Double-sided pressure-bearing rotor power propulsion mechanism with multi-specification cavities

Abstract

This invention discloses a double-sided pressure-bearing rotor propulsion mechanism with multiple cavities, belonging to the field of rotor internal combustion engine technology. The device includes a cylinder and a rotor. The cylinder and rotor are respectively provided with a first groove and a second groove, which together form a combustion chamber. The wall surface of the combustion chamber subjected to the impact of deflagration combustion gases is designated as a pressure-bearing surface, which includes circumferential sidewalls and axial sidewalls. The circumferential sidewalls of the cylinder and rotor sides are staggered circumferentially. Rotational torque is generated by the gas pressure, with one component of the cylinder and rotor fixed while the other rotates to perform work. The cylinder is provided with intake, fuel supply, ignition, and exhaust channels. The entire machine has at least two combustion chamber volumes, and airtight sealing structures are provided at the cavity partitions. This invention allows for independent start-stop of each cavity, adapting to different operating conditions and reducing fuel consumption. An axial limiting structure suppresses rotor movement, and a slotted high-temperature resistant protective coating reduces the probability of gas leakage and extends the overall service life. It can be applied to agricultural machinery, vehicles, and generator sets.

Description

Technical Field

[0001] This invention relates to the field of rotary internal combustion engine technology, and in particular to a double-sided pressure-bearing rotor power propulsion mechanism with multiple cavities. Background Technology

[0002] Existing dual-sided pressure rotary internal combustion engines rely on the pressure-bearing surfaces on the cylinder block and rotor to withstand the combined pressure of the deflagration gas and output torque. In traditional rotary engines, all combustion chambers have the same volume, and all chambers can only be injected with fuel and ignited synchronously to perform power. It is not possible to open or close some chambers individually according to different engine operating conditions.

[0003] During engine start-up, all chambers work simultaneously, resulting in high energy consumption. Even under low-load conditions such as constant-speed cruising, fuel injection and combustion continue throughout all chambers, leading to high fuel consumption and poor fuel economy. The sealing reliability between the multiple chambers is poor, and axial movement of the rotor during operation can easily occur, compressing the seals and causing gas leakage. The pressure-bearing surfaces are constantly subjected to detonation impacts and high-temperature environments, making the protective coating prone to peeling off and shortening the overall service life of the engine. Summary of the Invention Purpose of the invention

[0004] The technical problem to be solved by the present invention is to overcome the defects of the prior art and provide a double-sided pressure-bearing rotor power propulsion mechanism with multiple cavities, so as to realize independent start and stop of each cavity, participate in work as needed, reduce fuel consumption under low load conditions, reduce rotor axial movement, reduce the probability of gas leakage, and extend the service life of the pressure-bearing surface. Technical solution

[0005] A double-sided pressure-bearing rotor power propulsion mechanism with multi-specification cavities includes a cylinder and a rotor; The inner wall of the cylinder is provided with a first groove that extends synchronously in the axial and circumferential directions, and the outer wall of the rotor is provided with a second groove that extends synchronously in the axial and circumferential directions. The cylinder and the rotor are concentrically assembled and can rotate relative to each other. After assembly, the radial reference assembly gap between the inner circular surface of the cylinder and the outer circular surface of the rotor is fixed, and a thermal expansion compensation allowance is reserved.

[0006] The first groove and the second groove together form a combustion chamber, where the gas mixture completes deflagration and does work. The wall surface inside the combustion chamber that is impacted by the deflagration gas is a pressure-bearing surface. The pressure-bearing surface includes the circumferential sidewalls and axial sidewalls of the first groove and the second groove. The pressure-bearing surface bears the gas pressure generated by the deflagration in the combustion chamber and is divided into a cylinder pressure-bearing surface and a rotor pressure-bearing surface. The circumferential sidewalls of the cylinder side and the rotor side are arranged in a staggered manner along the circumference.

[0007] The staggered arrangement of the circumferential sidewalls only limits the cylinder side circumferential sidewalls and rotor side circumferential sidewalls to being staggered and not completely aligned in the circumferential direction. It does not restrict the planar angle of the two sidewalls themselves. The two sidewalls can be parallel structures or inclined angle structures. As long as the sidewalls are staggered in the circumferential direction, the pressure of the combustion gas acting on the sidewalls can be decomposed into a tangential component force in the circumferential direction, thereby forming a rotational torque. If the circumferential sidewalls are completely aligned in the circumferential direction, the gas pressure only forms a radial counterforce and cannot generate a tangential torque, so the rotor cannot achieve continuous rotation to do work.

[0008] The axial sidewall of the pressure-bearing surface only bears the axial thrust of the combustion gas and does not generate rotational torque; the rotational torque is generated only by the offset circumferential sidewall bearing the combustion gas pressure. The locking limiting structure is arranged at the axial ends of the cylinder and rotor, including detachable limiting (thrust key, flange, clamp, bolt) and fixed limiting (welding, interference fit); the present invention limits one of the cylinder and rotor to be locked and fixed by the limiting structure, while the other component rotates relative to it to do work, eliminating the work-doping structure of bidirectional reverse rotation of the cylinder and rotor.

[0009] The cylinder block is provided with an air intake passage, a fuel inlet, an ignition assembly mounting hole, and an exhaust passage. The entire machine is equipped with at least two combustion chambers of different volumes; A cavity partition is installed between adjacent cavities, and the cavity partition is equipped with an airtight sealing structure; Apart from the components locked by the limiting structure, another component rotates, relying on the relative rotation of the cylinder and rotor to output power.

[0010] Furthermore, the cylinder bearing surface and the rotor bearing surface are any one of a straight surface, an inclined surface, an inner arc surface, or an outer arc surface, respectively. The shape of the bearing surface does not change the working principle of generating tangential torque by the staggered arrangement of the circumferential sidewalls.

[0011] Furthermore, a single combustion chamber is equipped with one or more ignition holes, and a multi-ignition structure is adopted when operating under high load.

[0012] Furthermore, the intake channel can be selectively equipped with an external or integrated built-in physical supercharging component, or use intake resonance to achieve intake supercharging in order to increase the intake volume.

[0013] Furthermore, the airtight sealing structure at the cavity partition is any one of the following: metal elastic ring seal, graphite seal, spring seal, O-ring seal, packing seal, and spiral labyrinth seal; the spiral labyrinth seal includes a spiral labyrinth base and a metal sealing ring, with an elastic component added to the back of the metal sealing ring, and the elastic component applies axial preload to the metal sealing ring to compensate for thermal deformation and wear gaps, and prevent gas leakage.

[0014] Furthermore, the composite sealing structure at the rotor end is any one of the following: waveform elastic element-end face sealing ring, metal spring seal, graphite end face seal, skeleton oil seal, and flexible packing seal; high-temperature resistant waveform elastic compensation element and end face sealing ring are set at both ends of the rotor to jointly form the composite sealing structure at the rotor end.

[0015] Furthermore, a cylinder cooling channel is provided around the combustion chamber in the cylinder block, and a rotor cooling channel is opened inside the rotor to dissipate heat and cool down the pressure-bearing working surfaces of the cylinder block and rotor.

[0016] Furthermore, the cylinder bearing surface and the rotor bearing surface are covered with a high-temperature resistant protective coating. An annular groove is opened on the outer wall of the rotor to fit and limit the high-temperature resistant protective coating. Anti-detachment baffles are set at both ends of the annular groove to restrict the axial detachment of the high-temperature resistant protective coating.

[0017] Furthermore, axial limiting steps and buffer grooves are respectively provided at both ends of the rotor. The buffer grooves are used to absorb the axial impact margin. The axial limiting steps restrict the axial movement of the rotor, thereby achieving axial limiting and rotation buffering of the rotor. The rotor is mounted on the central shaft, the cylinder remains fixed, and the rotor outputs power as it rotates with the central shaft.

[0018] Furthermore, the cylinder block is provided with multiple combustion chambers along the axial direction, and the chamber partitions are an integral structure.

[0019] Furthermore, each combustion chamber is independently equipped with a fuel atomizing nozzle and an ignition control unit. The fuel circuit and ignition circuit of each combustion chamber are independent of each other, and the fuel supply and ignition of a single chamber can be cut off individually to achieve independent start and stop of a single chamber. The start and stop of fuel supply and ignition of each chamber can be controlled by an electronic controller or a mechanical on / off component. The electronic controller is electrically connected to the atomizing nozzle and ignition control unit of each chamber, and selectively opens or closes the corresponding chamber according to the operating conditions.

[0020] Furthermore, the independent central shaft structure is eliminated, and the entire machine is equipped with a fixed flange; the rotor is locked and fixed by the limiting structure on the fixed flange and kept stationary, while the cylinder body rotates circumferentially relative to the rotor; the outer ring of the cylinder body is integrally formed with a power output gear ring, and the cylinder body outputs torque to the outside through the power output gear ring; bearings, baffle rings, and an end composite sealing structure composed of high-temperature resistant waveform elastic compensation components and end face sealing rings are assembled between the cylinder body and the fixed flange to achieve rotational support and end face airtight protection. Beneficial effects

[0021] 1. This invention provides combustion chambers with at least two different volume specifications. Under low load conditions, only the small volume chamber is used to perform work, while under heavy load conditions, all chambers are opened, realizing chamber start-stop, reducing fuel consumption and improving fuel economy.

[0022] 2. The circumferential sidewalls of the cylinder block and rotor side adopt a staggered arrangement structure. The pressure of the combustion gas is decomposed into a tangential component in the circumferential direction, forming a superposition of bidirectional reaction forces, amplifying the output torque and improving the power output efficiency.

[0023] 3. An airtight sealing structure is set on the cavity partition to reduce gas leakage between cavities; the axial limiting step restricts the axial movement of the rotor, reduces the probability of the seal being crushed and damaged, and extends the service life of the seal.

[0024] 4. The high-temperature resistant protective coating on the pressure-bearing surface is clamped in the annular groove and axially limited by the anti-detachment stop edge to avoid the coating from falling off due to explosive impact and high-temperature vibration, thus extending the service life of the pressure-bearing surface.

[0025] 5. It has two power output modes: it can output power by rotating the rotor or output torque by rotating the cylinder, which can be adapted to the assembly needs of different equipment such as generator sets, vehicles, and agricultural machinery; it can use electronic control mode or mechanical mode to control the start and stop of a single chamber, which can be adapted to different production costs. Attached Figure Description

[0026] Figure 1 Overall axial sectional view of the rotary engine; Figure 2 Enlarged view of a portion of the rotor end sealing structure; Figure 3 Radial cross-sectional view of a rotary engine; Figure 4 Wiring diagram of the electrical control system; Figure 5 Axial sectional view of a cylinder-type rotary engine (without a central shaft structure).

[0027] Figure label: ① Cylinder block, ② Rotor, ③ Central shaft, ④ Cavity partition, ⑤ First groove, ⑥ Cylinder block bearing surface, ⑦ Intake passage, ⑧ Fuel inlet, ⑨ Ignition assembly mounting hole, ⑩ Exhaust passage, ⑪ Cylinder block cooling channel, ⑫ Power output gear ring, ⑬ Second groove, ⑭ Rotor bearing surface, ⑮ Axial limiting step, ⑯ Airtight sealing structure (spiral labyrinth base), ⑰ High-temperature resistant waveform elastic compensation component, ⑱ End face sealing ring, ⑲ High-temperature resistant protective coating, ⑳ Fuel atomizing nozzle, ㉑ Ignition control unit, ㉒ Electronic control unit, ㉓ External booster device, ㉔ Metal sealing ring, ㉕ Annular groove, ㉖ Anti-detachment flange, ㉗ Flow-blocking ring, ㉘ Bearing, ㉙ Rotor cooling channel, ㉚ Fixed flange. Detailed Implementation

[0028] Example 1 (Rotor-Center Shaft Output Mode) The cylinder ① is fixedly mounted on the frame, and the rotor ② is fitted onto the outside of the central shaft ③. A first groove ⑤ is machined on the inner wall of the cylinder ①, and a second groove ⑬ is machined on the outer wall of the rotor ②. The rotor ② rotates relative to the cylinder ①, and the first groove ⑤ and the second groove ⑬ align to form a combustion chamber. The combustion chamber has two volume specifications, large and small, which are arranged alternately along the circumference.

[0029] Each combustion chamber is independently equipped with a fuel atomizing nozzle (⑳) and an ignition control unit (㉑), with the fuel circuit and ignition circuit being independent of each other. The electronic control unit (㉒) collects engine speed and load signals; during engine start-up, only the small-volume chamber is opened to perform power; during climbing and heavy load conditions, the electronic control unit (㉒) opens the large-volume chamber to output full-load power; during constant speed cruising conditions, the large-volume chamber is shut off, and only the small-volume chamber operates to save fuel; the start and stop of a single chamber can also be manually controlled via mechanical fuel circuit valves and ignition switches.

[0030] The deflagration high-pressure gas acts simultaneously on the cylinder bearing surface ⑥ and the rotor bearing surface ⑭; the cylinder ① is locked and fixed by the limiting structure of the frame, and the reaction force generated by the cylinder bearing surface ⑥ is superimposed on the rotor bearing surface ⑭, amplifying the rotational torque of the rotor ②.

[0031] The multi-layered combustion chambers are arranged sequentially along the axial direction of the cylinder block ①, with chamber partitions ④ between adjacent chambers. A gas-tight sealing structure ⑯, consisting of a spiral labyrinth base and a metal sealing ring ㉔, is mounted on the chamber partition ④. The rear side of the metal sealing ring ㉔ is pre-tightened by an elastic component to compensate for thermal deformation gaps and prevent interlayer leakage of combustion gases. Axial limiting steps ⑮ at both ends of the rotor ② restrict axial movement of the rotor, and buffer grooves buffer axial impacts, protecting the end-face sealing structure. High-temperature resistant wave-shaped elastic compensation components ⑰ and end-face sealing rings ⑱ are mounted at both ends of the rotor ②, forming the end sealing structure.

[0032] The cylinder block ① has cooling channels machined around the combustion chamber ⑪, and the rotor ② has cooling channels ㉙ inside, where the coolant carries away the heat generated by the pressure-bearing surface. The pressure-bearing surface is sprayed with a high-temperature resistant protective coating ⑲, which is embedded in an annular groove ㉕ on the outer wall of the rotor ②. Anti-detachment flanges ㉖ at both ends of the groove ㉖ constrain the axial displacement of the coating and prevent it from falling off. When the rotor ② rotates, the torque is output outward through the central shaft ③.

[0033] Example 2 (Cylinder rotation output mode, no central shaft structure) The rotor ② is locked and fixed by the limiting structure of the fixed flange ㉚, and the central shaft ③ is eliminated; the cylinder ① is installed on the outer ring of the fixed flange ㉚ through the bearing ㉘, and the cylinder ① can rotate around the rotor ②; a fixed radial assembly gap is also maintained between the cylinder and the rotor, and a thermal expansion compensation allowance is reserved.

[0034] The combustion chamber structure, chamber volume ratio, sealing structure, cooling structure, coating structure, and single-chamber start-stop control method are consistent with those in Example 1. The mixture undergoes deflagration inside the combustion chamber, and the high-pressure gas acts on two sets of pressure-bearing surfaces. The rotor ② is locked by the flange, and the reaction force drives the cylinder ① to rotate. The outer ring of the cylinder ① is integrally formed with a power output gear ring ⑫, and the torque is output outward through the power output gear ring ⑫. The cylinder ① and the fixed flange ㉚ are equipped with a bearing ㉘, a baffle ring ㉗, and an end composite sealing structure to achieve rotational support and end-face airtight protection.

Claims

1. A double-sided pressure-bearing rotor power propulsion mechanism with multi-specification cavities, characterized in that, Including the cylinder block and rotor; The inner wall of the cylinder is provided with a first groove that extends synchronously in the axial and circumferential directions, and the outer wall of the rotor is provided with a second groove that extends synchronously in the axial and circumferential directions. The cylinder and the rotor are concentrically assembled and can rotate relative to each other. After assembly, the radial reference assembly gap between the inner circular surface of the cylinder and the outer circular surface of the rotor is fixed, and a thermal expansion compensation allowance is reserved. The first and second grooves together form a combustion chamber, where the gas mixture undergoes deflagration and performs work. The walls inside the combustion chamber impacted by the deflagration gases are pressure-bearing surfaces, which include the circumferential and axial sidewalls of the first and second grooves. These surfaces bear the gas pressure generated by the deflagration within the combustion chamber and are divided into cylinder pressure-bearing surfaces and rotor pressure-bearing surfaces. The circumferential sidewalls of the cylinder and rotor sides are staggered circumferentially. The high-pressure gas generated by the deflagration within the combustion chamber acts on the circumferential sidewalls, forming a rotational torque in the same direction. One side is locked and fixed by a limiting structure, and the reaction force is applied to the other component, amplifying the rotational torque. The cylinder block has an intake passage, a fuel inlet, an ignition assembly mounting hole, and an exhaust passage. The entire machine is equipped with at least two combustion chambers of different volumes; A cavity partition is installed between adjacent cavities, and the cavity partition is equipped with an airtight sealing structure; In addition to the component locked by the limiting structure, another component rotates, and the power is output by the relative rotation between the two.

2. The double-sided pressure-bearing rotor propulsion mechanism with multi-specification cavities according to claim 1, characterized in that: The cylinder bearing surface and the rotor bearing surface are any one of a straight surface, an inclined surface, an inner arc surface, or an outer arc surface.

3. The double-sided pressure-bearing rotor propulsion mechanism with multi-specification cavities according to claim 1, characterized in that: A single combustion chamber is equipped with one or more ignition holes, and a multi-ignition structure is adopted when operating under high load.

4. The double-sided pressure-bearing rotor power propulsion mechanism with multi-specification cavities according to claim 1, characterized in that: The intake channel can be selectively equipped with external or integrated built-in supercharger components, or intake resonance can be used to achieve intake supercharging to increase intake volume.

5. The double-sided pressure-bearing rotor propulsion mechanism with multi-specification cavities according to claim 1, characterized in that: The airtight sealing structure at the cavity partition is any one of the following: metal elastic ring seal, graphite seal, spring seal, O-ring seal, packing seal, and spiral labyrinth seal; the spiral labyrinth seal includes a spiral labyrinth matrix and a metal sealing ring; the composite sealing structure at the rotor end is any one of the following: waveform elastic element-end face sealing ring, metal spring seal, graphite end face seal, skeleton oil seal, and flexible packing seal; high-temperature resistant waveform elastic compensation elements and end face sealing rings are provided at both ends of the rotor to jointly constitute the composite sealing structure at the rotor end.

6. The double-sided pressure-bearing rotor propulsion mechanism with multi-specification cavities according to claim 1, characterized in that: The cylinder block has cooling channels surrounding the combustion chamber, and the rotor has cooling channels inside the rotor.

7. The double-sided pressure-bearing rotor propulsion mechanism with multi-specification cavities according to claim 1, characterized in that: Both the cylinder bearing surface and the rotor bearing surface are covered with a high-temperature resistant protective coating. An annular groove is opened on the outer wall of the rotor to fit and limit the high-temperature resistant protective coating. Anti-detachment baffles are set at both ends of the annular groove to limit the axial detachment of the high-temperature resistant protective coating.

8. The double-sided pressure-bearing rotor power propulsion mechanism with multi-specification cavities according to claim 1, characterized in that: Axial limiting steps and buffer grooves are respectively set at both ends of the rotor. The buffer grooves are used to absorb the axial impact margin. The axial limiting steps restrict the axial movement of the rotor, realizing the axial limiting and rotation buffering of the rotor. The rotor is mounted on the central shaft, the cylinder is kept fixed, and the rotor outputs power as it rotates with the central shaft.

9. The double-sided pressure-bearing rotor propulsion mechanism with multi-specification cavities according to claim 1, characterized in that: The cylinder block has multiple combustion chambers arranged axially, and the chamber partitions are an integral structure.

10. The double-sided pressure-bearing rotor propulsion mechanism with multi-specification cavities according to claim 1, characterized in that: Each combustion chamber is independently equipped with a fuel atomizing nozzle and an ignition control unit, which can cut off the fuel supply and ignition of a single chamber individually, and realize the independent start and stop of a single chamber. The start and stop of fuel supply and ignition of each chamber can be controlled by an electronic controller or a mechanical on / off component. The electronic controller is electrically connected to the atomizing nozzle and ignition control unit of each chamber, and can selectively open or close the corresponding chamber according to the working conditions.

11. The double-sided pressure-bearing rotor propulsion mechanism with multi-specification cavities according to claim 1, characterized in that: The independent central shaft structure is eliminated, and the whole machine is equipped with a fixed flange. The rotor is locked and fixed by the limiting structure on the fixed flange and kept stationary. The cylinder body rotates circumferentially relative to the rotor. The outer ring of the cylinder body is integrally formed with a power output gear ring, and the cylinder body outputs torque to the outside through the power output gear ring. Bearings, baffle rings, and an end composite sealing structure composed of high-temperature resistant waveform elastic compensation parts and end face sealing rings are assembled between the cylinder body and the fixed flange to achieve rotational support and end face airtight protection.

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