Collaborative swirl injection device for rotor engine

Abstract

The invention provides a collaborative swirl injection device for a rotor engine. The collaborative swirl injection device comprises a head cover main body, an outer flow channel shell, a piezoelectric needle-shaped turbomachine and an electromagnetic valve. Double reverse rotational flows are generated through reverse spiral flow guide grooves in the inner wall and the outer wall of the piezoelectric needle-shaped turbomachinery, and fuel shear mixing is enhanced; and through a pressure adjusting air hole and a control system, premixing and layering dual-mode switching and spraying pneumatic shaping are achieved. The device has the advantages that flow resistance is low, atomization is good, the spraying form is matched with the flat and long combustion chamber of the rotor engine in a self-adaptive mode, and combustion efficiency is effectively improved.

Description

Technical Field

[0001] This invention relates to the field of rotary engine technology, and in particular to a cooperative swirling jet device for rotary engines. Background Technology

[0002] Rotary engines have broad application prospects in the fields of drones, range-extended electric vehicles, and high-performance power units due to their advantages such as small size, light weight, high power density, and few moving parts. However, compared with traditional reciprocating piston engines, the combustion chamber of a rotary engine is a flat, crescent-shaped elongated strip, and its spatial shape and position change as the rotor rotates. This makes combustion organization difficult and can easily lead to problems such as incomplete combustion, high emissions, and high fuel consumption.

[0003] As a core component of the engine fuel supply system, the injector's atomization quality, spray shape, and fuel-air distribution directly determine combustion efficiency. Existing injector technology mainly suffers from the following problems:

[0004] First, traditional injectors typically produce a conical or solid circular spray. This axisymmetric spray shape is severely mismatched with the flat, elongated cross-section of a rotary engine's combustion chamber. In practice, the conical spray tends to hit the upper and lower sidewalls of the combustion chamber, creating a wet-wall effect. This prevents fuel from being atomized and participating in combustion, leading to carbon buildup, oil dilution, and increased hydrocarbon emissions.

[0005] Secondly, most existing designs employ unidirectional swirling or direct-flow impact, making it difficult to achieve efficient micro-mixing of gas-liquid or liquid-liquid within extremely short distances. Especially in the high-speed scavenging flow field of a rotary engine, without a strong active shearing mechanism, fuel struggles to break down and evaporate within a limited time. Furthermore, traditional side-intake structures often incorporate complex curved guide channels internally, which not only increases manufacturing difficulty but also generates significant pressure losses and unnecessary eddy current dissipation as the fluid flows through the curved channels, reducing injection momentum.

[0006] Furthermore, the engine's requirements for the air-fuel mixture state vary under different operating conditions. During low load or cold start, stratified combustion (rich at the center and lean at the periphery) is required to ensure ignition reliability; while during high load, homogeneous premixed combustion is required to output maximum power. Existing injector structures are usually relatively fixed, making it difficult to flexibly switch between premixed and stratified modes on the same device, especially making it difficult to actively control the physical shape of the spray using aerodynamic effects.

[0007] In summary, traditional injection devices are ill-suited to the extreme combustion chamber geometry variations and the demands for efficient multi-fuel mixing in rotary engines. Therefore, there is an urgent need to develop a novel injection device that can eliminate complex internal flow channel bends to reduce flow resistance, utilize a dual counter-swirling mechanism to enhance shear mixing, and actively control the spray shape and combustion mode through variable geometry and aerodynamic shaping. Summary of the Invention

[0008] To address the shortcomings of existing technologies, this invention provides a cooperative swirling injection device for rotary engines, which solves the technical problems of complex radial air intake channel structure of injectors leading to high flow resistance, insufficient unidirectional swirling shear force leading to incomplete atomization, and difficulty in adapting the spray shape to the flat combustion chamber of rotary engines, resulting in wetted walls and low combustion efficiency.

[0009] The present invention achieves the above-mentioned technical objectives through the following technical means.

[0010] A cooperative swirling jet device for a rotary engine includes a head cover body, an outer flow channel housing, a piezoelectric needle-shaped turbine mechanism, and a solenoid valve;

[0011] The outer flow channel housing is located below the head cover body, and the piezoelectric needle-shaped turbine is mechanically supported within the outer flow channel housing cavity. The outer flow channel housing and the piezoelectric needle-shaped turbine form an annular pressure-stabilizing chamber. At least two radial air inlets are provided on the side wall of the outer flow channel housing, and the radial air inlets are connected to the annular pressure-stabilizing chamber formed inside the outer flow channel housing. The outer wall of the piezoelectric needle-shaped turbine is provided with an external spiral guide groove for guiding the first fuel flowing through the annular pressure-stabilizing chamber to generate a swirling flow in a first direction. The piezoelectric needle-shaped turbine is provided with an inner flow channel for inputting a second fuel. The inner wall of the inner flow channel is provided with an internal spiral guide groove for guiding the second fuel flowing through the inner flow channel to generate a swirling flow in a second direction opposite to the first direction. The side of the annular pressure-stabilizing chamber is provided with a pressure regulating vent, which is connected to a common chamber with different pressures through a switching valve. The electromagnetic valve is located at the main nozzle at the outlet of the outer flow channel housing.

[0012] Furthermore, the piezoelectric needle turbine mechanism is a piezoelectrically driven needle valve, including a drive unit and a hollow valve body. The hollow valve body is supported in the inner cavity of the outer flow channel housing. The outer wall surface of the hollow valve body is provided with an external spiral guide groove, and the hollow hole of the hollow valve body is provided with an internal spiral guide groove. The drive unit is used to drive the hollow valve body to rotate.

[0013] Furthermore, the helix angle of both the outer spiral guide groove and the inner spiral guide groove is 45°~60°.

[0014] Furthermore, the outflow direction of the pressure regulating vent forms an angle of 30° to 60° with the central axis of the outer flow channel shell.

[0015] Furthermore, the swirl number S of the first directional swirling flow formed in the annular pressure-stabilizing cavity is greater than 0.6.

[0016] Furthermore, a gap is provided between the main nozzle of the outer flow channel housing and the outlet of the hollow valve body, and the gap forms a premixing chamber for premixing the second fuel and the second fuel.

[0017] Furthermore, it also includes a control system, which controls the piezoelectric needle turbine mechanism, solenoid valves, a first fuel supply system, a second fuel supply system, and a switching valve to achieve premixed mode control and stratified mode control.

[0018] Furthermore, the control system controls the piezoelectric needle turbine to rotate mechanically, and simultaneously controls the fuel supply of the first fuel supply system and the second fuel supply system, so that they respectively form swirling flows in opposite directions through the annular pressure regulating chamber and the inner flow channel and mix in the premixing chamber; when the mixing is completed, the control system controls the solenoid valve to open to spray out the mixed fuel, realizing the premixing mode control; in the premixing mode, the control system controls the switching valve to connect the pressure regulating vent to the common chamber with a pressure lower than that of the annular pressure regulating chamber.

[0019] Furthermore, the control system controls the piezoelectric needle turbine to stop rotating or maintain a preset low-speed rotation state, controls the fuel supply of the first fuel supply system and the second fuel supply system, and controls the opening of the solenoid valve so that the first fuel and the second fuel with opposite swirling directions form a flat fan-shaped jet with stratified concentration during the injection process; in the stratified mode, the control system controls the switching valve to connect the pressure regulating vent to the common chamber with a pressure greater than that of the annular pressure stabilizing chamber.

[0020] The beneficial effects of this invention are as follows:

[0021] 1. The synergistic swirling injection device for a rotary engine described in this invention, by employing a radial air inlet directly connected to an annular pressure stabilizing chamber, can significantly reduce the first fuel intake flow resistance, reduce pressure loss, improve injection response speed, and simplify the processing technology.

[0022] 2. The synergistic swirling jet device for rotary engines described in this invention employs an annular pressure stabilizing chamber and an inner flow channel with external and internal spiral guide grooves rotating in opposite directions. This generates a large relative tangential velocity and strong shear force at the interface where the internal and external fluids meet, thereby achieving extreme atomization and micro-mixing, and significantly reducing the Sutter average diameter (SMD).

[0023] 3. The synergistic swirling injection device for rotary engines described in this invention, by combining a rotatable piezoelectric needle turbine mechanism with a controllable electromagnetic valve and a specific helix angle design, achieves the effect of flexibly switching between premixed mode and stratified mode on the same device, meeting the different requirements of homogeneous combustion and stratified combustion of rotary engines under all operating conditions.

[0024] 4. The synergistic swirling jet device for rotary engines described in this invention achieves dynamic management of nozzle region pressure under different operating modes by controlling pressure regulating orifices to connect common chambers with different pressures. In premixed mode, it effectively releases internal high-pressure pulses, and in stratified mode, it actively introduces external airflow for shaping, thereby ensuring the stability and controllability of the spray pattern and resolving the technical contradiction that a single structure cannot simultaneously achieve bidirectional flow field control.

[0025] 5. The cooperative swirling injection device for rotary engines described in this invention injects high-speed shaping gas into the side of the first fuel jet through pressure regulating orifices, achieving the effect of actively constraining and shaping the macroscopic shape of the spray. This allows the flat, fan-shaped jet to maintain a stable shape in the complex engine sweeping airflow field, achieving active adaptation and locking of the spray shape to the geometry of the flat, elongated combustion chamber of the rotary engine, which is impossible for traditional injectors that rely on the momentum of the fuel itself. Attached Figure Description

[0026] To more clearly illustrate the technical solutions in the embodiments of the present invention or the prior art, the drawings used in the description of the embodiments or the prior art will be briefly introduced below. The drawings described below are some embodiments of the present invention. For those skilled in the art, it is obvious that other drawings can be obtained from these drawings without creative effort.

[0027] Figure 1 This is an internal cross-sectional view of the cooperative swirling jet device for a rotary engine according to the present invention.

[0028] Figure 2 This is a cross-sectional view of the hollow valve body described in this invention.

[0029] Figure 3 This is a schematic diagram of the premixed mode described in this invention.

[0030] Figure 4 This is a schematic diagram illustrating the working principle of the layered mode described in this invention.

[0031] In the picture:

[0032] 1-Head cover body; 2-Outer flow channel shell; 3-Piezoelectric needle valve; Piezoelectric needle turbine machinery; 4-Solenoid valve; 5-Axial air inlet; 6-Bearing; 7-Radial air inlet; 8-Pressure regulating hole; 9-External spiral guide groove; 10-Internal spiral guide groove. Detailed Implementation

[0033] Embodiments of the present invention are described in detail below, examples of which are illustrated in the accompanying drawings, wherein the same or similar reference numerals denote the same or similar elements or elements having the same or similar functions throughout. The embodiments described below with reference to the accompanying drawings are exemplary and intended to explain the present invention, and should not be construed as limiting the present invention.

[0034] In the description of this invention, it should be understood that the terms "center," "longitudinal," "lateral," "length," "width," "thickness," "upper," "lower," "axial," "radial," "vertical," "horizontal," "inner," and "outer," etc., indicating orientation or positional relationships based on the orientation or positional relationships shown in the accompanying drawings, are only for the convenience of describing the invention and simplifying the description, and do not indicate or imply that the device or element referred to must have a specific orientation, or be constructed and operated in a specific orientation, and therefore should not be construed as a limitation of the invention. Furthermore, the terms "first" and "second" are used for descriptive purposes only and should not be construed as indicating or implying relative importance or implicitly specifying the number of indicated technical features. Thus, a feature defined with "first" or "second" may explicitly or implicitly include one or more of that feature. In the description of this invention, "a plurality of" means two or more, unless otherwise explicitly specified.

[0035] In this invention, unless otherwise explicitly specified and limited, the terms "installation," "connection," "linking," and "fixing," etc., should be interpreted broadly. For example, they can refer to a fixed connection, a detachable connection, or an integral connection; they can refer to a mechanical connection or an electrical connection; they can refer to a direct connection or an indirect connection through an intermediate medium; and they can refer to the internal connection of two components. Those skilled in the art can understand the specific meaning of the above terms in this invention according to the specific circumstances.

[0036] like Figure 1 and Figure 2 As shown, the cooperative swirling jet device for a rotary engine according to the present invention includes a head cover body 1, an outer flow channel housing 2, a piezoelectric needle-shaped turbine mechanism 3, a solenoid valve 4, and a control system (not shown in the figure). All components are arranged coaxially along the central axis.

[0037] The outer flow channel housing 2 is fixed below the head cover body 1. The piezoelectric needle-shaped turbine 3 is supported in the inner cavity of the outer flow channel housing 2 by bearings 6. An annular pressure-stabilizing cavity is formed between the outer wall of the piezoelectric needle-shaped turbine 3 and the inner wall of the outer flow channel housing 2. At least two radial air inlets 7 are symmetrically provided on the side wall of the outer flow channel housing 2. The radial air inlets 7 are connected to the annular pressure-stabilizing cavity, and their internal structure eliminates the complex bends found in traditional designs. The radial air inlets 7 are connected to the first fuel supply system, enabling the first fuel to enter the annular pressure-stabilizing cavity directly with extremely low friction resistance, utilizing the volumetric effect of the cavity to buffer pressure pulsations and achieve stable flow.

[0038] The piezoelectric needle turbine 3 is a piezoelectrically driven needle valve, comprising a drive unit and a hollow valve body. The hollow portion of the hollow valve body forms an inner flow channel for introducing the second fuel. An external spiral guide groove 9 is machined on the outer wall of the valve body, with a spiral angle designed to be 45°~60°. When the first fuel flows through the annular pressure regulating chamber, it is guided by the external spiral guide groove 9, generating a swirling flow in a first direction. In this embodiment, the first direction is clockwise, but it can also be counterclockwise. An internal spiral guide groove 10 is machined on the inner flow channel wall, with a spiral angle also designed to be 45°~60°, but the direction of rotation is opposite to that of the external spiral guide groove 9. When the second fuel flows through the inner flow channel, a second swirling flow opposite to the first direction is generated. An axial air inlet 6 is provided on the head cover body 1, through which the second fuel is introduced. The axial air inlet 6 is connected to the inner flow channel of the hollow valve body.

[0039] The electromagnetic valve 4 is located at the bottom outlet of the outer flow channel housing 2, and its valve core controls the opening and closing of the main nozzle. A pressure regulating port 8 is provided on the side of the annular pressure regulating chamber. This pressure regulating port 8 is selectively connected to a common chamber with different pressures on the engine via a switching valve. The outflow direction of the pressure regulating port 8 forms an angle of 30° to 60° with the central axis of the device. An annular gap is left between the main nozzle of the outer flow channel housing 2 and the valve body outlet of the piezoelectric needle turbine 3; this gap constitutes a premixing chamber for accommodating and mixing the two fuel streams. This invention achieves dual counter-current swirling: the outer fluid rotates clockwise, and the inner fluid rotates counter-clockwise. When the two fluids converge in the premixing chamber, their tangential velocity components are in opposite directions, maximizing their relative velocity and thus producing a strong shearing and crushing effect.

[0040] In traditional co-current or direct-flow jetting, droplet breakup primarily depends on the gas-liquid velocity difference. However, in the dual-reverse swirling structure of this invention, the relative tangential velocities of the inner and outer fluids at the interface are significantly increased. According to atomization theory, the Sauter mean diameter (SMD) is negatively correlated with the Weber number (SMD & Weber number). -0.5Therefore, this design can obtain finer atomized particles. Secondly, regarding the control of swirl intensity: To ensure that the spray forms sufficient stratification under centrifugal force, the swirl number (S) of the outer channel must be kept within a certain range. The geometric swirl number can be estimated by the following formula:

[0041]

[0042] in Where n is the outlet radius of the vortex channel, and n is the number of spiral channels. Let be the cross-sectional area of ​​a single slot. Where is the nozzle exit radius. The α angle is the helix angle. This invention optimizes the α angle (recommended range 45°-60°) to ensure that S>0.6 under high load conditions, forming a strong vortex to generate a central recirculation zone (CTR), which contributes to flame stability.

[0043] The control system controls the piezoelectric needle turbine 3, the solenoid valve 4, the first fuel supply system, the second fuel supply system, and the switching valve to achieve premixed mode control and stratified mode control.

[0044] like Figure 3 As shown, when the engine is in a cold start or low load condition, the control system activates the premixed mode.

[0045] The piezoelectric needle-shaped turbine 3 is controlled to rotate at a relatively high first preset speed.

[0046] The supply of the first and second fuels is controlled so that they enter the premixing chamber through the annular pressure stabilizing chamber (which generates a first-direction swirling flow) and the inner flow channel (which generates a second-direction swirling flow), respectively. The two high-speed, counter-rotating fluids collide and shear violently in the premixing chamber, achieving thorough microscopic homogeneous mixing.

[0047] During the premixing process, the control system controls the switching valve to connect the pressure regulating vent 8 to a common chamber (such as the intake manifold) with a pressure lower than that of the current annular pressure regulating chamber. At this time, the pressure regulating vent 8 mainly serves to release some of the high pressure in the premixing chamber and stabilize the internal flow field.

[0048] After mixing is complete, the control system opens solenoid valve 4, and the uniform premixed gas is ejected at high speed through the main nozzle to form a homogeneous premixed spray that is easy to ignite.

[0049] In premixing mode, a strong shearing action is required to achieve thorough micro-mixing of the fuel in a very short time. At this time, the piezoelectric needle turbine 3 is controlled to rotate at a first preset speed, which ranges from 1500 rpm to 6000 rpm. Within this speed range, combined with the external spiral guide channel 9 and the internal spiral guide channel 10, sufficient tangential velocity is ensured for the fuel flowing through the inner and outer channels, allowing the two opposing swirling streams to have maximum relative velocity upon convergence, thereby achieving efficient droplet breakage and homogeneous premixing. The preferred first preset speed in premixing mode is 2000-4000 rpm.

[0050] like Figure 4 As shown, when the engine is under high load, the control system switches to a layered mode:

[0051] Control the piezoelectric needle turbine 3 to stop rotating or maintain it at a second preset speed.

[0052] The control system opens solenoid valve 4 and maintains the supply of the first and second fuels.

[0053] At this point, the two fuel streams are guided only by the fixed spiral grooves within their own flow channels, carrying opposite swirling angular momentum as they are ejected. Due to the lack of forced shear mixing within the premixing chamber, and thanks to the difference in centrifugal force of the swirling flow, the two naturally form a stratified structure with an inner layer rich in fuel and an outer layer lean in fuel during the ejection process.

[0054] The control system controls the switching valve to connect the pressure regulating port 8 to a common chamber (such as a booster air chamber) with a pressure higher than the current annular pressure regulating chamber pressure. High-pressure gas is then ejected from the pressure regulating port 8 at a specific angle. This lateral airflow balances the pressure difference inside and outside the nozzle, preventing combustion chamber backflow; it also constrains and shapes the ejected stratified fuel jet, forming and maintaining a flat, fan-shaped spray pattern that matches the elongated combustion chamber of the rotary engine. To ensure spray stability, the spiral rise angle is optimized to ensure the swirl number S of the airflow at the annular pressure regulating chamber outlet is greater than 0.6, which helps to form a stable recirculation zone at the spray center.

[0055] In stratified mode, to maintain the fuel concentration stratification structure using centrifugal force and aerodynamic effects, over-mixing must be avoided. At this time, the piezoelectric needle turbine 3 is controlled to be stationary or rotated at a second preset speed significantly lower than in premixed mode, ranging from 0 rpm to 1000 rpm. In this low-speed or stationary state, the fuel flow still acquires initial, opposite-direction swirling angular momentum after passing through the spiral guide channel, but it is insufficient to achieve complete mixing before ejection. When ejected from the main nozzle, it naturally forms and maintains a flat, fan-shaped stratified spray structure with an inner rich layer and an outer lean layer, primarily relying on its own swirling centrifugal force and external aerodynamic shaping effect, perfectly adapting to the shape of the rotary engine combustion chamber.

[0056] The control system precisely controls the rotational speed of the piezoelectric needle turbine 3 in different modes by adjusting the frequency and amplitude of the excitation signal that drives the piezoelectric ceramic.

[0057] This invention sets the operating mode according to the unique operating conditions of the rotary engine: during cold start and low load, a premixed mode is adopted to achieve fuel homogenization inside the device, which fundamentally ensures the reliability of ignition and the stability of initial combustion; during high load, a stratified mode is adopted, combined with aerodynamic shaping, to form a flat fan-shaped stratified spray that matches the shape of the combustion chamber. This is intended to optimize the flame propagation path, suppress knocking tendency, and use auxiliary airflow to resist the interference of high-speed scavenging, thereby achieving efficient and stable combustion at high power.

[0058] It should be understood that although this specification is described according to various embodiments, not every embodiment contains only one independent technical solution. This way of describing the specification is only for clarity. Those skilled in the art should regard the specification as a whole. The technical solutions in each embodiment can also be appropriately combined to form other implementation methods that can be understood by those skilled in the art.

[0059] The detailed descriptions listed above are merely specific illustrations of feasible embodiments of the present invention and are not intended to limit the scope of protection of the present invention. All equivalent embodiments or modifications made without departing from the spirit of the present invention should be included within the scope of protection of the present invention.

Claims

1. A cooperative swirling injection device for a rotary engine, characterized in that, It includes a head cover body (1), an outer flow channel shell (2), a piezoelectric needle turbine mechanism (3), and a solenoid valve (4); The outer flow channel housing (2) is located below the head cover body (1), and the piezoelectric needle-shaped turbine (3) is supported in the inner cavity of the outer flow channel housing (2). The outer flow channel housing (2) and the piezoelectric needle-shaped turbine (3) form an annular pressure stabilizing cavity. At least two radial air inlets (7) are provided on the side wall of the outer flow channel housing (2), and the radial air inlets (7) are connected to the annular pressure stabilizing cavity formed inside the outer flow channel housing (2). The outer wall of the piezoelectric needle-shaped turbine (3) is provided with an external spiral guide groove (9) for guiding the flow through the annular cavity. The first fuel in the annular pressure stabilizing chamber generates a swirling flow in the first direction; the piezoelectric needle turbine (3) is provided with an inner flow channel for inputting the second fuel; the inner wall of the inner flow channel is provided with an internal spiral guide groove (10) for guiding the second fuel flowing through the inner flow channel to generate a swirling flow in the second direction opposite to the first direction; the side of the annular pressure stabilizing chamber is provided with a pressure regulating vent (8), and the pressure regulating vent (8) is connected to a common chamber with different pressures through a switching valve; the electromagnetic valve (4) is located at the main nozzle at the outlet of the outer flow channel housing (2).

2. The cooperative swirling injection device for a rotary engine according to claim 1, characterized in that, The piezoelectric needle turbine (3) is a piezoelectrically driven needle valve, including a drive unit and a hollow valve body. The hollow valve body is supported in the inner cavity of the outer flow channel housing (2). The outer wall of the hollow valve body is provided with an external spiral guide groove (9), and the hollow hole of the hollow valve body is provided with an internal spiral guide groove (10). The drive unit is used to drive the hollow valve body to rotate.

3. The cooperative swirling jet device for a rotary engine according to claim 1, characterized in that, The spiral angles of the external spiral guide groove (9) and the internal spiral guide groove (10) are both 45°~60°.

4. The cooperative swirling injection device for a rotary engine according to claim 1, characterized in that, The outflow direction of the pressure regulating vent (8) forms an angle of 30° to 60° with the central axis of the outer flow channel shell (2).

5. The cooperative swirling injection device for a rotary engine according to claim 1, characterized in that, The swirl number S of the first directional swirling flow formed in the annular pressure-stabilizing cavity is greater than 0.

6.

6. The cooperative swirling jet device for a rotary engine according to claim 2, characterized in that, A gap is provided between the main nozzle of the outer flow channel housing (2) and the outlet of the hollow valve body. The gap forms a premixing chamber for premixing the second fuel and the second fuel.

7. The cooperative swirling jet device for a rotary engine according to claim 1, characterized in that, It also includes a control system, which controls the piezoelectric needle turbine mechanism (3), the solenoid valve (4), the first fuel supply system, the second fuel supply system and the switching valve to achieve premixed mode control and stratified mode control.

8. The cooperative swirling jet device for a rotary engine according to claim 1, characterized in that, The control system controls the rotation of the piezoelectric needle turbine (3) and simultaneously controls the fuel supply of the first fuel supply system and the second fuel supply system, so that they form swirling flows with opposite rotation directions through the annular pressure stabilizing chamber and the inner flow channel and mix in the premixing chamber; when the mixing is completed, the control system controls the opening of the solenoid valve (4) to spray out the mixed fuel, thereby realizing the premixing mode control; in the premixing mode, the control system controls the switching valve to connect the pressure regulating vent (8) with the common chamber with a pressure lower than that of the annular pressure stabilizing chamber.

9. The cooperative swirling jet device for a rotary engine according to claim 1, characterized in that, The control system controls the piezoelectric needle turbine (3) to stop rotating or maintain a preset low-speed rotation state, controls the fuel supply of the first fuel supply system and the second fuel supply system, and controls the opening of the solenoid valve (4) so ​​that the first fuel and the second fuel with opposite swirling directions form a flat fan-shaped jet with stratified concentration during the injection process; in the stratified mode, the control system controls the switching valve to connect the pressure regulating vent (8) with the common chamber with a pressure greater than that of the annular pressure stabilizing chamber.

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