A fuel supply control system and control method for a jet propulsion device

Abstract

A kind of jet propulsion device fuel supply control system and control method, air combustion-supporting jet propulsion device fuel supply control device technical field, can solve the problems raised in the background: the existing jet propulsion engine when using, the vortex fan is pumped, the vortex fan is limited by the drive motor speed, when the speed reaches the limit, it cannot increase the air intake problem, and the existing fuel supply system when suddenly increasing air intake, it will lead to fuel supply shortage and cause engine surge problem. The steps are: the air is sucked into the combustion section by the air intake section through the energization of the compressor, the fuel enters the fuel cavity through the fuel inlet; the ignition device is energized to make the fuel burn, and is ejected along with the air flow through the tail jet section; the electric telescopic rod is energized to drive the baffle to rotate and increase the air intake; the fuel pump is started to send the fuel in the fuel cavity to another fuel pipe to increase the fuel supply.

Description

TECHNICAL FIELD

[0001] The present application belongs to the technical field of air-assisted jet propulsion device fuel supply control device, and particularly relates to a jet propulsion device fuel supply control system and a control method. BACKGROUND

[0002] With the development of science and technology, the performance requirements for jet propulsion engines are getting higher and higher. In the existing jet propulsion engines, the linkage control between various components plays a key role in the performance and efficiency of the engine. The principle is to draw gas into the body through a turbofan, and after pressurized combustion, high-temperature and high-pressure gas is obtained, which is ejected from the tail to produce reverse thrust.

[0003] The existing jet propulsion engines generally directly set the turbofan at the front end for air extraction during use, and then mix and burn after fuel supply in the combustion chamber. The above-mentioned mode is limited by the rotation speed of the driving motor, and when the rotation speed reaches the limit, the intake amount cannot be increased, and at the same time, the existing fuel supply system will cause insufficient fuel supply when the intake amount is suddenly increased, thereby causing engine surge. SUMMARY

[0004] The present application aims to solve the above-mentioned problems existing in the prior art, and provides a jet propulsion device fuel supply control system and a control method.

[0005] To achieve the above-mentioned purpose, the present application adopts the following technical solutions:

[0006] A jet propulsion device fuel supply control system, comprising: a shell, a protection assembly, a compressor, a control assembly, a combustion assembly and a supply assembly, the shell is internally fixed with the protection assembly, the compressor, the control assembly and the combustion assembly, the shell is fixed with the supply assembly at the upper end, and the control assembly is evenly arranged as a plurality of.

[0007] The shell is divided into an air inlet section, a pressurization section, a combustion section and a tail section from right to left, the air inlet section is provided with a plurality of impurity removal holes along the circumferential direction, and the pressurization section is provided with a plurality of air inlets along the circumferential direction.

[0008] The protection assembly comprises a fixed frame, a driving motor, a screw rod, a moving block, a support rod and a hinged rod, the fixed frame is fixed in the air inlet section through a support, the driving motor is fixed in the fixed frame, one end of the screw rod is rotatably connected to the air inlet section through a support, the other end of the screw rod is rotatably connected to the fixed frame and fixedly connected to the output shaft of the driving motor, the moving block is rotatably connected to the screw rod, one end of the support rod is rotatably connected to the fixed frame, one end of the hinged rod is rotatably connected to the moving block, and the other end of the hinged rod is rotatably connected to the support rod, the support rod is evenly arranged as a plurality of rods with the fixed frame as the center, the hinged rod is arranged as a plurality of rods, a waterproof cloth is fixed on each of the support rods, and the waterproof cloths are arranged in a circular shape.

[0009] Each of the control assemblies comprises an electric telescopic rod and a blocking plate, one end of the electric telescopic rod is rotatably connected to the outer wall of the pressurizing section, the other end of the electric telescopic rod is rotatably connected to the top surface of the blocking plate, the blocking plate is rotatably connected to the two side walls of the air inlet through a rotating shaft, the size of the blocking plate matches the size of the air inlet, and the bottom surface of the blocking plate is an arc surface.

[0010] The combustion assembly comprises a combustion chamber, an air inlet cone, a heat insulation tile, a fuel pipe and an ignition device, the combustion chamber is fixed in the combustion section, the combustion chamber is provided with the air inlet cone at one end, the heat insulation tile is detachably fixed in the combustion chamber, the fuel pipe is sealingly and fixedly inserted into the combustion section and the combustion chamber, the fuel pipe is symmetrically arranged as two, and the ignition device is fixed between the two fuel pipes.

[0011] The supply assembly comprises a fuel chamber, a fuel inlet and a fuel pump, the fuel chamber is fixed on the outer wall of the combustion section, the fuel inlet is arranged on the fuel chamber, and the fuel pump is fixed in the fuel chamber, one of the fuel pipes is fixedly communicated with the fuel chamber, and the other fuel pipe is sealingly and fixedly inserted into the fuel chamber and fixedly communicated with the discharge port of the fuel pump.

[0012] A control method of a fuel supply control system of a jet propulsion device, the method comprising the following steps:

[0013] S1, the air is sucked into the combustion section through the air inlet section by energizing the compressor, and the fuel is introduced into the fuel chamber through the fuel inlet;

[0014] S2, the fuel is combusted by energizing the ignition device, and the air flows through the tail section and is ejected;

[0015] S3, the electric telescopic rod is energized to drive the blocking plate to rotate and increase the air intake;

[0016] S4, the fuel pump is started to send the fuel in the fuel chamber into the other fuel pipe to increase the fuel supply.

[0017] Compared with the prior art, the present application has the beneficial effects of:

[0018] The present application provides a kind of jet propulsion device fuel supply control system, can solve the background problem proposed in: existing jet propulsion engine when using generally directly fan is set in the forefront and carries out suction, then after fuel supply mixing in combustion chamber, carries out combustion, the above-mentioned mode fan is limited by driving motor speed, when speed reaches limit, then cannot in the problem of increasing air intake, and existing fuel supply system when suddenly increasing air intake, it will lead to fuel supply shortage and then lead to engine surge problem.

[0019] The device can protect the compressor when the device is not in use by setting the protection assembly, preventing foreign matter from blowing into the shell interior and causing damage to the compressor fan and affecting the operation of the device. BRIEF DESCRIPTION OF DRAWINGS

[0020] Figure 1 It is the internal schematic diagram of the overall structure of the present application.

[0021] Figure 2 It is the structure schematic diagram of protection assembly;

[0022] Figure 3 It is the structure schematic diagram of control assembly;

[0023] Figure 4 It is the structure schematic diagram of combustion assembly;

[0024] Figure 5 It is the structure schematic diagram of supply assembly. DETAILED DESCRIPTION

[0025] The technical solutions in the present application will be described clearly and completely below in conjunction with the drawings in the embodiments of the present application. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. Based on the embodiments in the present application, all other embodiments obtained by those of ordinary skill in the art without creative labor fall within the scope of protection of the present application.

[0026] Please refer to Figures 1-5The application provides a technical scheme: a fuel supply control system of a jet propulsion device, which comprises a shell 1, a protection assembly 2, a compressor 3, a control assembly 4, a combustion assembly 5 and a supply assembly 6, the protection assembly 2, the compressor 3, the control assembly 4 and the combustion assembly 5 are fixedly arranged in the shell 1, the supply assembly 6 is fixedly arranged on the upper end of the shell 1, the control assembly 4 is arranged in multiple, the shell 1 is divided into an air inlet section 1-1, a pressurizing section 1-3, a combustion section 1-4 and a tail jet section 1-5 from right to left, the air inlet section 1-1 is uniformly arranged with a plurality of impurity removal holes 1-2 along the circumferential direction, the pressurizing section 1-3 is uniformly arranged with a plurality of air inlets 1-6 along the circumferential direction, the control assembly 4 comprises an electric telescopic rod 4-1 and a blocking plate 4-2, one end of the electric telescopic rod 4-1 is rotationally connected with the outer wall of the pressurizing section 1-3, the other end of the electric telescopic rod 4-1 is rotationally connected with the top surface of the blocking plate 4-2, the blocking plate 4-2 is rotationally connected with the two side walls of the air inlet 1-6 through a rotating shaft, the size of the blocking plate 4-2 is matched with the size of the air inlet 1-6, the bottom surface of the blocking plate 4-2 is an arc surface, the compressor 3 and the electric telescopic rod 4-1 are purchased from the prior art, and thus are not described in detail.

[0027] The protection assembly 2 comprises a fixed frame 2-1, a driving motor 2-2, a screw rod 2-3, a moving block 2-4, a supporting rod 2-5 and a hinged rod 2-6, the fixed frame 2-1 is fixedly arranged in the air inlet section 1-1 through a support one, the driving motor 2-2 is fixedly arranged in the fixed frame 2-1, one end of the screw rod 2-3 is rotationally connected with the air inlet section 1-1 through a support two, the other end of the screw rod 2-3 is rotationally connected with the output shaft of the driving motor 2-2 and penetrates through the fixed frame 2-1, the moving block 2-4 is screw-coupled with the screw rod 2-3, one end of the supporting rod 2-5 is rotationally connected with the fixed frame 2-1, one end of the hinged rod 2-6 is rotationally connected with the moving block 2-4, the other end of the hinged rod 2-6 is rotationally connected with the supporting rod 2-5, the supporting rod 2-5 is arranged in multiple and is uniformly arranged around the fixed frame 2-1, the hinged rod 2-6 is arranged in multiple, a waterproof cloth is fixedly arranged on the supporting rod 2-5, the waterproof cloths are circumferentially arranged, the driving motor 2-2 is purchased from the prior art, and thus is not described in detail.

[0028] The combustion assembly 5 comprises a combustion cavity 5-1, an air inlet cone 5-2, a heat insulation tile 5-3, a fuel pipe 5-4 and an ignition device 5-5, the combustion cavity 5-1 is fixedly arranged in the combustion section 1-4, the combustion cavity 5-1 is provided with the air inlet cone 5-2 at one end, the heat insulation tile 5-3 is detachably fixedly arranged in the combustion cavity 5-1, the fuel pipe 5-4 is sealingly and fixedly arranged in the combustion section 1-4 and penetrates into the combustion cavity 5-1, the fuel pipe 5-4 is arranged in two and symmetrically, the ignition device 5-5 is fixedly arranged between the two fuel pipes 5-4, the ignition device 5-5 is purchased from the prior art, and thus is not described in detail.

[0029] The fuel supply assembly 6 comprises a fuel cavity 6-1, a fuel inlet 6-2 and a fuel pump 6-3, the fuel cavity 6-1 is fixed on the outer wall of the combustion section 1-4, the fuel inlet 6-2 is arranged on the fuel cavity 6-1, and the fuel pump 6-3 is fixed inside the fuel cavity 6-1, one of the fuel pipes 5-4 is fixedly communicated with the fuel cavity 6-1, and the other fuel pipe 5-4 is sealingly fixed into the fuel cavity 6-1 and fixedly communicated with the fuel pump 6-3.

[0030] A control method of a jet propulsion device fuel supply control system, the method comprising the steps of:

[0031] S1, the compressor 3 is powered to suck air into the combustion section 1-4 through the air inlet section 1-1, and the fuel enters the fuel cavity 6-1 through the fuel inlet 6-2;

[0032] S2, the ignition device 5-5 is powered to make the fuel burn and be sprayed out along with the air flow through the tail jet section 1-5;

[0033] S3, the electric telescopic rod 4-1 is powered to drive the baffle 4-2 to rotate to increase the air intake;

[0034] S4, the fuel pump 6-3 is started to send the fuel in the fuel cavity 6-1 into the other fuel pipe 5-4 to increase the fuel supply.

[0035] The working principle of the present application is:

[0036] The device is in communication connection with the PLC controller, the fuel inlet 6-2 is fixedly communicated with the fuel tank, the electric telescopic rod 4-1, the driving motor 2-2, the compressor 3 and the ignition device 5-5 are connected with the storage battery;

[0037] The compressor 3 is powered to suck air into the pressurizing section 1-3 through the air inlet section 1-1, and then into the combustion section 1-4, the fuel in the fuel tank enters the fuel cavity 6-1 through the fuel inlet 6-2, when the fuel cavity 6-1 is filled, the fuel is sprayed in the combustion cavity 5-1 through one of the fuel pipes 5-4, when the air enters the air inlet cone 5-2 through the combustion cavity 5-1, the diameter of the combustion cavity 5-1 is reduced, the air entering through the air inlet cone 5-2 can further increase the flow rate, the air mixes with the sprayed fuel, the ignition device 5-5 is powered to make the fuel burn and be sprayed out along with the air flow through the tail jet section 1-5, the heat insulation tile 5-3 plays a protective role on the combustion cavity 5-1 and the combustion section 1-4, avoiding deformation or burning of the combustion cavity 5-1 and the combustion section 1-4;

[0038] When the compressor 3 reaches the limit of the rotation speed, the electric telescopic rod 4-1 is powered to retract, thereby driving the blocking plate 4-2 to rotate and separate from the air inlet 1-6. When the device is installed on an airplane, the airplane moves and hits the wind. Air enters the pressurization section 1-3 through the arc-shaped surface at the bottom of the blocking plate 4-2, and then flows into the combustion chamber 5-1 together with the air pressed by the compressor 3. This can increase the air intake of the combustion chamber 5-1. The electric telescopic rod 4-1 retraction simultaneously sends a signal to the PLC controller. The PLC controller controls the fuel pump 6-3 to start. The fuel pump 6-3 sends the fuel in the fuel chamber 6-1 into another fuel pipe 5-4, and then sprays it into the combustion chamber 5-1 through the other fuel pipe 5-4. At this time, the fuel supply can be increased to avoid surging caused by insufficient fuel supply when the air intake increases. When the electric telescopic rod 4-1 controls the blocking plate 4-2 to rotate and reset, the PLC controller controls the fuel pump 6-3 to stop supplying fuel, which can prevent excessive fuel from burning insufficiently and increase carbon deposition. At the same time, it can also reduce the operating cost of the device. If the device is set to be fixed, the compressor 3 will quickly press air into the shell 1. At this time, the air pressure in the shell 1 is lower than the external air pressure. When the blocking plate 4-2 is opened, the air pressure will press the air into the pressurization section 1-3 through the air inlet 1-6.

[0039] When the device is not in use, the driving motor 2-2 is powered to drive the screw rod 2-3 to rotate. The screw rod 2-3 rotates through the limiting of the support rod 2-5 and the hinge rod 2-6, drives the moving block 2-4 to move left along the screw rod 2-3, and then drives the support rod 2-5 to rotate and unfold by the hinge rod 2-6, and rests on the inner wall of the air inlet section 1-1. At this time, the tarpaulin is unfolded to shield the air inlet section 1-1. When impurities are blown into the air inlet section 1-1, they are blocked by the tarpaulin, and the wind carrying impurities flows out through the impurity removal hole 1-2. This can protect the compressor 3. Reverse operation of the above steps can reset the support rod 2-5 and fold the tarpaulin.

[0040] Meanwhile, the contents not described in detail in the specification all belong to the existing technology known to those skilled in the art.

[0041] It should be noted that in this paper, relationship terms such as first and second are only used to distinguish one entity or operation from another, and do not necessarily require or imply any actual relationship or order between the entities or operations. Moreover, the terms "include", "contain" or any other variant thereof are intended to cover non-exclusive inclusion, so that the process, method, article or device including a series of elements not only includes those elements, but also includes other elements not explicitly listed or inherent to such process, method, article or device.

[0042] It will be apparent to those skilled in the art that the application is not limited to the details of the above-exemplified embodiments and that the present application can be implemented in other forms without departing from the spirit or essential characteristics of the present application. The embodiments should therefore be considered in all respects as illustrative and not restrictive, the scope of the application being indicated by the appended claims rather than by the above description, and all changes which come within the meaning and range of equivalency of the claims are therefore intended to be embraced therein. No reference signs in the claims should be considered as limiting the scope of the claims to the features to which the reference signs are attached.

[0043] While the embodiments of the application have been shown and described, it is to be understood that the embodiments described are only exemplary and that changes can be made in the details of the embodiments without departing from the spirit and the principles of the application, which is defined by the following claims and their equivalents.

Claims

1. A fuel supply control system for a jet propulsion device, characterized in that: include: The housing (1) comprises a protective assembly (2), a compressor (3), a control assembly (4), a combustion assembly (5), and a supply assembly (6). The protective assembly (2), compressor (3), control assembly (4), and combustion assembly (5) are fixed inside the housing (1). The supply assembly (6) is fixed at the upper end of the housing (1). Multiple control assemblies (4) are evenly distributed. The housing (1) is divided from right to left into: an intake section (1-1), a pressurization section (1-3), a combustion section (1-4), and a tail spray section (1-5). The intake section (1-1) has exhaust holes (1-2) evenly distributed around its circumference. The pressurization section (1-3) has multiple air inlets (1-6) evenly distributed around its circumference. Each of the multiple control assemblies (4) includes: an electric... The electric telescopic rod (4-1) and the baffle plate (4-2) are provided. One end of the electric telescopic rod (4-1) is rotatably connected to the outer wall of the pressurization section (1-3), and the other end of the electric telescopic rod (4-1) is rotatably connected to the top surface of the baffle plate (4-2). The baffle plate (4-2) is rotatably connected to the two side walls of the air inlet (1-6) via a rotating shaft. The size of the baffle plate (4-2) matches the size of the air inlet (1-6). The bottom surface of the baffle plate (4-2) is an arc-shaped surface. The protective assembly (2) includes: a fixed frame (2-1), a drive motor (2-2), a screw (2-3), a moving block (2-4), a support rod (2-5), and a hinge rod (2-6). The fixed frame (2-1) is fixed inside the air inlet section (1-1) by a bracket. The unit comprises a fixed frame (2-1) with a drive motor (2-2) fixed inside. One end of the screw (2-3) is rotatably connected to the intake section (1-1) via a bracket. The other end of the screw (2-3) rotatably passes through the fixed frame (2-1) and is fixedly connected to the output shaft of the drive motor (2-2). The moving block (2-4) is screwed into the screw (2-3). One end of the support rod (2-5) is rotatably connected to the fixed frame (2-1). One end of the hinge rod (2-6) is rotatably connected to the moving block (2-4). The other end of the hinge rod (2-6) is rotatably connected to the support rod (2-5). Multiple support rods (2-5) are evenly distributed around the fixed frame (2-1), and multiple hinge rods (2-6) are provided. A waterproof cloth is fixed on each of the multiple support rods (2-5), forming a circle. The combustion assembly (5) includes a combustion chamber (5-1), an air intake cone (5-2), a heat insulation tile (5-3), a fuel pipe (5-4), and an ignition device (5-5). The combustion chamber (5-1) is fixed inside the combustion section (1-4). An air intake cone (5-2) is provided at one end of the combustion chamber (5-1). The heat insulation tile (5-3) is detachably fixed inside the combustion chamber (5-1). The fuel pipe (5-4) is sealed and fixedly inserted into the combustion section (1-4) and into the combustion chamber (5-1). Two fuel pipes (5-4) are symmetrically arranged, and an ignition device (5-5) is fixed between the two fuel pipes (5-4).The supply assembly (6) includes a fuel chamber (6-1), a fuel inlet (6-2), and a fuel pump (6-3). The fuel chamber (6-1) is fixed to the outer wall of the combustion section (1-4). The fuel inlet (6-2) is provided on the fuel chamber (6-1). The fuel pump (6-3) is fixed inside the fuel chamber (6-1). One fuel pipe (5-4) is fixedly connected to the fuel chamber (6-1), and the other fuel pipe (5-4) is sealed and fixedly inserted into the fuel chamber (6-1) and fixedly connected to the outlet of the fuel pump (6-3).

2. A control method for a fuel supply control system for a jet propulsion device according to any one of claims 1, characterized in that: The method includes the following steps: S1. Power on the compressor (3) to draw in air through the intake section (1-1) and send it into the combustion section (1-4), and fuel enters the fuel chamber (6-1) through the fuel inlet (6-2); S2. Power on the ignition device (5-5) to burn the fuel, and spray it out through the tail nozzle (1-5) with the airflow; S3. Powering on the electric telescopic rod (4-1) causes the baffle plate (4-2) to rotate, increasing the air intake. S4. The fuel pump (6-3) is started to send the fuel inside the fuel chamber (6-1) into another fuel pipe (5-4) to increase the fuel supply.

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