superposition.

[0013] As a further improvement of the present invention, the number of rotors in the multi-rotor rotor-type gas energy engine is an even number; and the linkage mechanism is a herringbone gear.

[0014] As a further improvement of the present invention, the compressed gas in the compressed gas source mechanism includes any one of air, nitrogen or carbon dioxide.

[0015] As a further improvement of the present invention, one end of the rotor shaft extends outside the rotor shell and is connected to a drive wheel for driving accessories, and the other end extends outside the rotor shell and is connected to a flywheel for storing kinetic energy.

[0016] As a further improvement of the present invention, the flywheel is provided with a balancing weight, a gear ring meshingly connected to the starter, and a position sensor for monitoring the rotational position of the rotor.

[0017] As a further improvement of the present invention, an oil channel is provided at the center of the rotor shaft.

[0018] As a further improvement of the present invention, an oil cavity is provided inside the rotor wing close to the rotor shaft.

[0019] The present invention also provides a method for operating a rotor-type gas energy engine, comprising the following steps: S1. The electronic control system controls the opening of the intake valve and the flow rate of the compressed gas source mechanism, so that the compressed gas enters the rotor cavity to drive the rotor blades to rotate. When a predetermined amount of compressed gas is delivered to the rotor cavity, the electronic control system controls the closing of the intake valve, and the intake is completed. S2. Under the expansion pressure of the compressed gas, the rotor continues to rotate until it reaches the exhaust duct in front of the rotor, and the work is completed; S3, the electronic control system controls the exhaust valve to open, and the exhaust gas after the rotor chamber works is discharged through the exhaust duct, and the exhaust is completed; S4: The electronic control system controls the exhaust valve to close, and the steps S1-S3 are circulated to achieve continuous operation of the engine.

[0020] The beneficial effects of the present invention are: 1. The present invention provides compressed gas to the rotor chamber through a compressed gas source mechanism, externalizes the compression process, and makes the working steps of the engine only three processes: intake, power generation, and exhaust. This can effectively increase the power generation time, thereby improving the power generation efficiency of the engine, and can also eliminate the vibration generated by the compression process; at the same time, the setting of externalizing the compression process, combined with the setting of using the rotor wings to divide the rotor chamber into one or more rotor cavities of equal volume, can make the volume of the rotor cavity constant during the rotation of the rotor, achieve ideal isochoric power generation, and avoid the situation in which the non-isochoric power generation of the air energy engine in the prior art affects the power generation efficiency due to the existence of upper and lower dead points. That is, the rotor-type gas energy engine of the present invention can increase the central angle of rotation of the rotor during the power generation process by reasonably setting the dimensions of the rotor wings and the rotor cavity, thereby increasing the power generation time of the rotor, and effectively improving the power generation efficiency while maximizing the utilization of the compressed gas energy.

[0021] 2. The rotor-type gas energy engine of the present invention has a simple structure, small size, light weight, low center of gravity, smooth operation, low vibration, low noise, and optional high, medium and low speeds, which can meet the needs of different workplaces. When multiple air inlets and exhaust ducts are provided on the rotor shell, and multiple rotor wings are provided on the corresponding rotor shaft to divide the rotor chamber into multiple rotor cavities, the instantaneous output torque of the rotor shaft is the superimposed torque generated by several rotor cavities. Compared with the air energy engine in the prior art which needs to overcome the resistance corresponding to the compression stroke, has large operating vibration, and the output instantaneous torque is a single torque generated successively by several cylinders, the more rotor cavities the rotor-type gas energy engine of the present invention has, the greater the instantaneous output torque of the rotor shaft. That is, the rotor-type gas energy engine can be configured with a corresponding number of air inlets, exhaust ducts and rotor wings according to different usage scenarios to meet the requirements of different speeds and torques, and has wide applicability.

[0022] 3. The rotor shaft of the present invention can be used as an output shaft to directly output power outward without an intermediate transmission mechanism, with high transmission efficiency, reduced energy loss, and lower failure rate; the rotor rotates in a circle with the center of the rotor shaft as the center of the circle, with good smoothness and small rotational vibration; and an even number of rotors can be arranged side by side and the adjacent rotors can be placed in reverse at the head and tail and connected through a linkage mechanism, and the relative positions of the two adjacent rotor end faces are mirror-symmetrical, so that the two adjacent rotors rotate synchronously in opposite directions, and the torque of multiple rotors is superimposed on the basis of not changing the original single rotor speed and not increasing the engine height, thereby greatly improving the engine torque, while eliminating the overturning moment generated by the rotation of a single rotor, reducing operating vibration, increasing smoothness, and meeting the use requirements of large torque.

[0023] 4. The present invention utilizes an electronic control system to flexibly adjust the intake volume, and can adjust the output power and output torque accordingly as the load changes. It has a fast response speed and can adapt to frequently changing working conditions. That is, the rotor-type gas energy engine has strong adaptability and a wide range of uses, and can be used as a power source for unmanned submersibles, emergency peak-shaving power stations, pumped-storage power stations, ship engineering machinery, etc. BRIEF DESCRIPTION OF THE DRAWINGS

[0024] Figure 1 This is a schematic diagram of the cross-section of a single-inlet, single-chamber rotor-type gas energy engine, where (a), (b) and (c) are schematic diagrams of the intake, power and exhaust states, respectively.

[0025] Figure 2 This is a schematic diagram of the cross-sectional structure of a single-inlet dual-cavity rotor gas energy engine, where (a), (b) and (c) are schematic diagrams of the intake, power and exhaust states, respectively.

[0026] Figure 3 This is a schematic diagram of the cross-sectional structure of a dual-inlet dual-cavity rotor gas energy engine, where (a), (b) and (c) are schematic diagrams of the intake, power and exhaust states, respectively.

[0027] Figure 4 This is a schematic diagram of the cross-sectional structure of a three-inlet three-chamber rotor gas energy engine, where (a), (b) and (c) are schematic diagrams of the intake, power and exhaust states, respectively.

[0028] Figure 5 This is a schematic diagram of the cross-sectional structure of a four-inlet four-cavity rotor gas energy engine, where (a), (b) and (c) are schematic diagrams of the intake, power and exhaust states, respectively.

[0029] Figure 6 This is a schematic diagram of the cross-sectional structure of a five-inlet five-cavity rotor gas energy engine, where (a), (b) and (c) are schematic diagrams of the intake, power and exhaust states, respectively.

[0030] Figure 7 This is a schematic diagram of the top view of the multi-rotor rotor gas energy engine.

[0031] Reference numerals 10. Rotor shell; 21. Rotor shaft; 22. Rotor blade; 221. Force plane; 222. Windward surface; 31. Inlet duct; 32. Exhaust duct; 40. Linkage mechanism. DETAILED DESCRIPTION

[0032] In order to make the objectives, technical solutions and advantages of the present invention more clear, the present invention is described in detail below with reference to the accompanying drawings and specific embodiments.

[0033] It should also be noted here that, in order to avoid obscuring the present invention due to unnecessary details, only structures and / or processing steps closely related to the solutions of the present invention are shown in the drawings, while other details that are not closely related to the present invention are omitted.

[0034] In addition, it should be noted that the terms "comprises", "includes" or any other variations thereof are intended to cover non-exclusive inclusion, so that a process, method, article or apparatus that includes a series of elements includes not only those elements, but also includes other elements not explicitly listed, or also includes elements inherent to such process, method, article or apparatus.

[0035] like Figures 1 to 6 As shown, the present invention provides a rotor type gas energy engine, comprising: The rotor housing 10 has a cylindrical rotor chamber formed therein; a rotor disposed in the rotor chamber, comprising a rotor shaft 21 coaxially disposed with the rotor chamber and at least one rotor wing 22 disposed on the rotor shaft 21, wherein the rotor is in clearance fit with an inner wall of the rotor chamber and the rotor divides the rotor chamber into rotor cavities equal in number to the number of rotor wings 22; The air inlet and outlet channels include at least one air inlet channel 31 and at least one air exhaust channel 32, which are provided on the side surfaces of two opposite ends of the rotor housing 10. The air inlet channel 31 and the air exhaust channel 32 are provided with an air inlet valve and an air exhaust valve, respectively. A compressed gas source mechanism, connected to the air inlet duct 31, for providing compressed gas into the rotor chamber; The electronic control system is used to control the start and stop of the intake valve and exhaust valve and the gas flow rate provided by the compressed gas source mechanism to cooperate with the rotation of the rotor, so that a working cycle is completed through the three processes of intake, power generation and exhaust.

[0036] Specifically, the rotor housing 10 includes a shell and a front cover and a rear cover respectively provided at both ends of the shell, so that the shell, the front cover and the rear cover are enclosed to form a cylindrical rotor chamber.

[0037] Specifically, according to the classification of the air inlet duct 31 and the number of rotor cavities, the rotor type gas energy engine includes a single air inlet single cavity type rotor type gas energy engine, a single air inlet multi-cavity type rotor type gas energy engine and a multi-air inlet multi-cavity type rotor type gas energy engine, wherein the rotor wings 22 of the single air inlet multi-cavity type rotor type gas energy engine and the multi-air inlet multi-cavity type rotor type gas energy engine are both symmetrically arranged along the circumference of the rotor shaft 21, and the number of air inlet ducts 31 in the multi-air inlet multi-cavity type rotor type gas energy engine is equal to the number of rotor wings 22, and the number of exhaust ducts 32 is also equal to the number of rotor wings 22; the number of rotor cavities in the above three engines is equal to the number of rotor wings 22.

[0038] Assume that the number of rotor wings 22 is E, the central angle corresponding to the rotor wings 22 is β, the central angle corresponding to the rotor cavity is γ, and the central angle corresponding to the normal of adjacent rotor wings 22 is ω, wherein the relationship between E, β, γ, and ω is ω=γ+β=360° / E; The single-inlet single-cavity rotor gas energy engine and the single-inlet multi-cavity rotor gas energy engine are provided with only one set of airflow inlet and outlet channels. The multi-inlet multi-cavity rotor gas engine is provided with multiple sets of airflow inlet and outlet channels corresponding to the number of multiple rotor cavities. In the direction opposite to the rotation of the rotor, the corresponding central angle between the inlet duct 31 and the exhaust duct 32 of one set of airflow inlet and outlet channels is set to θ, as shown in FIG. Figure 1 As shown in FIG. 2 , θ is the angle between a straight line passing through the center of the intake passage 31 and pointing to the center of the rotor case 10 and a straight line passing through the center of the exhaust passage 32 and pointing to the center of the rotor case 10 .

[0039] As shown in Table 1, for a single-inlet single-cavity rotor gas energy engine, the number E of the rotor wings 22 is 1, the range of γ is ω / 8 to ω / 4, the range of β is (ω-ω / 8) to (ω-ω / 4), and the range of θ is ω / 8 to ω / 4; For a single-inlet multi-cavity rotor gas energy engine, the number E of rotor wings 22 is in the range of 2 to 10, preferably 2 to 7; γ is in the range of ω / 4 to ω / 2, β is in the range of (ω-ω / 4) to (ω-ω / 2), and θ is in the range of ω / 4 to ω / 2; For a multi-inlet multi-cavity rotor gas energy engine, the number E of rotor wings 22 ranges from 2 to 10, preferably from 2 to 7; the range of γ is from ω / 4 to ω / 2, the range of β is from (ω-ω / 4) to (ω-ω / 2), and the range of the corresponding central angle θ between the inlet and the exhaust located behind the inlet along the direction of rotor rotation is from ω / 8 to ω / 4.

[0040] Preferably, the central angle γ corresponding to the rotor cavity of the single-inlet single-cavity rotor type gas energy engine is ω / 8, the central angle β corresponding to the rotor wing 22 is (ω-ω / 8), and the central angle θ corresponding between the inlet duct normal and the exhaust duct normal is ω / 8; the central angle γ corresponding to the rotor cavity of the single-inlet multi-cavity rotor type gas energy engine is ω / 4, the central angle β corresponding to the rotor wing 22 is (ω-ω / 4), and the central angle θ corresponding between the inlet duct normal and the exhaust duct normal is ω / 4; the central angle γ corresponding to the rotor cavity of the multi-inlet multi-cavity rotor type gas energy engine is ω / 4, the central angle β corresponding to the rotor wing 22 is (ω-ω / 4), and the central angle θ corresponding between the inlet duct normal and the exhaust duct normal is ω / 8. Since ω=γ+β, by increasing the central angle β of the rotor blade 22 as much as possible within a reasonable range and reducing the central angle γ of the rotor cavity, the amount of compressed gas used can be reduced, which is conducive to maximizing the utilization rate of compressed gas and thus achieving the purpose of improving efficiency and saving energy and reducing consumption.

[0041] In addition, by minimizing the distance between the intake duct 31 and the exhaust duct 32 behind it along the direction of rotor rotation within a reasonable range, that is, reducing the adjacent central angles, the central angle of the rotor rotation during the intake and exhaust processes can be reduced, and the central angle of the rotor rotation during the power generation process can be increased, thereby reducing the gas consumption and improving the power generation efficiency, which is beneficial to the full utilization of the compressed gas and meeting the economic requirements.

[0042] Specifically, during the intake and exhaust processes, the central angle of the rotor's rotation is equal to the corresponding central angle θ between the intake duct 31 and the exhaust duct 32 behind the rotor's rotation direction.

[0043] Specifically, the shapes of the rotor wings 22 of the single-inlet single-cavity rotor gas energy engine, the single-inlet multi-cavity rotor gas energy engine, and the multi-inlet multi-cavity rotor gas energy engine are the same.

[0044] The shape of the rotor blade 22 will be described below by taking a single-inlet single-cavity rotor gas energy engine as an example.

[0045] like Figure 1 As shown, a rotor wing 22 is provided on a single-inlet single-cavity rotor gas energy engine, so that a rotor cavity is formed in the rotor chamber. Along the direction of rotor rotation, the rotor wing 22 is provided with a windward surface 222 and a force-bearing plane 221, as shown in FIG. Figure 1As shown in Figure (a), in the initial state of the intake process, the force-bearing plane 221 of the rotor wing 22 is located in front of the intake duct 31, allowing compressed gas to enter the rotor cavity through the intake duct 31 and drive the rotor wing 22 to rotate. The force-bearing plane 221 is a plane perpendicular to the tangent direction of the rotor shell 10, and the windward surface 222 is a streamlined arc shape to reduce the resistance to the forward movement of the rotor wing 22. The specific shape of the force-bearing plane 221 and the windward surface 222 of the rotor wing 22 ensures that during rotor rotation, the tangential torque on the force-bearing plane 221 of the rotor wing 22 is much greater than the force acting in the opposite direction of the rotor rotation on the windward surface 222. This, in turn, utilizes the principle of leverage to make the rotor rotation more energy-saving.

[0046] Specifically, the rotor shaft 21 and the rotor blade 22 are integrated; an oil passage is provided at the center of the rotor shaft 21, and an oil chamber is provided inside the rotor blade 22 and is connected to the oil passage at the center of the rotor shaft 21; The oil chamber is arranged in the inner ring area of the rotor wing 22, that is, the position of the rotor wing 22 close to the rotor shaft 21. By arranging the oil chamber in the inner ring area of the rotor wing 22, the mass of the outer ring part of the rotor as a whole, that is, the part of the rotor away from the rotor shaft 21, can be made greater than the mass of the inner ring part of the rotor as a whole, so as to increase the inertia of the rotor rotation, and thus can generate a flywheel-like effect to assist the rotor rotation during the rotor rotation process.

[0047] Specifically, the two end surfaces of the rotor are planes that are clearance-matched with the end surfaces of the rotor chamber. The side surfaces of the rotor adjacent to the rotor chamber, i.e., the side surfaces of the rotor wings 22, are arcuate surfaces that are clearance-matched with the side surfaces of the rotor chamber. For a single-inlet duct type, when there are two or more rotor chambers, the working surfaces of the rotor adjacent to the rotor chamber, i.e., the end surfaces and side surfaces of the rotor, must be provided with seals. Such seals include oil seals and air seals. In other words, the working surfaces of the rotor adjacent to the rotor chamber of a single-inlet duct multi-chamber rotor-type gas energy engine must be provided with seals to prevent leakage between adjacent rotor chambers from affecting work efficiency. However, in a single-inlet duct single-chamber rotor-type gas energy engine, since only a single rotor chamber is present, the working surfaces of the rotor adjacent to the rotor chamber do not require seals.

[0048] In addition, for the multi-inlet duct multi-cavity rotor type gas energy engine, since the rotor shell 10 is provided with an equal number of air inlet and outlet channel groups formed by the air inlet ducts 31 and exhaust ducts 32 which are equal to the number of rotor cavities, multiple rotor cavities simultaneously complete a working cycle during operation and synchronously go through the same three processes of intake, work and exhaust, so that the instantaneous air pressure in the multiple rotor cavities in the rotor chamber is equal to achieve dynamic balance. Therefore, there is no problem of air leakage between adjacent rotor cavities, that is, the working surface adjacent to the rotor chamber of the multi-inlet duct multi-cavity rotor type gas energy engine does not need to be provided with seals.

[0049] The working surfaces of the single-inlet single-cavity rotor gas energy engine and the multi-inlet multi-cavity rotor gas energy engine do not need to be equipped with seals, which can effectively reduce the friction resistance at the working surface, reduce friction work, and reduce the failure rate of components; the rotor chamber and the rotor working surface are easier to achieve full ion coating, and without the friction of seals, they are also more durable.

[0050] In addition, in this example, the engine's oil tank is independently set and separated from the rotor chamber, and the two are not connected. For engine types in which the working surface of the rotor has no seals, that is, the single-inlet single-cavity rotor gas energy engine and the multi-inlet multi-cavity rotor gas energy engine, there is no oil involved in the rotor chamber during operation, and ideal zero emissions can be achieved. In particular, when compressed air is used as the energy medium, these two engines can be used in manned and enclosed spaces.

[0051] Specifically, such as Figure 1 As shown, the single-inlet single-cavity rotor gas energy engine is provided with only one rotor wing 22, a rotor cavity is formed in the rotor chamber, and both the inlet duct 31 and the exhaust duct 32 are provided with one; For a single-inlet multi-cavity rotor gas energy engine, there is one inlet duct 31 and one exhaust duct 32, and multiple rotor wings 22 are provided, so that the rotor chamber is formed with a rotor cavity equal to the number of rotor wings 22, such as Figure 2 The figure shows a single-inlet dual-cavity rotor gas energy engine, with two rotor wings 22 provided, forming two rotor cavities in the rotor chamber; for single-inlet three-cavity rotor gas energy engines and single-inlet multi-cavity rotor gas energy engines with four cavities or more, the arrangement of the inlet duct 31 and exhaust duct 32 is the same as that of the single-inlet multi-cavity rotor gas energy engine, and the arrangement of the rotor wings 22 and rotor cavities is the same as that of the single-inlet dual-cavity rotor gas energy engine, and will not be repeated here; For a multi-inlet multi-cavity rotor gas energy engine, a plurality of rotor wings 22 are provided on the rotor shaft 21, and a corresponding rotor chamber is formed with a rotor cavity equal to the number of rotor wings 22, and a corresponding rotor shell 10 is provided with an air flow inlet and outlet channel equal to the number of rotor wings 22. Figures 3 to 6 They are, in order, a dual-inlet dual-cavity rotor gas energy engine, a triple-inlet three-cavity rotor gas energy engine, a quad-inlet four-cavity rotor gas energy engine, and a quad-inlet five-cavity rotor gas energy engine.

[0052] The structures of the intake duct 31 and the exhaust duct 32 on the single-inlet-single-cavity rotor gas energy engine, the single-inlet-multi-cavity rotor gas energy engine and the multi-inlet-multi-cavity rotor gas energy engine are the same. The following is an example of the rotor rotating counterclockwise during the operation of the single-inlet-single-cavity rotor gas energy engine ( Figure 1The arrangement of the intake duct 31 and the exhaust duct 32 will be described by taking the direction indicated by the arrow (a) as an example.

[0053] like Figure 1 As shown, the center lines of the inlet duct 31 and the exhaust duct 32 are parallel to the tangent or secant of the rotor shell 10, and the flow direction of the gas is set along the direction of rotation of the rotor, so that when the compressed gas enters the rotor cavity through the inlet duct 31 during the intake process, it will give the force plane 221 of the rotor wing 22 a force to rotate in the counterclockwise direction, and when the rotor wing 22 rotates to the exhaust position for exhaust, it is conducive to the rapid discharge of the gas to the outside of the rotor shell 10 without affecting the periodic motion of the rotor wing 22.

[0054] Specifically, the exhaust passage 32 is connected to an exhaust manifold and a muffler in sequence to discharge exhaust gas after work.

[0055] Specifically, the compressed air source mechanism is connected to the air inlet duct 31 via a one-way valve and a flow control valve. The compressed air source mechanism is any mechanism that can provide compressed air to the rotor housing 10. Depending on the use environment, the compressed air source mechanism includes any of a compressed air supply station connected to the air inlet duct 31 via a pipeline, a high-pressure gas storage tank, or an air compressor that can provide compressed air. Exemplarily, the terminal of the compressed air source mechanism is a high-pressure gas storage tank, which is equipped with a valve for controlling gas output and a safety valve. When the air pressure exceeds the safety value, the gas is automatically exhausted and reduced in pressure to ensure operational safety.

[0056] The compressed gas in the compressed gas source mechanism includes any one of air, nitrogen or carbon dioxide.

[0057] Specifically, the electronic control system is an ECU (electronic control unit), which is electrically connected to the intake valve, exhaust valve, one-way valve and flow regulating valve, and is also electrically connected to the position sensor on the flywheel. The electronic control system is used to control the start and stop of the intake valve and exhaust valve and the gas flow rate provided by the compressed air source mechanism, and cooperate with the rotation of the rotor to complete a working cycle through the three processes of intake, power generation and exhaust.

[0058] Specifically, one end of the rotor shaft 21 extends outside the rotor housing 10 and is connected to a drive wheel for driving accessories. The other end extends outside the rotor housing 10 and is connected to a flywheel for storing kinetic energy, which outputs power outward from this end. The flywheel and the rotating shaft are circumferentially positioned using a flat key. The flywheel is also equipped with a balance weight and a gear ring that meshes with the starter. The flywheel is also equipped with a position mark for the rotor shaft 21, as well as a magnetic induction position sensor and a speed sensor for monitoring the rotor's rotational position. The flywheel is a circular disk with a large rotational inertia. During the rotor's work, the flywheel stores some of the rotor's kinetic energy, which is used to overcome resistance during the intake and exhaust processes, driving the rotor shaft 21 to complete the intake and exhaust processes, ensuring that the rotational angular velocity and output torque of the rotor shaft 21 are as uniform as possible, and enabling the engine to overcome short-term overloads. Specifically, the various parameters of the single-inlet-duct single-cavity rotor gas energy engine, the single-inlet-duct multi-cavity rotor gas energy engine and the multi-inlet-duct multi-cavity rotor gas energy engine classified according to the inlet duct 31 and the number of rotor cavities are shown in Table 1, among which the single-inlet-duct single-cavity rotor gas energy engine and the single-inlet-duct multi-cavity rotor gas energy engine are summarized as single-inlet-duct type, and the multi-inlet-duct multi-cavity rotor gas energy engine is summarized as multi-inlet-duct type.

[0059] Table 1 Parameters of the rotary gas energy engine

[0060] Specifically, the "others" in Table 1 refer to the single air inlet and double-cavity or higher type; α is the number of groups of air inlet and outlet channels.

[0061] The three types of rotor-type gas energy engines shown in Table 1 are all single-rotor settings. The rotor completes a working cycle through three processes: intake, power generation, and exhaust. For the single-inlet type, the number of times the rotor rotates 360° and performs power generation is equal to the number of rotor cavities. Among them, the instantaneous torque generated by the single-inlet single-cavity rotor-type gas energy engine is the torque generated by a single rotor cavity, and the instantaneous torque generated by the single-inlet multi-cavity rotor-type gas energy engine is the single torque generated successively by several rotor cavities; for the multi-inlet multi-cavity rotor gas energy engine, the number of times the rotor rotates 360° and performs power generation is equal to the square of the number of rotor cavities E, and the instantaneous torque generated is the superimposed torque generated simultaneously by several rotor cavities.

[0062] The rotor-type gas energy engine is provided with a rotor cavity (E=1), and the rotor shell has only one set of airflow inlet and outlet channels (α=1). The central angle of the rotor rotation is 360° (derived from 360° / α). It completes one working cycle and performs one work. The central angles of the rotor rotation during the three processes of intake, power generation, and exhaust are specifically: the central angles of the rotor rotation during the intake and exhaust processes are equal to the corresponding central angle θ between the intake channel 31 of a set of airflow inlet and outlet channels and the exhaust channel 32 behind the rotor in the direction of rotation. The central angle of the rotor rotation during the power generation process is Q=360° / α-θ-θ, where α is the number of airflow inlet and outlet channels.

[0063] When the rotor-type gas energy engine is provided with two or more rotor cavities (E ≥ 2) and the rotor housing has only one set of airflow inlet and outlet channels (α = 1), the average central angle of the rotor's rotation is 360° / α. The rotor completes a number of working cycles equal to the number of rotor cavities E, and the number of times the rotor performs work is equal to the number of rotor cavities E. Specifically, the central angles of the rotor's rotation during the intake, power, and exhaust processes are: the central angles of the rotor's rotation during both intake and exhaust processes are equal to the corresponding central angle θ between the intake channel 31 of a set of airflow inlet and outlet channels and the exhaust channel 32 located behind the rotor in the direction of rotation. The central angle of the rotor's rotation during the power process is Q = 360° / α - θ - θ, where α is the number of airflow inlet and outlet channels.

[0064] The rotor-type gas energy engine, when provided with two or more rotor cavities (E≥2) and the rotor shell has a number of groups of airflow inlet and outlet channels equal to the number E of rotor cavities (α=E≥2), the central angle of the rotor's rotation is 360° / α. The rotor completes a number of working cycles equal to the number E of rotor cavities. The central angles of the rotor's rotation during the three processes of intake, power generation, and exhaust are specifically as follows: the central angles of the rotor's rotation during intake and exhaust are equal to the corresponding central angle θ between an intake channel 31 of a group of airflow inlet and outlet channels and an exhaust channel 32 behind the rotor in the direction of rotation. The central angle of the rotor's rotation during the power generation process is Q=360° / α-θ-θ, where α is the number of groups of airflow inlet and outlet channels.

[0065] In summary, in the single-rotor gas energy engine, the rotor rotates with the rotor shaft axis as the center, and the average central angle of rotation is 360°, which corresponds to the bisection value (360° / α) of the number of groups α of the airflow inlet and outlet channels of the rotor shell. After the three processes of intake, power generation, and exhaust, the central angles of rotation of the rotor are θ, Q, and θ respectively, completing a number of working cycles equal to the number E of rotor cavities, and the number of power generation times is equal to the number E of rotor cavities.

[0066] In applications such as ships and aircraft tractors, engines need to meet the requirements of high torque, low vibration, and low height. In order to increase the torque of a single rotor, the size of the rotor and rotor shell needs to be increased. However, due to the height restrictions of the environmental space, there are many limitations on increasing the size. Because the rotor shaft 21 of the gas energy engine of the present invention is coaxially arranged with the rotor chamber, the rotor shaft 21 can be used as an output shaft to output power outward. Therefore, the present invention can arrange multiple rotors in sequence on the same horizontal plane, so that the rotor shafts 21 of the multiple rotors are parallel and the head and tail of adjacent rotors are arranged in opposite directions, and the relative positions of the end faces of two adjacent rotors are mirror-symmetrical. At the same end of the engine, the multiple rotor shafts 21 are sequentially connected through a linkage mechanism 40 to achieve torque superposition, and power is output outward from one or two rotor shafts 21. In particular, the arrangement in which two counter-rotating rotor shafts 21 output power outward is directly compatible with some ships that utilize two counter-rotating shafts to install two propellers, without requiring a conversion mechanism. As a result, the instantaneous torque generated by the engine is the superimposed torque generated synchronously by multiple rotors. Therefore, without changing the original speed of a single rotor, without increasing the size of the rotor shell and rotor, etc., and without increasing the height of the engine, the instantaneous torque output by the engine is effectively increased by the multi-rotor arrangement, and the overturning moment generated by the rotation of a single rotor can be eliminated, thereby improving the stability of the ship during navigation.

[0067] Specifically, such as Figure 7 The figure shows an engine with multiple rotors. The number of rotors is even, and multiple rotors of the same model are arranged coplanarly, with their rotor shafts parallel to each other. A linkage mechanism 40, such as a herringbone gear, is coaxially arranged on the rotor shaft 21. The head and tail positions of the two adjacent rotors are opposite, that is, when viewed from the same end, the tail end of one rotor is located at that end, and the head end of the other rotor is located at that end. Moreover, on the same end face, the relative positions of the end faces of the two adjacent rotors are arranged in a mirror-symmetrical manner, and the positions of the drive wheels, balance weights, flywheels, etc. used to drive accessories at the front and rear ends of one rotor shaft are adjusted accordingly to be consistent with the setting positions of the other. Moreover, at the same end of the engine, the two adjacent rotor shafts are meshed and connected by herringbone gears of the same size, so that the relative positions of the adjacent rotor end faces are mirror-symmetrical. That is, when viewed from the same end, one of the two adjacent rotors rotates clockwise and the other rotates counterclockwise. Therefore, the simultaneous and synchronous counter-rotation of the two adjacent rotors can be used to eliminate the overturning torque generated by the rotation of a single rotor, thereby ensuring the stability of the engine during operation. At the same time, the speed of the original single rotor is not changed, and the torque is effectively increased without occupying space height.

[0068] That is, the rotor type gas energy engine of the present invention can also be divided into a single rotor type rotor type gas energy engine and a multi-rotor type rotor type gas energy engine according to the number of rotors. Among them, the above-mentioned single-inlet duct single-cavity type rotor type gas energy engine, single-inlet duct multi-cavity type rotor type gas energy engine and multi-inlet duct multi-cavity type rotor type gas energy engine belong to single-rotor type rotor type gas energy engine; the multi-rotor type rotor type gas energy engine can be further divided into a single-inlet duct single-cavity multi-rotor type rotor type gas energy engine, a single-inlet duct multi-cavity multi-rotor type rotor type gas energy engine and a multi-inlet duct multi-cavity multi-rotor type rotor type gas energy engine based on the classification of the inlet duct 31 and the number of rotor cavities.

[0069] The working methods of the above six rotor-type gas energy engines are described in detail below, taking the end face of the rotor rotating counterclockwise as an example.

[0070] (1) Single-inlet single-chamber rotor gas energy engine During intake, the starter starts (automatically separates after starting), and the electronic control system controls the intake valve to open. At the same time, the electronic control system also controls the size of the flow regulating valve according to the working conditions, so that the compressed gas in the compressed gas source mechanism enters the rotor cavity through the intake duct 31 and gives the force plane 221 of the rotor blade 22 a counterclockwise rotation force, that is, the force plane 221 converts the expansion pressure of the compressed gas into torque and pushes the rotor to rotate forward in a circumferential direction. When a predetermined amount of compressed gas is delivered to the rotor cavity, the electronic control system controls the intake valve to close. At this time, the intake is completed. Under the action of the expansion pressure of the compressed gas, the rotor continues to rotate counterclockwise to perform work. The rotor cavity moves circumferentially with the rotation of the rotor and reaches the position of the exhaust duct 32 in front of the rotor rotation. The electronic control system controls the exhaust valve to open through the obtained rotor position signal. After that, the exhaust gas after the work of the rotor cavity is discharged into the exhaust manifold through the exhaust duct 32 and is finally discharged by the exhaust muffler, and the exhaust ends. Figure 1 (a) to Figure 1 (b) is the intake process, Figure 1 (b) to Figure 1 (c) is the work process, Figure 1 (c) to Figure 1 (a) is the exhaust process; The rotor continues to rotate counterclockwise, starting the next identical cycle over and over again.

[0071] In the above process, the rotor rotates 360° (obtained from 360° / α=360° / 1). After the three processes of intake, power generation, and exhaust, the central angles of the rotor rotation are θ, Q, and θ respectively, completing a number of working cycles equal to the number of rotor cavities E. The number of times power generation is equal to the number of rotor cavities E.

[0072] When one working cycle is completed and one work is performed, the instantaneous torque generated is the expansion pressure exerted on the force-bearing plane 221 of one rotor blade 22 .

[0073] Since the rotor shaft 21 can directly serve as an output shaft to output power outward, gas energy is converted into mechanical energy without an intermediate transmission mechanism, and thus the energy conversion efficiency is high.

[0074] (2) Single-inlet multi-cavity rotor gas energy engine Compared with the single-inlet single-cavity rotor gas energy engine, the single-inlet multi-cavity rotor gas energy engine only increases the number of rotor wings 22. For the force rotation and work process of a single rotor wing 22, the single-inlet multi-cavity rotor gas energy engine is the same as the single-inlet single-cavity rotor gas energy engine, that is, the electronic control system controls the intake valve and the flow regulating valve according to the working conditions to allow the compressed gas in the compressed gas source mechanism to enter the rotor cavity. After that, the expansion pressure of the compressed gas is converted into torque to drive the rotor to work. Finally, when the rotor rotates until the rotor cavity is connected to the exhaust duct 32, the electronic control system obtains the rotor rotation position signal and controls the exhaust valve to open for exhaust.

[0075] The difference is that the rotor rotates counterclockwise, and multiple identical rotor cavities simultaneously and synchronously move forward circumferentially with the rotation of the rotor, and are connected in sequence with the intake duct 31 and the exhaust duct 32 in front of the rotor. When the average central angle of the rotor rotation is 360° (360° / α, α=1), a working cycle is completed through the three processes of intake, work, and exhaust; that is, after the first rotor cavity completes a cycle, the remaining rotor cavities also complete a cycle in sequence. The phase relationship between the multiple rotor cavities is fixed, and the central angle difference between them is ω. The gas flow direction and gas pressure change law of the multiple rotor cavities are the same. The volume of the rotor cavity remains unchanged throughout the whole process, and work is performed at equal volume. The total number of times work is performed is equal to the number of rotor cavities E. The output torque is the resultant force of the gas expansion pressure of the multiple rotor cavities, that is, the resultant force of the expansion pressure obtained by the force-bearing planes 221 of the multiple rotor wings 22, which is converted into the torque of the rotor rotation. The gas energy is converted into mechanical energy and the power is directly output outward from the rotor shaft 21. The instantaneous torque generated is the individual torque generated in sequence by the multiple rotor cavities.

[0076] Figure 2 This is a schematic diagram of the intake, power generation, and exhaust processes of the rotor cavity above the rotor wing in a single-inlet dual-cavity rotor gas energy engine, where the initial force plane is horizontal. Figure 2 (a) to 2(b) are the intake process. Figure 2 (b) to Figure 2 (c) is the work process, Figure 2 (c) to Figure 2 (a) is the exhaust process; The working principles of the remaining single-inlet multi-cavity rotor gas energy engines are the same as those of the single-inlet dual-cavity rotor gas energy engines, and will not be repeated here.

[0077] In general, in the single-inlet multi-cavity gas energy engine, the rotor rotates at an average central angle of 360° with the rotor shaft axis as the center, which corresponds to the equal value of the number α of the airflow inlet and outlet channels of the rotor shell (360° / α). After the three processes of intake, power generation, and exhaust, the central angles of the rotor rotation are θ, Q, and θ respectively, where Q = 360° / α-θ-θ. A number of working cycles equal to the number E of rotor cavities are completed, and the number of power generation times is equal to the number E of rotor cavities.

[0078] (3) Multi-inlet multi-cavity rotor gas energy engine Compared with the single-inlet single-cavity rotor gas energy engine, the multi-inlet multi-cavity rotor gas energy engine increases the number of rotor wings 22, inlet ducts 31 and exhaust ducts 32 at the same time. Figure 3 As shown, a dual-inlet dual-cavity rotor gas energy engine is used as an example for explanation.

[0079] Two identical rotor wings 22 are provided on the rotor, so that two rotor cavities are formed in the rotor chamber. The number of inlet ducts 31 and exhaust ducts 32 is the same as the number of rotor wings 22, both being two. One inlet duct 31 and one exhaust duct 32 located behind the inlet duct 31 along the direction of rotation of the rotor constitute a group of airflow inlet and outlet channels, that is, two groups of airflow inlet and outlet channels are provided on the rotor shell 10 (α=2), and the corresponding central angles between the inlet ducts 31 of the two groups of airflow inlet and outlet channels and between the exhaust ducts 32 of the two groups of airflow inlet and outlet channels are both 360° / E.

[0080] During operation, during the intake process, the starter automatically separates after starting, and the two rotor chambers are each connected to a corresponding intake duct 31. The electronic control system controls the two intake valves to open at the same time. The compressed gas entering reaches a predetermined pressure that can drive the rotor to rotate, and the two rotor chambers complete the intake synchronously. The amount of intake varies with the load. Under the action of the expansion pressure of the compressed gas, the two identical rotor chambers move forward circumferentially as the rotor rotates, and then the electronic control system controls the intake valve to close; the rotor continues to rotate counterclockwise, and after each rotor chamber completes the working process synchronously, each is connected to an exhaust duct 32 in front of the rotor rotation; in the exhaust process, the electronic control system controls the two exhaust valves to open at the same time, and the two rotor chambers synchronously discharge the exhaust gas after the work during the exhaust process, and then the electronic control system controls the exhaust valve to close. When the central angle of the rotor rotation is 360° / α, each rotor cavity completes an identical cycle at the same time. That is, for a dual-inlet dual-cavity rotor gas energy engine, when the rotor rotates 180° (360° / α=360° / 2), each rotor cavity completes an identical cycle at the same time. When the rotor rotates 360°, the two rotor cavities respectively complete two identical cycles at the same time, namely the intake, power generation, and exhaust processes. Figure 3 (a) to Figure 3 (b) is the intake process, Figure 3 (b) to Figure 3 (c) is the work process, Figure 3 (c) to Figure 3 (a) is the exhaust process.

[0081] For a multi-inlet, multi-cavity rotor-type gas energy engine, when the rotor rotates 360°, each rotor cavity simultaneously completes a number of cycles equal to the number of rotor cavities E. The number of times each rotor cavity performs work is equal to the number of rotor cavities E. The total number of times the rotor performs work is the sum of the number of times the rotor cavities perform work, which is equal to the square of the number of rotor cavities E. The torque generated is the resultant force of the expansion pressures generated by the multiple rotor cavities. The instantaneous output torque is the resultant force of the expansion pressures simultaneously exerted on the force-bearing surfaces 221 of the multiple rotor blades 22. This is the superimposed torque generated simultaneously by the multiple rotor cavities, driving the rotor to rotate, directly outputting power outward from the rotor shaft 21, and converting gas energy into mechanical energy. The more rotor cavities a multi-inlet, multi-cavity rotor-type gas energy engine has, the greater the instantaneous superimposed torque it outputs. Furthermore, this multi-inlet, multi-cavity rotor-type gas energy engine offers advantages such as uniform torque, smooth operation, strong power, fast response, high power density, and a wide speed range. Furthermore, because the multiple rotor cavities simultaneously and synchronously perform the same process, the central angle of the rotor rotation is the same, making the electronic control system simple to manage and easy to maintain.

[0082] For a dual-inlet dual-cavity rotor gas energy engine (α=E=2), when the rotor rotates 360°, each rotor cavity performs work twice, that is, the total number of times the rotor performs work is four times, which is the square of the number of rotor cavities E.

[0083] For a three-inlet three-chamber rotor gas energy engine (α=E=3), when the rotor rotates 120° (360° / α), each rotor chamber completes an identical cycle. When the rotor rotates 360°, the three rotor chambers complete three identical cycles respectively. That is, when the rotor rotates 360°, the rotor does work a total of 9 times, which is the square of the number of rotor chambers E.

[0084] For a four-inlet four-cavity rotor gas energy engine (α=E=4), when the rotor rotates 90° (360° / α), each rotor cavity completes an identical cycle. When the rotor rotates 360°, the four rotor cavities complete four identical cycles respectively. That is, when the rotor rotates 360°, the rotor does work 16 times in total, which is the square of the number of rotor cavities E.

[0085] The working principles of the other multi-inlet multi-cavity rotor gas energy engines are the same as those of the above-mentioned dual-inlet dual-cavity rotor gas energy engine, three-inlet three-cavity rotor gas energy engine, four-inlet four-cavity rotor gas energy engine, and five-inlet five-cavity rotor gas energy engine, and will not be repeated here.

[0086] In general, in the multi-inlet multi-cavity gas energy engine, the rotor rotates with the rotor shaft axis as the center, and the central angle of rotation is 360°, which corresponds to the equal value of the number α of the airflow inlet and outlet channels of the rotor shell (360° / α). After the three processes of intake, power generation, and exhaust, the central angles of the rotor rotation are θ, Q, and θ respectively, where Q=360° / α-θ-θ, completing a round of several working cycles equal to the number E of rotor cavities, and the number of work cycles is equal to the number E of rotor cavities; when the central angle of rotation of the rotor is 360°, several rotor cavities simultaneously complete a round of several working cycles equal to the number E of rotor cavities, and the total number of work cycles is equal to the sum of the number of work cycles of several rotor cavities, which is equal to the square of the number E of rotor cavities.

[0087] Regarding the multi-rotor type rotor gas energy engine, it is set on the basis of the corresponding single-rotor type rotor gas energy engine, and the rotor shafts 21 of an even number of rotors are arranged in parallel and coplanar, and the head and tail of adjacent rotors are arranged in opposite directions. At the same time, the rotor shafts 21 of adjacent rotors are connected by a linkage mechanism 40, so that the relative positions of two adjacent rotors on the same end face are mirror-symmetrical, so that the two adjacent rotors rotate synchronously in opposite directions, that is, one rotates clockwise and the other rotates counterclockwise ( Figure 7 ) to eliminate the overturning moment generated by the rotation of a single rotor and minimize vibration.

[0088] Specifically, a single-inlet single-cavity multi-rotor rotor gas energy engine is formed by an even number of single-inlet single-cavity rotor gas energy engines connected in sequence through a linkage mechanism 40; a single-inlet multi-cavity multi-rotor rotor gas energy engine is formed by an even number of single-inlet multi-cavity rotor gas energy engines connected in sequence through a linkage mechanism 40; a multi-inlet multi-cavity multi-rotor rotor gas energy engine is formed by an even number of multi-inlet multi-cavity rotor gas energy engines connected in sequence through a linkage mechanism 40; the torque output principles of these three types of multi-rotor rotor gas energy engines are the same, and the single-inlet single-cavity multi-rotor rotor gas energy engine is used as an example for explanation below.

[0089] (4) Single-inlet, single-cavity, multi-rotor rotor gas energy engine The single-inlet single-cavity multi-rotor rotor gas energy engine is designed based on the single-inlet single-cavity rotor gas energy engine. The same even number of rotor shafts 21 are arranged in parallel, and the head and tail positions of adjacent rotors are reversed. The rotor shafts 21 of adjacent rotors are connected by a linkage mechanism 40, so that the relative positions of two adjacent rotors on the same end face are mirror-symmetrical, so that the two adjacent rotors rotate synchronously in opposite directions, that is, one rotates clockwise and the other rotates counterclockwise, so as to eliminate the overturning moment generated by the rotation of a single rotor and minimize vibration.

[0090] During operation, multiple rotors synchronously complete the intake, power generation, and exhaust processes. The rotors rotate an average of 360°, each completing a cycle simultaneously and synchronously, each performing power once. Power is then output outwardly from one or both rotor shafts 21. The instantaneous output torque is generally the combined torque generated by several single-inlet, single-cavity rotor-type gas energy engines. Taking two connected rotors as an example, the two rotors rotate in opposite directions at the same central angle during operation and undergo the same process. During power generation, the force planes 221 of both rotor wings 22 simultaneously experience a tangential torque for forward motion, and the output torque is the combined torque generated by the two rotors. Since the intake, power generation, and exhaust processes of a single rotor in a single-inlet, single-cavity, multi-rotor rotor-type gas energy engine are identical to those of a single-inlet, single-cavity rotor-type gas energy engine, they will not be further described here.

[0091] The single-inlet single-cavity multi-rotor rotor gas energy engine can fully utilize the expansion pressure of compressed gas to generate a large torque and output a strong power, and it rotates smoothly, has little vibration, a low center of gravity, and good stability. It does work once per rotation and has a low speed. It is particularly suitable as a ship power to directly drive the propeller. The single-inlet single-cavity multi-rotor rotor gas energy engine can be matched with a rotary drum wind energy air compressor to achieve continuous endurance at sea. Moreover, when two of the counter-rotating rotor shafts are used to output power outward, it can directly match and drive a ship of the type that uses two rotor shafts and two propellers rotating in opposite directions, without the need to add additional devices for conversion. In particular, for the multi-inlet multi-cavity multi-rotor rotor gas energy engine, the operating principle of each rotor is the same as that of the multi-inlet multi-cavity rotor gas energy engine. Each rotor cavity performs the same process simultaneously. During operation, the instantaneous air pressure between the rotor cavities is equal, achieving dynamic balance and excellent sealing performance. The working surface of the rotor does not need to be equipped with seals to reduce friction resistance. The working cavity can be set to a full ion coating, which is more durable.

[0092] The multi-rotor rotor gas energy engine can meet the needs of high, medium and low speeds, has a wide range of applications, and can use a fixed gas source such as high-pressure air stored in abandoned mines as an energy medium to provide power for peak-shaving power stations, pumped storage water pumps and other machinery, thereby saving energy and being environmentally friendly.

[0093] The multi-rotor type rotor type gas energy engine further designed on the basis of the single-rotor type rotor type gas energy engine can provide greater torque without changing the original speed of a single rotor or increasing the height, meeting the high torque demand.

[0094] In summary, the rotor-type gas energy engine of the present invention completes a working cycle, including three processes: intake, power generation, and exhaust. By rationally setting the central angle of the rotor's rotation during these three processes, the central angle of the rotor's rotation during the intake and exhaust processes can be minimized, while the central angle of the rotor's rotation during the power generation process can be increased, allowing sufficient time for the power generation process, thereby effectively improving power generation efficiency and reducing energy consumption. Furthermore, the rotor shaft 21 can directly serve as an output shaft to output power outward. The rotor rotates in a circular motion about the rotor shaft 21. Since there is no mass that reciprocates, rotational inertia can be effectively utilized, resulting in smooth overall engine operation and, when multiple rotor chambers are provided, high rotational speeds can be achieved, resulting in excellent high-speed performance. The present invention externalizes the compressed gas process as a power source, and controls the intake airflow through an electronic control system. The air supply can be set based on the minimum speed required to maintain stable rotor rotation in the working chamber. Furthermore, the air supply can be adjusted to adjust the rotor's speed and torque as power demand changes, thereby achieving stepless speed regulation. This not only meets response speed requirements but also fully meets the engine's various speed and torque regulation requirements.

[0095] In addition, after the compressed gas has done work, the waste gas can be recovered at the exhaust end, compressed by the compressor and then re-input into the gas storage tank, thereby realizing the recycling of the gas.

[0096] The above embodiments are only used to illustrate the technical solutions of the present invention and are not intended to limit the present invention. Although the present invention has been described in detail with reference to the preferred embodiments, it should be understood by those skilled in the art that the technical solutions of the present invention may be modified or replaced by equivalents without departing from the spirit and scope of the technical solutions of the present invention.

Claims

1. A rotary gas energy engine, characterized in that: include: a rotor housing having a cylindrical rotor chamber formed therein; a rotor disposed in the rotor chamber, comprising a rotor shaft coaxially disposed with the rotor chamber and at least one rotor wing disposed on the rotor shaft, wherein the rotor divides the rotor chamber into rotor cavities equal in number to the number of the rotor wings; The air inlet and outlet channels include at least one air inlet channel and at least one exhaust channel, which are provided on the side surfaces of two opposite ends of the rotor housing. The air inlet channel and the exhaust channel are provided with an air inlet valve and an exhaust valve respectively. a compressed gas source mechanism connected to the air inlet duct and configured to provide compressed gas into the rotor chamber; The electronic control system is used to control the start and stop of the intake valve and the exhaust valve and the gas flow rate provided by the compressed gas source mechanism to cooperate with the rotation of the rotor so that a working cycle is completed through the three processes of intake, power generation and exhaust.

2. The rotary gas energy engine according to claim 1, characterized in that: According to the classification of the number of air inlets and rotor cavities, the rotor type gas energy engine includes a single air inlet single-cavity rotor type gas energy engine, a single air inlet multi-cavity rotor type gas energy engine and a multi-air inlet multi-cavity rotor type gas energy engine. Among them, in the multi-air inlet multi-cavity rotor type gas energy engine, the number of air inlets is equal to the number of rotor wings.

3. The rotary gas energy engine according to claim 2, characterized in that: Set the value of the central angle corresponding to the normal line of the adjacent rotor blades to ω, where ω is the value that divides 360° by the number of rotor blades; The central angle of the rotor cavity of the single-inlet single-cavity rotor-type gas energy engine is ω / 8 to ω / 4, and the central angle of the rotor wing is (ω-ω / 8) to (ω-ω / 4); the central angle of the rotor cavity of the single-inlet multi-cavity rotor-type gas energy engine is ω / 4 to ω / 2, and the central angle of the rotor wing is (ω-ω / 4) to (ω-ω / 2); The central angle of the rotor cavity of the multi-inlet multi-cavity rotor type gas energy engine is ω / 4 to ω / 2, and the central angle of the rotor wing is (ω-ω / 4) to (ω-ω / 2).

4. The rotary gas energy engine according to claim 3, characterized in that: The single-inlet single-cavity rotor gas energy engine and the single-inlet multi-cavity rotor gas energy engine are provided with only one set of airflow inlet and outlet channels. The multi-inlet multi-cavity rotor gas energy engine is provided with multiple sets of airflow inlet and outlet channels corresponding to the number of rotor cavities. The central angle between the inlet and exhaust channels of one set of airflow inlet and outlet channels is set to θ in the direction opposite to the rotation of the rotor. Among them, θ of the single-inlet single-cavity rotor gas energy engine is ω / 8 to ω / 4; θ of the single-inlet multi-cavity rotor gas energy engine is ω / 4 to ω / 2; θ of the multi-inlet multi-cavity rotor gas energy engine is ω / 8 to ω / 4.

5. The rotary gas energy engine according to claim 4, characterized in that: The central angle of the rotor during intake and exhaust is equal to θ. The central angle of the rotor during power generation is Q = 360° / α-θ-θ, where α is the number of airflow inlet and outlet channels.

6. The rotary gas energy engine according to claim 2, characterized in that: According to the classification of the number of rotors, rotor-type gas energy engines include single-rotor rotor-type gas energy engines and multi-rotor rotor-type gas energy engines. In the multi-rotor rotor-type gas energy engine, the multiple rotor shafts are parallel and the head and tail of adjacent rotors are set in opposite directions. At the same time, the relative positions of the end faces of two adjacent rotors are mirror-symmetrical. The multiple rotor shafts are connected in sequence through a linkage mechanism, and the two adjacent rotors rotate synchronously in opposite directions to achieve torque superposition.

7. The rotary gas energy engine according to claim 6, characterized in that: The number of rotors in the multi-rotor rotor-type gas energy engine is an even number; the linkage mechanism is a herringbone gear.

8. The rotary gas energy engine according to claim 1, characterized in that: One end of the rotor shaft extends out of the rotor shell and is connected to a driving wheel for driving accessories, and the other end extends out of the rotor shell and is connected to a flywheel for storing kinetic energy.

9. The rotary gas energy engine according to claim 1, characterized in that: An oil cavity is arranged inside the rotor wing close to the rotor shaft.

10. A method for operating a rotary gas energy engine according to claim 1, characterized in that: The following steps are involved: S1. The electronic control system controls the opening of the intake valve and the flow rate of the compressed gas source mechanism, so that the compressed gas enters the rotor cavity to drive the rotor blades to rotate. When a predetermined amount of compressed gas is delivered to the rotor cavity, the electronic control system controls the closing of the intake valve, and the intake is completed. S2. Under the expansion pressure of the compressed gas, the rotor continues to rotate until it reaches the exhaust duct in front of the rotor, and the work is completed; S3, the electronic control system controls the exhaust valve to open, and the exhaust gas after the rotor chamber works is discharged through the exhaust duct, and the exhaust is completed; S4: The electronic control system controls the exhaust valve to close, and the steps S1-S3 are circulated to achieve continuous operation of the engine.

Images