Fuel supply flow path, injection equipment, supply system, engine, aircraft

Abstract

The invention discloses a fuel supply flow channel, an injection device, a supply system, an engine, and an aircraft, and relates to a fuel supply flow channel, an injection device, a supply system, a continuous rotating detonation engine, and an aircraft. The technical problem to be solved is that the diffusion, fragmentation, atomization degree, and circumferential distribution uniformity of the liquid-phase fuel are poor. The fuel supply flow channel may have a main channel, a branch channel assembly, a flow channel temperature control assembly, and a channel assembly. Each branch channel is evenly distributed circumferentially and forms an equal obtuse angle with the main channel. Each channel sub-assembly of any group of channel assemblies includes a channel antechamber and two or more channel outlets. More than or equal to 12 channel outlets are evenly distributed circumferentially. The flow channel temperature control assembly includes a heating element, a temperature sensing element, and a temperature control element. The heating element transfers heat to the outer wall of the channel assembly. The technical effect of improving the mixing uniformity and circumferential uniformity of the combustible mixture is achieved by adopting the technical means of arranging a large number of preheating flow channels and nozzles evenly distributed circumferentially.

Description

Technical Field

[0001] The present invention relates to a fuel supply flow channel, a fuel injection device, a fuel supply system, a continuously rotating detonation engine, and an aircraft using the continuously rotating detonation engine. Background Art

[0002] The most relevant comparative documents to the present invention are: Document 1: A rotating detonation engine experimental device, Chinese invention patent, application number 201510055761.1; Document 2: Bykovskii, FA, Zhdan, SA & Vedernikov, EF Continuous Detonation of the Liquid Kerosene—Air Mixture with Addition of Hydrogen or Syngas[J], Combustion, Explosion, and Shock Waves, 2019, 55(5): 589-598; Document 3: Jan Kindracki, Experimental research on rotating detonation in liquid fuel-gaseous air mixtures[J], Aerospace Science and Technology, 2015, 43: 445-453. In the prior art, the primary goal is to improve the mixing uniformity and circumferential uniformity of the combustible mixture. The main technical feature is to arrange four to eight cylindrical fuel channels circumferentially on the outer wall of a cylindrical combustion chamber, relying on the high-speed flow of oxidant to collide with the fuel at the outlet of each cylindrical fuel channel. The main effect is that the limited area near the impact point of the fuel and oxidant can form localized fuel diffusion and localized mixing with the oxidant. In the process of realizing the present invention, the inventors discovered that the prior art has at least the following problems: when using liquid-phase fuel, that is, the fuel exists in liquid form upstream of the channel outlet, the diffusion, fragmentation, and atomization of the fuel downstream of the channel outlet are poor, and the circumferential distribution uniformity of the fuel is poor. Summary of the Invention

[0003] The technical problem to be solved by the present invention is that the diffusion, fragmentation, atomization degree and circumferential distribution uniformity of liquid fuel are poor.

[0004] In order to solve the above technical problems, the specific technical solutions adopted by the present invention are as follows.

[0005] The fuel supply flow channel involved in the first aspect of the present invention may have a main channel, a branch channel assembly, a flow channel temperature control assembly and at least one group of channel assemblies. The branch channel assembly includes two or more branches. The structure of all branches is the same. The flow cross-sectional area of ​​each branch channel is smaller than the flow cross-sectional area of ​​the main channel. The flow direction is from the main channel to the branch channel. All branches are evenly distributed circumferentially. The center lines of all branches converge at one point and this intersection is located on the center line of the main channel. The center line of any branch channel along the flow direction forms an obtuse angle with the center line of the main channel. The obtuse angles formed by the center lines of all branches and the center line of the main channel are equal.

[0006] Each channel assembly includes two or more channel sub-components. The structures of the channel sub-components in each channel assembly are identical. The number of all branch channels is equal to and corresponds to the number of each channel sub-component in each channel assembly. Each channel sub-component includes a channel antechamber and two or more channel outlets. The number of channel outlets in each channel assembly is greater than or equal to 12. Each branch channel and its corresponding channel sub-component form a high-pressure seal using a detachable connector, allowing fluid flow between the branch channel and the channel antechamber. Each channel outlet of each channel sub-component separately forms fluid flow with the channel antechamber. The structures of the channel outlets in each channel assembly are identical. The shape of each channel outlet in each channel assembly is an axisymmetric hole. The channel outlets in each channel assembly are evenly distributed circumferentially. The axes of the channel outlets in each channel assembly intersect at a single point. The cross-sectional flow area of ​​each channel outlet is less than or equal to 0.1 square millimeters. The axis of any channel outlet along the flow direction forms an obtuse angle with the center line of the main channel. The obtuse angles formed by the axes of the channel outlets of any group of channel components and the center line of the main channel are equal.

[0007] The flow channel temperature control assembly includes a heating element, a temperature sensing element, and a temperature control element. The heating element and temperature control element are connected by a signal data cable. The temperature sensing element and temperature control element are also connected by a signal data cable. The heating element and the outer wall of the branch channel assembly are connected by direct contact heat conduction or indirect heat transfer. The temperature control element receives data from the temperature sensing element and controls the input power and duty cycle of the heating element. When electrical energy is input, the heating element generates heat and changes its surface temperature. The surface temperature of the heating element during operation can be adjusted between 30 and 1200 degrees Celsius.

[0008] A fuel injection device according to a second aspect of the present invention may include a fuel flow on / off actuator and the fuel supply passage of the first aspect. The fuel flow on / off actuator communicates with a main passage. The fuel flow on / off actuator is upstream of the main passage. The fuel flow on / off actuator and the main passage form a high hydraulic seal.

[0009] The fuel supply system according to the third aspect of the present invention may include a fuel storage unit, a fuel pressurizing unit, and a fuel injection unit. The fuel storage unit and the fuel pressurizing unit are connected by a pipe, and the fuel pressurizing unit and the fuel injection unit are connected by a pipe. The fuel injection unit is the fuel injection device according to the second aspect.

[0010] The continuous rotating detonation engine according to the fourth aspect of the present invention may include a fuel supply component, a combustion chamber component, and an initiator component. The fuel supply component and the combustion chamber component are connected by a pipeline, and the initiator component extends into the combustion chamber component through a hole in the outer wall of the combustion chamber component's housing. The fuel supply component is the fuel supply system of the third aspect described above. Connectors are used to connect, secure, and provide a high-pressure seal between the fuel supply flow channel and the combustion chamber inner wall of the combustion chamber component.

[0011] The aircraft according to the fifth aspect of the present invention may include an engine component, a control component, and a payload component. The engine component and the control component are connected by a communication data line. The payload component includes the aircraft shell and a payload. The payload, control component, and engine component are sequentially arranged at the top, center, and bottom of the aircraft shell. The engine component is the continuously rotating detonation engine according to the fourth aspect.

[0012] One of the above technical solutions has the following advantages or beneficial effects:

[0013] The fuel supply flow channel involved in the first aspect of the present invention utilizes a large number of preheating flow channels and nozzles uniformly distributed around the circumference. This overcomes the technical issues of "poor diffusion, fragmentation, atomization, and circumferential distribution uniformity of liquid fuel," thereby achieving the technical effect of improving the mixing uniformity and circumferential uniformity of the combustible mixture. Specifically, this effect can be quantified by improving the Sauter mean diameter of liquid aviation fuel droplets under steady-state flow conditions of 60 MPa pressure differential to 45 microns, and improving circumferential uniformity by more than 1.5 times. Furthermore, the ease of disassembly and replacement of the channel assembly with the same or different channel outlet structure or size allows for greater performance adjustment flexibility.

[0014] The fuel injection device according to the second aspect of the present invention includes the fuel supply flow path of the first aspect, thereby achieving the technical advantages of the fuel supply flow path. Furthermore, the Sauter mean diameter of liquid aviation fuel droplets under single injection flow conditions at a pressure difference of 180 MPa can be improved to 25 microns.

[0015] The fuel supply system according to the third aspect of the present invention includes the fuel supply flow path of the first aspect, thereby achieving the technical advantages of the fuel supply flow path. Furthermore, the Sauter mean diameter of liquid aviation fuel droplets can be improved to 25 microns under single or multiple injection or steady-state flow conditions at a pressure differential of 180 MPa.

[0016] The continuous rotating detonation engine according to the fourth aspect of the present invention comprises the fuel supply passage of the first aspect and has the technical advantages of a fuel supply passage, wherein improved uniformity of the combustible mixture improves combustion efficiency, and improved circumferential uniformity of the combustible mixture improves combustion stability. Furthermore, the engine overcomes the disadvantage of the prior art of requiring gaseous fuel to assist in igniting liquid fuel, achieving the technical advantage of being able to generate continuous rotating detonation combustion using only liquid fuel.

[0017] The aircraft according to the fifth aspect of the present invention comprises the fuel supply flow passage of the first aspect, thereby achieving the technical advantages of the fuel supply flow passage. Improved mixing uniformity of the combustible mixture can increase thrust and Mach number, and improved circumferential uniformity of the combustible mixture can enhance flight stability. Furthermore, the aircraft overcomes the complexity of prior art aircraft employing liquid-fuel continuous rotating detonation engines requiring auxiliary gaseous fuel systems, thereby achieving the technical advantages of improved operational reliability and volumetric energy density. BRIEF DESCRIPTION OF THE DRAWINGS

[0018] Figure 1 It is a schematic diagram showing the relationship between several embodiments of the present invention.

[0019] Figure 2A 1 is a schematic structural diagram (section A) of an embodiment of a fuel supply flow channel according to the present invention.

[0020] Figure 2B It is a structural schematic diagram of an embodiment of a fuel supply channel according to the present invention (partial details of section A).

[0021] Figure 3A It is a structural schematic diagram (section A) of an embodiment of a channel sub-component of a fuel supply channel according to the present invention.

[0022] Figure 3B It is a structural schematic diagram of an embodiment of a channel sub-component of a fuel supply channel according to the present invention (section B perpendicular to section A).

[0023] Figure 4 It is an assembly diagram of an embodiment of a fuel supply channel component according to the present invention.

[0024] Figure 5 1 is a schematic diagram of a sealing structure of an embodiment of a fuel injection device according to the present invention (section A).

[0025] Explanation of symbols

[0026] 100 fuel supply flow channel

[0027] 120 Trunk Road

[0028] 130 branch channel components

[0029] 132 branches

[0030] 150 channel sub-components

[0031] 152 channel front room

[0032] 154 channel exit

[0033] 172 screw with A

[0034] 182 heating element

[0035] 184 cylindrical heat conducting parts

[0036] 190 fuel flow on-off actuator

[0037] 200 fuel injection equipment

[0038] 210 inner cone-spherical crown seal fit A

[0039] 300 fuel supply system

[0040] 320 fuel storage components

[0041] 340 fuel boost components

[0042] 360 fuel injection components

[0043] 400 continuous rotating detonation engine

[0044] 420 fuel supply components

[0045] 440 combustion chamber components

[0046] 442 Inner wall of combustion chamber

[0047] 444 screw fit B

[0048] 446 Metal Pad B

[0049] 460 detonating components

[0050] 500 aircraft

[0051] 520 engine parts

[0052] 540 control components

[0053] 560 load components DETAILED DESCRIPTION

[0054] like Figure 1 As shown, the relationship between the embodiments of several aspects of the present invention is illustrated, and the embodiments of several aspects of the present invention are arranged in series.

[0055] like Figure 2A and relevant local details Figure 2B As shown, an embodiment of the fuel supply flow channel 100 involved in the first aspect of the present invention may include a main channel 120, a branch channel assembly 130, a flow channel temperature control assembly and at least one set of channel assemblies. The flow cross-sectional area of ​​the main channel 120 may be less than or equal to 9 square millimeters, and the flow cross-sectional shape of the main channel 120 may be circular. The branch channel assembly 130 includes two or more branch channels 132. Further, the branch channel assembly 130 may include more than or equal to 12 branch channels 132. The flow cross-sectional area of ​​each branch channel 132 may be less than or equal to 4 square millimeters. The flow cross-sectional shape of each branch channel 132 may be circular. The structure of all branch channels 132 is the same. The flow cross-sectional area of ​​each branch channel 132 is smaller than the flow cross-sectional area of ​​the main channel 120. The flow direction is from the main channel 120 to the branch channel 132. All branches 132 are evenly distributed circumferentially. The centerlines of all branch channels 132 intersect at a single point, and this intersection is located on the centerline of the main channel 120. Along the flow direction, the centerline of any branch channel 132 forms an obtuse angle with the centerline of the main channel 120. Furthermore, along the flow direction, the centerline of any branch channel 132 may form an obtuse angle greater than or equal to 120 degrees with the centerline of the main channel 120. The obtuse angles formed by the centerlines of all branch channels 132 and the centerline of the main channel 120 are equal.

[0056] Any group of channel components includes two or more channel sub-components 150. The structure of each channel sub-component 150 in any group of channel components is the same. The number of all branches 132 is equal to the number of each channel sub-component 150 in any group and corresponds one to one. Figure 3A and the relevant vertical sections Figure 3B As shown, each channel sub-assembly 150 includes a channel front chamber 152 and two or more channel outlets 154. Further, each channel sub-assembly 150 may include more than or equal to 4 channel outlets 154. The number of each channel outlet 154 of any group of channel components is more than or equal to 12. Figure 4As shown, the number of channel outlets 154 in any channel assembly group can be greater than or equal to 48. Each channel antechamber 152 can be shaped as an arcuate flat groove, and the volume of each channel antechamber 152 can be less than or equal to 40 cubic millimeters. A detachable connector forms a high-pressure seal between each branch channel 132 and the corresponding channel sub-assembly 150, allowing flow between the branch channel 132 and the channel antechamber 152. One implementation of the detachable connector can be a screw connection A172, and one implementation of the high-pressure seal can be a flat seal. Each channel outlet 154 in any channel sub-assembly 150 is in flow with the channel antechamber 152. The structure of each channel outlet 154 in any channel assembly group is the same. Each channel outlet 154 in any channel assembly group is an axisymmetric hole. Furthermore, the axisymmetric hole can be any of a cylindrical hole, a gradually converging hole, a gradually expanding hole, a hole that first gradually converges and then gradually expands, or a hole that first gradually expands and then gradually converges. The channel outlets 154 of any group of channel assemblies are uniformly arranged in the circumferential direction. The axes of the channel outlets 154 of any group of channel assemblies converge at a point. The flow cross-sectional area of ​​each channel outlet 154 is less than or equal to 0.1 square millimeters. Further, the flow cross-sectional area of ​​each channel outlet 154 may be less than or equal to 0.01 square millimeters. The flow cross-sectional shape of each channel outlet 154 may be circular. The axis of any channel outlet 154 along the flow direction forms an obtuse angle with the center line of the main channel 120. Further, the axis of any channel outlet 154 along the flow direction may form an obtuse angle greater than or equal to 120 degrees with the center line of the main channel 120. The obtuse angles formed by the axes of the channel outlets 154 of any group of channel assemblies and the center line of the main channel 120 are equal.

[0057] The flow channel temperature control assembly includes a heating element 182, a temperature sensing element, and a temperature control element. The heating element 182 and the temperature control element are connected by a signal data line. The temperature sensing element and the temperature control element are connected by a signal data line. The heating element 182 and the outer wall surface of the branch channel assembly 130 are directly contacted by heat conduction or indirect heat transfer. One implementation method of direct contact heat conduction or indirect heat transfer can be to install a cylindrical heat conductor 184. The inner surface of the cylindrical heat conductor 184 can directly contact the outer wall surface of the heating element 182 or leave a gap of less than 0.1 mm. The outer surface of the cylindrical heat conductor 184 can directly contact the inner wall 442 of the combustion chamber. The end surface of the cylindrical heat conductor 184 can directly contact the outer wall surface of the branch channel assembly 130. The end surface of the heating element 182 can directly contact the outer wall surface of the branch channel assembly 130. The temperature control element receives data from the temperature sensing element. The temperature control element controls the input power and duty cycle of the heating element 182. When input with electrical energy, the heating element 182 generates heat and experiences changes in surface temperature. The surface temperature of the heating element 182 during operation can be adjusted within a range of 30 to 1200 degrees Celsius. The temperature sensing element can be integrated within the heating element 182. Furthermore, the temperature sensing element can be integrated into the end surface of the heating element 182, placing the temperature sensing element closer to the outer wall of the branch assembly 130.

[0058] The trunk channel 120, the branch channel assembly 130 and the channel assembly may all have a structural strength and high hydraulic sealing performance to withstand an internal hydraulic pressure greater than or equal to 30 MPa. Further, the trunk channel 120, the branch channel assembly 130 and the channel assembly may all have a structural strength and high hydraulic sealing performance to withstand an internal hydraulic pressure greater than or equal to 180 MPa.

[0059] The technical effect achieved by this embodiment is that, by employing a large number of preheating channels and nozzles uniformly distributed around the circumference, the technical issues of "poor diffusion, fragmentation, atomization, and circumferential distribution uniformity of liquid fuel" are overcome, thereby improving the mixing uniformity and circumferential uniformity of the combustible mixture. Specifically, this effect is quantified by the Sauter mean diameter of liquid aviation fuel droplets under steady-state flow conditions of 60 MPa pressure differential, which can be improved to 45 microns and circumferential uniformity by more than 1.5 times. Furthermore, the ease of disassembly and replacement of the channel assembly with the same or different channel outlet 154 configuration or size allows for greater performance adjustment flexibility.

[0060] An embodiment of the fuel injection device 200 involved in the second aspect of the present invention may include a fuel flow on-off actuator 190 and an embodiment of the fuel supply flow channel 100 of the first aspect. An implementation means of the fuel flow on-off actuator 190 may be a straight-through electromagnetic needle valve commonly used in the hydraulic industry. The fuel flow on-off actuator 190 is connected to the main channel 120. The fuel flow on-off actuator 190 is upstream of the main channel 120. The fuel flow on-off actuator 190 and the main channel 120 have a high hydraulic sealing fit, such as Figure 5 As shown, one implementation of this high-hydraulic sealing fit can be an inner cone-spherical crown seal fit A210. One implementation of the required compression force for this seal fit can be the axial force provided by the threads. This embodiment of the fuel injection device 200 incorporates the fuel supply flow channel 100 and thus achieves the technical benefits of the embodiment of the fuel supply flow channel 100. Furthermore, the Sauter mean diameter of liquid aviation fuel droplets under single injection flow conditions of 180 MPa pressure differential can be improved to 25 microns.

[0061] An embodiment of a fuel supply system 300 according to the third aspect of the present invention may include a fuel storage component 320, a fuel pressurizing component 340, and a fuel injection component 360. Fuel storage component 320 and fuel pressurizing component 340 are connected by a pipeline, and fuel pressurizing component 340 and fuel injection component 360 are connected by a pipeline. This pipeline may be a high-pressure oil pipe assembly commonly used in the hydraulic industry. The implementation of such a common high-pressure oil pipe assembly may refer to the national machinery industry standard JB / T12036-2015. Fuel injection component 360 is an embodiment of the fuel injection device 200 according to the second aspect. This embodiment of the fuel supply system 300 includes the fuel supply flow channel 100 according to the first aspect, and thus has the technical effects of the fuel supply flow channel 100 embodiment. Furthermore, the Sauter mean diameter of liquid aviation fuel droplets can be improved to 25 microns under single or multiple injection or steady-state flow conditions with a pressure differential of 180 MPa.

[0062] An embodiment of the continuous rotating detonation engine 400 involved in the fourth aspect of the present invention may include a fuel supply component 420, a combustion chamber component 440, and an ignition component 460. The fuel supply component 420 and the combustion chamber component 440 are connected by a pipeline, which can be a high-pressure oil pipe assembly commonly used in the hydraulic industry. The ignition component 460 extends into the interior of the combustion chamber component 440 through a hole in the outer wall of the shell of the combustion chamber component 440. Among them, the fuel supply component 420 is an embodiment of the fuel supply system 300 of the third aspect mentioned above. The fuel supply flow channel 100 and the combustion chamber inner wall 442 of the combustion chamber component 440 are connected, fastened and sealed with high pressure using a connector. One implementation method of the connector can be a screw connection B444, and one implementation method of the high-pressure seal can be a flat seal using a metal gasket B446. This embodiment of the continuous rotating detonation engine 400 includes the fuel supply passage 100 embodiment of the first aspect described above and achieves the technical effects of the fuel supply passage 100 embodiment. Improved uniformity of the combustible mixture enhances combustion efficiency, and improved circumferential uniformity enhances combustion stability. Furthermore, it overcomes the drawback of the prior art, which requires the use of gaseous fuel to assist in igniting liquid fuel, achieving the technical effect of generating continuous rotating detonation combustion using only liquid fuel.

[0063] An embodiment of an aircraft 500 according to the fifth aspect of the present invention may include an engine component 520, a control component 540, and a payload component 560. The engine component 520 and the control component 540 are connected by a communication data line. The payload component 560 includes an aircraft shell and a filler. The filler, the control component 540, and the engine component 520 are sequentially arranged at the upper, middle, and lower positions within the aircraft shell. The engine component 520 is an embodiment of the continuous rotating detonation engine 400 according to the fourth aspect. This embodiment of the aircraft 500 includes the fuel supply channel 100 according to the first aspect, thus achieving the technical advantages of the fuel supply channel 100 embodiment. Improved mixing uniformity of the combustible mixture can increase thrust and Mach number, and improved circumferential uniformity of the combustible mixture can enhance flight stability. Furthermore, it overcomes the complexity of conventional aircraft using liquid-fueled continuous rotating detonation engines, which require auxiliary gaseous fuel systems, thereby achieving the technical advantages of improved operational reliability and volumetric energy density.

Claims

1. A fuel supply channel, characterized in that include: A main channel, a branch channel assembly, a flow channel temperature control assembly, and at least one group of channel assemblies; the branch channel assembly includes two or more branches, all of which have the same structure, each branch has a flow cross-sectional area smaller than the flow cross-sectional area of ​​the main channel, the flow direction is from the main channel to the branch channel, all of the branches are evenly distributed circumferentially, the centerlines of all of the branches intersect at a point and this intersection is located on the centerline of the main channel, along the flow direction, the centerline of any branch forms an obtuse angle with the centerline of the main channel, and the obtuse angles formed by the centerlines of all of the branches and the centerline of the main channel are equal; Any group of the channel components includes two or more channel sub-components, and the structures of the channel sub-components of any group of the channel components are the same. The number of all the branches is equal to and corresponds to the number of the channel sub-components of any group. Each of the channel sub-components includes a channel front chamber and two or more channel outlets. The number of all the channel outlets is greater than or equal to 12. Any of the branches and the corresponding channel sub-components is formed in the form of a detachable connector to form a high-pressure seal and to allow the branch to flow with the channel front chamber. Each channel outlet of any of the channel sub-components forms a flow channel with the channel front chamber. The structure of each of the duct outlets of any group of the duct components is the same, the shape of each of the duct outlets of any group of the duct components is an axisymmetric hole, the duct outlets of any group of the duct components are evenly arranged in the circumferential direction, the axes of the duct outlets of any group of the duct components intersect at a point, the flow cross-sectional area of ​​each of the duct outlets is less than or equal to 0.1 square millimeters, and along the flow direction, the axis of any of the duct outlets forms an obtuse angle with the center line of the main channel, and the obtuse angles formed by the axes of the duct outlets of any group of the duct components and the center line of the main channel are equal; The flow channel temperature control component includes a heating element, a temperature sensing element and a temperature control element. The heating element and the temperature control element are connected by a signal data line, and the temperature sensing element and the temperature control element are connected by a signal data line. The heating element and the outer wall surface of the branch channel component are directly contacted for heat conduction or indirectly for heat transfer. The temperature control element receives the data of the temperature sensing element. The temperature control element can control the input electrical energy power and input electrical energy duty cycle of the heating element. The heating element generates heat and the surface temperature changes when electrical energy is input. The surface temperature of the heating element when working can be adjusted within the range of 30 to 1200 degrees Celsius.

2. The fuel supply channel according to claim 1, characterized in that: The flow cross-sectional area of ​​the main channel is less than or equal to 9 square millimeters, and the flow cross-sectional shape of the main channel is circular.

3. The fuel supply channel according to claim 1, characterized in that: The branch channel assembly includes more than or equal to 12 branches, the flow cross-sectional area of ​​each branch channel is less than or equal to 4 square millimeters, and the flow cross-sectional shape of each branch channel is circular.

4. The fuel supply channel according to claim 1, characterized in that: Along the flow direction, the center line of any branch channel forms an obtuse angle greater than or equal to 120 degrees with the center line of the main channel.

5. The fuel supply channel according to claim 1, characterized in that: Each of the channel sub-components includes more than or equal to 4 channel outlets, and the total number of the channel outlets is more than or equal to 48. The shape of each channel front chamber is an arched flat groove, and the volume of each channel front chamber is less than or equal to 40 cubic millimeters.

6. The fuel supply channel according to claim 1, characterized in that: The axisymmetric hole can be any one of a cylindrical hole, a tapering hole, a gradually expanding hole, a hole that first gradually shrinks and then gradually expands, and a hole that first gradually expands and then gradually shrinks. The flow cross-sectional area of ​​each channel outlet is less than or equal to 0.01 square millimeters, and the flow cross-sectional shape of each channel outlet is circular. The axis of any channel outlet along the flow direction forms an obtuse angle greater than or equal to 120 degrees with the center line of the main channel. The main channel, the branch channel assembly and the channel assembly all have structural strength and high hydraulic sealing that can withstand internal hydraulic pressure greater than or equal to 30 MPa, and the temperature sensing element is integrated inside the heating element.

7. A fuel injection device, characterized in that: It is equipped with a fuel flow on-off actuator and the fuel supply flow channel as claimed in claim 1, the fuel flow on-off actuator is connected to the main channel, the fuel flow on-off actuator is upstream of the main channel, and the fuel flow on-off actuator and the main channel have a high hydraulic sealing fit with each other.

8. A fuel supply system comprising a fuel storage component, a fuel pressurizing component, and a fuel injection component, wherein the fuel storage component and the fuel pressurizing component are connected by a pipeline, and the fuel pressurizing component and the fuel injection component are connected by a pipeline, characterized in that: The fuel injection component is defined as the fuel injection device according to claim 7.

9. A continuous rotating detonation engine comprising a fuel supply component, a combustion chamber component, and an ignition component, wherein the fuel supply component and the combustion chamber component are connected by a pipeline, and the ignition component extends into the interior of the combustion chamber component through a hole in the outer wall of the combustion chamber component, characterized in that: The fuel supply component is defined as the fuel supply system according to claim 8, and the fuel supply flow channel and the combustion chamber inner wall of the combustion chamber component are connected, fastened and sealed under high pressure by a connecting piece.

10. An aircraft comprising an engine component, a control component, and a payload component, wherein the engine component and the control component are connected by a communication data line, the payload component comprises an aircraft shell and a filling, the filling, the control component, and the engine component are sequentially arranged at the upper, middle, and lower positions inside the aircraft shell, characterized in that: The engine component is defined as the continuously rotating detonation engine according to claim 9.

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