High-Mach-number boron powder ramjet engine based on air fluidization

Abstract

The invention provides a high-Mach-number boron powder ramjet engine based on air fluidization. The high-Mach-number boron powder ramjet engine comprises a boron powder conveying module and a kerosene conveying module. The boron powder conveying module can convey boron powder to the combustion part; the kerosene conveying module can convey kerosene to the combustion part; and the combustion part is provided with a stable combustion support plate. The problems of boron powder conveying and ignition stable combustion of the high-Mach-number boron powder ramjet engine based on air fluidization are solved, and incoming flow air is directly used as driving gas and fluidizing gas to fluidize boron powder fuel; kerosene is combusted, and injected fluidized air generates a high-temperature low-speed oxygen-enriched area behind the stable combustion support plate, so that removal of an oxide layer on the surface of the boron powder fuel is accelerated, and the combustion effect of the boron powder fuel is improved. The problem that in the prior art, a boron powder fuel conveying system is too complex to be integrated with an engine system is solved, the defects that reliable ignition and stable combustion are difficult to achieve due to the poor ignition combustion characteristic of boron powder fuel are overcome, and high integration of the boron powder fuel conveying system and the engine and ignition stable combustion of the boron powder fuel are achieved.

Description

Technical Field

[0001] This application relates to the field of aerospace technology, and in particular to a high Mach number boron powder ramjet engine based on air fluidization. Background Technology

[0002] Hypersonic air-breathing vehicles are a focal point of aerospace competition, and ramjet engines, as their core technology, have received considerable attention in recent decades. Powder ramjet engines, using high-energy solid powders as fuel, possess advantages such as high specific impulse, adjustable thrust, and simple structure, while avoiding the problem of insufficient heat release at high Mach numbers with hydrocarbon fuels. They demonstrate potential for adapting to even higher flight Mach numbers and have broad application prospects in the field of aircraft. Among various solid powder fuels, boron powder fuel stands out due to its high quality calorific value and high volumetric calorific value. However, as the most promising technology, boron powder fuel still faces many challenges.

[0003] In boron powder fuel ramjet engines, precise fuel supply is a key technology for their engineering application. Currently, most powder fuel supply methods are air entrainment, with powder flow rate primarily controlled by pneumatic drive or electric motor displacement-driven pistons. However, both of these methods require fluidizing gas for powder transport, which increases engine structural complexity and reduces reliability. Furthermore, due to the irregular, sheet-like structure and strong adhesion of boron powder, it is prone to clogging of transport pipelines during transport. Therefore, a high-flow-rate gas source is required to achieve stable powder delivery.

[0004] Meanwhile, under high Mach number conditions, the airflow velocity inside the engine will exceed the flame propagation velocity, easily causing engine stall. Therefore, it is necessary to select a suitable combustion stabilization device to reduce the airflow velocity and accelerate flame propagation. However, the addition of the corresponding combustion stabilization device will cause a total pressure loss inside the engine, so it is necessary to minimize flow losses while stabilizing flame combustion. In addition, high airflow velocity will significantly reduce the residence time of powdered fuel in the engine. Considering the poor ignition and combustion characteristics of boron powdered fuel, it is necessary to optimize the combustion organization scheme to ensure stable ignition and efficient combustion of boron powdered fuel in order to improve engine performance.

[0005] In summary, there is an urgent need to propose a high Mach number boron powder ramjet engine based on air fluidization, which can, to some extent, solve the technical problems existing in the current technology. Summary of the Invention

[0006] The purpose of this application is to provide a high Mach number boron powder ramjet engine based on air fluidization, which aims to achieve a stable supply of boron powder fuel at high Mach numbers and a combustion organization scheme for boron powder fuel.

[0007] This application provides a high Mach number boron powder ramjet engine based on air fluidization, including a housing body and an engine flow channel; the engine flow channel is sequentially divided into an intake section, an isolation section, and a combustion section along a first direction; the high Mach number boron powder ramjet engine based on air fluidization further includes: A boron powder conveying module is located at the front end of the shell body. It stores boron powder inside and can guide the boron powder to the combustion section at the position of the flame stabilizing support plate. The flame stabilizing support plate is provided with a cooling channel inside. A kerosene delivery module is located at the rear end of the shell body and has a supply unit; the supply unit stores kerosene and can deliver the kerosene to the combustion stabilizing support plate; the input end of the heat exchange unit is connected to the supply unit, and the output end is located inside the combustion stabilizing support plate and connected to its internal cooling pipes. The flame-stabilizing support plate protrudes outward from the middle of the shell body.

[0008] In the above technical solution, the first direction further includes a first sidewall, a second sidewall, and a third sidewall connected in sequence; There are two first sidewalls, and the two first sidewalls are at a first preset angle. The second sidewall forms a second preset angle with the first sidewall; The third sidewall and the second sidewall are at a third preset angle.

[0009] In the above technical solution, further, let the projected area of ​​the combustion stabilizing support plate in the first direction be A1, and let the projected area of ​​the engine flow channel at the combustion stabilizing support plate be A2, then the value of A1 / A2 is less than or equal to 0.15.

[0010] In the above technical solution, the boron powder conveying module further includes: The booster unit is used to increase the pressure of the incoming airflow; The cooling section is used to cool high-pressure air; Storage section for storing the boron powder; The fluidization section is used to transport fluidized air. The first flow guide has one end connected to the storage unit, and the storage unit is connected to the flame stabilizing support plate through the second flow guide; The driving unit is capable of pushing the boron powder in the storage unit so that the boron powder can be guided to the flame-stabilizing support plate through the second flow guide.

[0011] In the above technical solution, the driving unit further includes: A piston, which is placed inside the storage section.

[0012] In the above technical solution, the kerosene delivery module further includes: The storage section contains the kerosene. The third flow guide has one end connected to the storage section and the other end connected to the flame stabilizing support plate.

[0013] In the above technical solution, the heat exchange unit further includes: The cooling channel has its inlet end connected to the third guide section and its other end connected to the injection outlet.

[0014] In the above technical solution, the equivalence ratio of the kerosene is less than or equal to 0.2.

[0015] Compared with the prior art, this application has the following beneficial effects: This application provides a high Mach number boron powder ramjet engine based on air fluidization, including a housing body and an engine flow channel; the engine flow channel is sequentially divided into an intake section, an isolation section, and a combustion section along a first direction; the high Mach number boron powder ramjet engine based on air fluidization further includes: A boron powder conveying module is located at the front end of the shell body, stores boron powder inside, and can guide the boron powder to the combustion section at the position of the combustion stabilizing support plate of the combustion section; A kerosene delivery module is located at the rear end of the shell body and includes a supply unit and a heat exchange unit. The supply unit stores kerosene and can deliver the kerosene to the combustion stabilizing support plate. The input end of the heat exchange unit is connected to the supply unit, and the output end is located inside the combustion stabilizing support plate and connected to its internal cooling pipes. The flame-stabilizing support plate protrudes outward from the middle of the shell body.

[0016] In summary, this application solves the problem of boron powder delivery in high Mach number ramjet engines: the incoming air captured by the intake is pressurized and cooled and then directly used as the driving gas and auxiliary fluidizing gas of the boron powder delivery system, avoiding the need for additional air supply structures, optimizing system integration, simplifying engine structure, and effectively fluidizing and delivering boron powder fuel.

[0017] In addition, stable ignition and efficient combustion of boron powder fuel are achieved: the combustion section is equipped with a flame-stabilizing support plate, into which kerosene fuel is injected. While cooling and protecting the structure, the kerosene combustion generates a high-temperature, low-speed zone behind it, which enhances the residence time of boron powder fuel and uses fluidized air to form an oxygen-rich zone. This significantly improves the combustion efficiency of boron powder fuel, stabilizes the flame, and avoids the problems of shortened residence time and flame extinction caused by high-speed airflow.

[0018] Furthermore, the combustion-stabilizing support plate employs a low blockage ratio design, which stabilizes and promotes combustion while avoiding significant total pressure loss to ensure engine performance. Simultaneously, the internal cooling channels effectively prevent thermal erosion, ensuring stable operation of the support plate. Attached Figure Description

[0019] To more clearly illustrate the technical solutions in the specific embodiments of this application or the prior art, the drawings used in the description of the specific embodiments or the prior art will be briefly introduced below. Obviously, the drawings described below are some embodiments of this application. For those skilled in the art, other drawings can be obtained from these drawings without creative effort.

[0020] Figure 1 A first structural schematic diagram of a high Mach number boron powder ramjet engine based on air fluidization provided in this application; Figure 2 for Figure 1 Enlarged view of point A; Figure 3 This is a second structural schematic diagram of a high Mach number boron powder ramjet engine based on air fluidization, provided in this application.

[0021] Reference numerals: 1-Shell body; 101-First direction; 102-Air intake; 103-Isolation section; 104-Combustion section; 105-Engine flow passage; 201-Pressure boosting section; 202-Cooling section; 203-First flow guide section; 204-First shut-off valve; 205-Flow control device; 206-Fluidization section; 207-Piston; 208-Storage section; 209-Second flow guide section; 210-Second shut-off valve; 301 - Third shut-off valve; 302 - Third flow guide section; 303 - Suction pump; 304 - Storage section; 401-First sidewall; 402-Kerosene passage; 403-Second sidewall; 404-Gas-solid two-phase flow passage; 405-Cooling passage; 406-Third sidewall; 407-Injection outlet. Detailed Implementation

[0022] To help those skilled in the art fully understand the methods, devices, and systems disclosed in this application, specific embodiments will be described below in conjunction with the accompanying drawings. However, it should be understood that the described embodiments are only a portion of the embodiments of this application, not all of them. The following detailed description of the embodiments of this application provided in the accompanying drawings is not intended to limit the scope of the claimed application, but merely represents selected embodiments of this application.

[0023] The components, structures, and connections shown in the accompanying drawings of this application can be arranged and designed in various different configurations according to actual application requirements. Therefore, the following detailed description of the embodiments disclosed in the drawings is only used to illustrate the technical concept and selected implementation methods of this application, and is not a direct limitation on the scope of protection of this application.

[0024] Based on the embodiments disclosed in this application, all other technical solutions obtained by those skilled in the art through reasonable deduction, equivalent substitution, or simple modification without creative effort should be included within the protection scope of this application.

[0025] In the description of this application, the terms "front end," "middle end," "rear end," "upper," "above," "lower," "below," "left," "right," "vertical," "horizontal," "inner," and "outer," etc., indicate the orientation or positional relationship based on the relative orientation or positional relationship shown in the accompanying drawings. Their purpose is to simplify the description and facilitate understanding of the technical solution of this application, and is not intended to explicitly limit the device or element to have a specific orientation, or to be constructed and operated in a specific orientation. Therefore, they should not be construed as limitations on this application. If the device is positioned in other ways (such as swinging 90 degrees or being in other orientations), the above spatial relationship terms should be interpreted accordingly.

[0026] The terms “first,” “second,” and “third” are used only to distinguish the objects being described (such as components, parts, regions, layers, or sections) and do not imply any order of precedence, hierarchy, or quantity limitation. They should not be construed as limitations on the technical solution of this application.

[0027] The terms “and” and “or” include any one of the listed related items, as well as any combination of two or more items.

[0028] In the description of this application, it should be noted that, unless otherwise expressly specified and limited, those skilled in the art can understand the specific meaning of the above terms in this application according to the specific circumstances.

[0029] This application provides a high Mach number boron powder ramjet engine based on air fluidization, combined with... Figure 3 As shown, the high Mach number boron powder ramjet engine based on air fluidization includes a housing body 1. The first direction 101 refers to the direction from left to right. In practical applications, an engine flow channel 105 is formed along the first direction 101. This flow channel 105 is sequentially divided into an intake section 102, an isolation section 103, and a combustion section 104 along the first direction 101. The intake section 102 is used to decelerate the high-speed incoming flow, ensuring that the gas entering the intake section reaches a certain temperature and pressure. The isolation section 103 isolates the pressure fluctuations of the combustion section from the intake section through a shock wave train, ensuring the normal operation of the intake section.

[0030] Combination Figure 1 As shown, the high Mach number boron powder ramjet engine based on air fluidization also includes a boron powder delivery module, which is located at the front end of the housing 1 and can guide boron powder fuel to the combustion chamber 104. (Specifically combined...) Figure 1 As shown, the boron powder conveying module includes a pressurizing unit 201, a cooling unit 202, a first flow guiding unit 203 and a second flow guiding unit 209, a flow control device 205, a fluidizing unit 206, a driving unit piston 207, a storage unit 208, and a second shut-off valve 210.

[0031] The system includes a pressurization section for increasing the pressure of the incoming air. A cooling section for cooling the high-pressure air. A storage section for storing the boron powder. A fluidization section for conveying fluidizing gas. A first guide section is connected at one end to the storage section, and the storage section is connected to the flame-stabilizing support plate via a second guide section. A drive section is capable of pushing the boron powder within the storage section, allowing it to flow through the second guide section to the flame-stabilizing support plate. The drive section includes a piston positioned within the storage section.

[0032] In actual operation, high-speed air is pressurized by the booster unit 201 and then reaches a suitable temperature through the cooling unit 202. Once the first shut-off valve 204 opens, the driving air enters the piston 207 of the drive unit via the flow control device 205, propelling it forward to transport boron powder. Fluidizing air enters the storage unit 208 via the fluidizing unit 206 to assist in fluidizing the boron powder fuel. Afterward, the gas-solid two-phase flow passes through the second guide unit 209 and the second shut-off valve 210 before entering the combustion stabilization support plate. This operation directly utilizes the incoming airflow as the driving and fluidizing air source, simplifying the engine structure and improving its reliability.

[0033] Combination Figure 1 As shown, the high Mach number boron powder ramjet engine based on air fluidization also includes a kerosene delivery module, which includes a storage section 304, a suction pump 303, a third guide section 302, and a third shut-off valve 301. The storage section stores kerosene. The third guide section is connected at one end to the storage section and at the other end to a combustion stabilization support plate.

[0034] In actual operation, kerosene is supplied by the storage unit 304 and transported to the combustion stabilization support plate via the suction pump 303, the third guide unit 302, and the third shut-off valve 301. During this operation, the kerosene equivalence ratio is less than or equal to 0.2.

[0035] Combination Figure 1 and Figure 2As shown, the high Mach number boron powder ramjet engine based on air fluidization also includes a combustion stabilization support plate. The combustion stabilization support plate includes a first sidewall 401, a kerosene passage 402, a second sidewall 403, a gas-solid two-phase flow passage 404, a cooling passage 405, a third sidewall 406, and an injection outlet 407. The cooling passage has its inlet end connected to the third guide section and its other end connected to the injection outlet. During operation, kerosene enters the combustion stabilization support plate through 402, absorbs heat in the cooling passage 405, and is ejected from the injection outlet 407, forming a high-temperature, low-speed zone at the rear end of the combustion stabilization support plate. This prolongs the residence time of the boron powder fuel, shortens the ignition delay time, and protects the support plate structure. The boron powder fuel and fluidizing gas enter the combustion stabilization support plate through the gas-solid two-phase flow passage 404 and are ejected from the injection outlet 407, entering the high-temperature, low-speed zone generated by kerosene combustion. Under the combined action of the fluidizing air and the mainstream air, they ignite and burn rapidly, effectively improving the combustion efficiency of the boron powder fuel.

[0036] Combination Figure 2 As shown, it should be noted that the combustion stabilizing support plate has two first sidewalls 401, which are arranged at a first preset angle, preferably 30°. The second sidewall 403 is arranged at a second preset angle with the first sidewall 401, preferably 165°. The third sidewall 406 is arranged at a third preset angle with the second sidewall 403, preferably 105°. Furthermore, if the projected area of ​​the combustion stabilizing support plate in the first direction 101 is A1, and the projected area of ​​the engine flow channel 105 at the position of the combustion stabilizing support plate is A2, then the value of A1 / A2 is less than or equal to 0.15, preferably 0.15.

[0037] In summary, this application solves the problem of boron powder delivery in high Mach number ramjet engines: the incoming air captured by the intake manifold is pressurized and cooled and then directly used as the driving gas and auxiliary fluidizing gas of the boron powder delivery system, avoiding the need for additional air supply structures, optimizing system integration, simplifying engine structure, and effectively fluidizing and delivering boron powder fuel.

[0038] In addition, stable ignition and efficient combustion of boron powder fuel are achieved: the combustion section is equipped with a flame-stabilizing support plate, into which kerosene fuel is injected. While cooling and protecting the structure, the kerosene combustion generates a high-temperature, low-speed zone behind it, which enhances the residence time of boron powder fuel and uses fluidized air to form an oxygen-rich zone. This significantly improves the combustion efficiency of boron powder fuel, stabilizes the flame, and avoids the problems of shortened residence time and flame extinction caused by high-speed airflow.

[0039] Furthermore, the combustion-stabilizing support plate employs a low blockage ratio design, which stabilizes and promotes combustion while avoiding significant total pressure loss to ensure engine performance. Simultaneously, the internal cooling channels effectively prevent thermal erosion, ensuring stable operation of the support plate.

[0040] A high Mach number boron powder ramjet engine based on air fluidization includes a boron powder delivery module and a kerosene delivery module. The boron powder delivery module delivers boron powder to the combustion chamber, and the kerosene delivery module delivers kerosene to the combustion chamber. The combustion chamber is equipped with a combustion stabilization support plate. This application solves the problems of boron powder delivery and ignition stabilization in a high Mach number boron powder ramjet engine based on air fluidization. It uses incoming air as the driving gas and auxiliary fluidizing gas to atomize the boron powder fuel. Through kerosene combustion and the injection of fluidizing air behind the combustion stabilization support plate, a high-temperature, low-speed, oxygen-rich region is generated, accelerating the removal of the oxide layer on the surface of the boron powder fuel, shortening its ignition delay time, and improving its combustion efficiency. This application overcomes the problems of existing technologies where the boron powder fuel delivery system is too complex to integrate with the engine system, and the poor ignition and combustion characteristics of boron powder fuel make reliable ignition and stable combustion difficult. It achieves a high degree of integration between the boron powder fuel delivery system and the engine, as well as ignition and stable combustion of the boron powder fuel.

[0041] Finally, it should be noted that the above embodiments are only used to illustrate the technical solutions of this application, and are not intended to limit them. Although this application has been described in detail with reference to the foregoing embodiments, those skilled in the art should understand that modifications can still be made to the technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some or all of the technical features therein. Such modifications or substitutions do not cause the essence of the corresponding technical solutions to deviate from the scope of the technical solutions of the embodiments of this application.

Claims

1. A high Mach number boron powder ramjet engine based on air fluidization, comprising a casing and an engine flow channel; wherein the engine flow channel is sequentially divided into an intake section, an isolation section, and a combustion section along a first direction; characterized in that, The high Mach number boron powder ramjet engine based on air fluidization also includes: A boron powder conveying module is located at the front end of the shell body. It stores boron powder inside and can guide the boron powder to the combustion section at the position of the flame stabilizing support plate. The flame stabilizing support plate is provided with a cooling channel inside. A kerosene delivery module is located at the rear end of the shell body and has a supply unit; the supply unit stores kerosene and can deliver the kerosene to the combustion stabilizing support plate; the input end of the heat exchange unit is connected to the supply unit, and the output end is located inside the combustion stabilizing support plate and connected to its internal cooling pipes. The flame-stabilizing support plate protrudes outward from the middle of the shell body.

2. The high Mach number boron powder ramjet engine based on air fluidization according to claim 1, characterized in that, The first direction includes a first sidewall, a second sidewall, and a third sidewall connected in sequence; There are two first sidewalls, and the two first sidewalls are at a first preset angle. The second sidewall forms a second preset angle with the first sidewall; The third sidewall and the second sidewall are at a third preset angle.

3. The high Mach number boron powder ramjet engine based on air fluidization according to claim 2, characterized in that, it is provided that... Let A1 be the projected area of ​​the combustion stabilizing support plate in the first direction, and let A2 be the projected area of ​​the engine flow channel at the combustion stabilizing support plate. Then the value of A1 / A2 is less than or equal to 0.

15.

4. The high Mach number boron powder ramjet engine based on air fluidization according to claim 1, characterized in that, The boron powder conveying module includes: The booster unit is used to increase the pressure of the incoming airflow; The cooling section is used to cool high-pressure air; Storage section for storing the boron powder; The fluidization section is used to transport fluidized air. The first flow guide has one end connected to the storage unit, and the storage unit is connected to the flame stabilizing support plate through the second flow guide; The driving unit is capable of pushing the boron powder in the storage unit so that the boron powder can be guided to the flame-stabilizing support plate through the second flow guide.

5. The high Mach number boron powder ramjet engine based on air fluidization according to claim 4, characterized in that, The drive unit includes: A piston, which is placed inside the storage section.

6. The high Mach number boron powder ramjet engine based on air fluidization according to claim 5, characterized in that, The kerosene delivery module includes: The storage section contains the kerosene. The third flow guide has one end connected to the storage section and the other end connected to the flame stabilizing support plate.

7. The high Mach number boron powder ramjet engine based on air fluidization according to claim 6, characterized in that, The heat exchange unit includes: The cooling channel has its inlet end connected to the third guide section and its other end connected to the injection outlet.

8. The high Mach number boron powder ramjet engine based on air fluidization according to claim 6, characterized in that, The kerosene equivalence ratio is less than or equal to 0.2.

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