CN119957384B - With afterburners micro turbine jet engine - Google Patents
With afterburners micro turbine jet engineInfo
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- CN119957384B CN119957384B CN202510176172.2A CN202510176172A CN119957384B CN 119957384 B CN119957384 B CN 119957384B CN 202510176172 A CN202510176172 A CN 202510176172A CN 119957384 B CN119957384 B CN 119957384B
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- afterburner
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Abstract
The invention relates to a microminiature turbojet engine with an afterburner, which comprises a core machine, a tail nozzle and an afterburner, wherein two ends of the afterburner are respectively connected with the core machine and the tail nozzle, and the flow direction of fuel gas sequentially passes through the core machine, the afterburner and the tail nozzle. The tail nozzle is a subsonic convergent type tail nozzle, the area of the tail nozzle can be adjusted, the engine efficiency and afterburning efficiency are further maximized, compared with the traditional microminiature turbojet engine, the performance is more excellent, afterburning control is simpler, more convenient and more reliable, and the use scene of the microminiature aeroengine is widened.
Description
Technical Field
The invention relates to the technical field of aeroengines, in particular to a microminiature turbojet engine with an afterburner.
Background
The miniature turbojet engine is an aeroengine with low manufacturing cost, short service life, light weight and small thrust, and is generally applied to the fields of aeromodelling, fixed-wing unmanned aerial vehicles, gliders, targets, cruise missiles and the like.
For the microminiature turbojet engine, the application of the microminiature turbojet engine to the afterburning technology is almost zero due to the use of manufacturing, maintenance and maintenance costs, design application scenes and the like, and the additional added mass of an accessory device and an afterburner required by afterburning and a tail nozzle matched with the microminiature turbojet engine is overlarge, so that the fuel economy is reduced and the thrust-weight ratio of the whole engine is obviously reduced. From the specific technical implementation point of view, the microminiature turbojet engine can be used for afterburning, because the total gas pressure after the turbine of the microminiature turbojet engine is lower, forced afterburning can lead to the fact that the total gas pressure in the afterburner is higher than the total gas pressure after the turbine, the turbine gas flows back and surge, the engine is stopped, if the afterburning is excessive, supersonic airflow is possibly generated in the afterburner, a series of excitation systems are generated, the state adjustment of the tail nozzle is influenced, if the tail nozzle is in a supersonic tail nozzle shape for adapting to shock waves, the core efficiency when the afterburning is not used is remarkably reduced, if the subsonic tail nozzle is in a subsonic tail nozzle, the afterburning of the excitation systems cannot be matched, the afterburning chamber is overheated, the gas circulation is not smooth, and the afterburning efficiency is greatly reduced.
If the microminiature turbojet engine is combined with the afterburning technology, the technology to be solved comprises the steps of determining the configuration of the tail nozzle, optimizing a diffuser, simplifying engine accessories, selecting a path of the afterburning ignition technology, controlling the afterburner and the core machine to work together, and additionally introducing air to support combustion in a proper amount.
With development of technological process and social demands on aeroengine performance, higher requirements are put on performance of micro aeroengines, especially in the military field, new equipment such as a patrol bomb and the like has higher standards on performance and reliability of the micro turbojet engine, in some cases, the thrust maximization is allowed to be pursued in a short time without considering fuel economy, thus coping with some special situations such as end military strike, balancing a plurality of engine thrust, quick take-off of an aircraft and the like, and for aeroengines, the thrust of the engines can be greatly promoted in a short time by afterburning, so that the demands are realized, but only the subsonic tail nozzle, the afterburner air entraining device with an assembling sleeve are added, the afterburner structure is optimized for the micro turbojet engine, and therefore, the design of the turbojet engine with the afterburner is necessary.
Disclosure of Invention
The invention aims to provide a microminiature turbojet engine with an afterburner, which combines an afterburning technology with the microminiature turbojet engine to greatly improve the performance of the microminiature turbojet engine, and simultaneously has the reliability and convenience in use and control, so that the problem of insufficient instantaneous performance of the conventional microminiature turbojet engine in the background technology is solved.
The invention is realized by the following technical scheme.
The microminiature turbojet engine with the afterburner comprises a core machine, a tail nozzle and an afterburner, wherein two ends of the afterburner are respectively connected with the core machine and the tail nozzle;
The core machine comprises a gas compressor impeller, a core machine casing, a core machine combustion chamber, a turbine guide, a main shaft, a support bearing, a spark plug, a core machine fuel pipe and a gas compressor diffusion disc, wherein the gas compressor impeller, the core machine combustion chamber and the turbine are arranged in the core machine casing, the gas compressor impeller and the turbine are jointly arranged on the main shaft through the support bearing, the gas compressor impeller is arranged at the front end of the core machine casing through the gas compressor diffusion disc in interference fit, the turbine is arranged at the rear end of the core machine casing through the turbine guide, the core machine combustion chamber is arranged between the gas compressor impeller and the turbine, the spark plug is arranged on the core machine casing, the ignition end of the spark plug is arranged at the outer side of the core machine combustion chamber, and the core machine fuel pipe is communicated with a main fuel tank and the core machine combustion chamber;
The afterburner comprises an afterburner casing, a diffusion type flame standing flow combustion stabilizing groove, an afterburner fuel pipe, a fuel atomizer, a gas guiding hole, a gas guiding one-way valve and an afterburner matching surface, wherein the front end of the afterburner is provided with the diffusion type flame standing flow combustion stabilizing groove, the front end of the afterburner is provided with the gas guiding hole, the gas guiding hole corresponds to the position of the diffusion type flame standing flow combustion stabilizing groove, the gas guiding hole is internally provided with the gas guiding one-way valve, air is introduced through an external air pump to support combustion, and meanwhile, the gas overflow caused by the excessive internal air pressure of the afterburner is prevented, the afterburner casing is provided with the afterburner fuel pipe, the fuel is sprayed into the afterburner through the fuel atomizer distributed in an annular shape, the afterburner matching surface is positioned in the afterburner casing before a tail nozzle behind the diffusion type standing flow flame combustion stabilizing groove, and a gap exists between the afterburner matching surface and the afterburner casing;
The tail nozzle is a subsonic convergent type tail nozzle and consists of a plurality of guide plates, and the convergence of the tail nozzle 3 is controlled by controlling the rotation angle of the guide plates along the shaft.
Further, the core machine belongs to a centrifugal gas generator.
Further, a support bearing at the impeller of the compressor is connected with the main shaft and the diffuser plate of the compressor, and a support bearing at the turbine is connected with the main shaft and the turbine guider, and is in a 0-2-0 type layout.
Further, the diffusion type standing-flow flame stabilizing groove is composed of an outer standing-flow combustion stabilizing groove and an inner standing-flow combustion stabilizing groove, and the diffusion opening angles of the inner standing-flow combustion stabilizing groove and the outer standing-flow combustion stabilizing groove are the same.
Further, the afterburner casing is formed by a plurality of sections of casings, and each section of casing is externally connected through a casing external bolt.
Further, the core machine, the afterburner and the tail nozzle are externally connected through an external bolt.
The afterburner fuel pipe is connected with the core engine fuel pipe through an external fuel pipe, the fuel sources are the same as the main fuel tank, the same type of fuel is used for sharing one fuel pump and one oil-gas separator, an electromagnetic throttle valve is arranged at the joint of the core engine fuel pipe and the afterburner fuel pipe, the electromagnetic throttle valve is opened when the core engine is in a maximum state and afterburning is carried out, the minimum regulating flow of the electromagnetic throttle valve is the critical ignition fuel supply amount of the afterburner, and the maximum regulating flow is the critical temperature fuel supply amount of the afterburner.
Further, the diameter of the largest expanding inner wall of the tail pipe is the same as the diameter of the mating surface of the afterburner, when the electromagnetic throttle valve is in the minimum throttle state, afterburning is in the critical ignition state, when the tail pipe is in the minimum convergence state, when the electromagnetic throttle valve is in the maximum throttle state, afterburning is in the critical temperature state, when the tail pipe is in the maximum expanding state, and if the afterburning state is not started, the tail pipe can also be subjected to convergence degree adjustment according to the state of the core machine.
Further, the afterburner is ignited by the gas after the turbine. The afterburner is not equipped with an ignition device, and when afterburner is required, the core is necessarily at a maximum condition, and the post-turbine gas temperature is sufficient to ignite the afterburner fuel.
Compared with the prior art, the invention has the advantages that:
1. By organically combining the afterburning technology with the microminiature turbojet engine, the microminiature turbojet engine not only ensures small volume and low quality, but also can greatly increase the instantaneous thrust of the engine, further improves the performance indexes such as the flying speed, the maneuverability, the flight envelope and the like of the aircraft, and enables the aircraft to be used in more scenes.
2. Through designing the diffusion type flame standing-flow combustion stabilizing tank in the novel afterburner, make it adapt to the core machine based on centrifugal compressor more, this type compressor has the air velocity of flow in the compressor lower, the pressure is bigger, core machine based on centrifugal compressor has the characteristics such as core machine combustion chamber combustion temperature is lower, the main shaft rotational speed is higher, temperature is lower before the turbine, the whole subsonic flow of air current, for a series of characteristics, diffusion type flame standing-flow combustion stabilizing tank compares in traditional V type flame standing-flow combustion stabilizing tank that is applicable to axial-flow turbojet engine, it is weaker to the deceleration effect of air current, pressure loss is less, can make afterburning efficiency higher, and then the effective thrust that the engine obtained is bigger.
3. By using the subsonic convergent type tail nozzle, the expansion degree of the afterburning gas can be balanced, the gas is maintained in a critical working state as far as possible, the gas reaches the sonic velocity as far as possible at the outlet section of the tail nozzle, the thrust is increased, the sufficient turbine drop pressure ratio can be maintained, the total pressure recovery coefficient in the combustion chamber of the core machine is ensured, the stable working of the core machine can be effectively ensured while the afterburning efficiency is improved, and the balanced core machine and the afterburning are operated together. Meanwhile, the subsonic convergent type tail nozzle can also adjust the turbine drop pressure ratio of the core machine under the condition that afterburning is not started, so that the efficiency of the core machine is improved, and the fuel gas circulation rate can be adjusted when the core machine is started and accelerated, so that the core machine is prevented from being overheated under the starting state.
4. By combining the core engine fuel pipeline and the afterburner fuel pipeline and assisting in electromagnetic throttle valve control, the fuel control is simplified, the weight of engine accessories is reduced, the fuel economy and the thrust-weight ratio of the whole engine are improved, and the failure rate of the fuel system is reduced.
5. By means of the mode that the afterburner is ignited by the gas after the turbine, the situation that the afterburner is forcibly ignited when the core engine does not reach the maximum state or the core engine is not started is avoided, the engine is overheated and burnt, and the use safety of the engine is improved.
Drawings
FIG. 1 is a schematic cross-sectional view of the overall structure of the present invention;
FIG. 2 is a schematic view of the overall structural components of the present invention;
FIG. 3 is a cross-sectional view of the core machine of the present invention;
FIG. 4 is a cross-sectional view of the afterburner structure of the present invention;
FIG. 5 is a block diagram of a tail pipe of the present invention;
FIG. 6 is a schematic diagram of a core engine structure with a casing removed according to the present invention;
FIG. 7 is a schematic diagram of the air inlet surface of the diffusion flame stagnation combustion stabilization slot of the present invention;
FIG. 8 is a schematic diagram of the exhaust face of the diffusion flame stagnation combustion stabilization slot of the present invention;
FIG. 9 is a partial schematic view of a fuel pipe section of an afterburner.
In the figure, 1, a core machine, 2, an afterburner, 3, a tail nozzle, 101, a compressor impeller, 102, a core machine casing, 103, a core machine combustion chamber, 104, a turbine, 105, a turbine guider, 106, a main shaft, 107, a support bearing, 108, a spark plug, 109, a core machine fuel pipe, 110, a compressor expansion disc, 201, an afterburner casing, 202, a diffusion type flame standing flow combustion stabilizing groove, 212, an external standing flow combustion stabilizing groove, 222, an internal standing flow combustion stabilizing groove, 203, an afterburner fuel pipe, 204, a fuel atomizer, 205, a bleed air hole, 206, a bleed air one-way valve, 207, an afterburner matching surface and 301, a rectifying plate.
Detailed Description
In the description of the present invention, it should be noted that, the azimuth or positional relationship indicated by the terms "upper", "lower", "inner", "outer", etc., are based on the azimuth or positional relationship shown in the drawings, or the azimuth or positional relationship in which the inventive product is conventionally put in use, are merely for convenience of describing the present invention and simplifying the description, and are not indicative or implying that the apparatus or element to be referred to must have a specific azimuth, be configured and operated in a specific azimuth, and therefore should not be construed as limiting the present invention. In the description of the present invention, it should also be noted that, unless explicitly specified and limited otherwise, the terms "configured," "mounted," and "connected" are to be construed broadly, and may be, for example, fixedly connected, detachably connected, integrally connected, mechanically connected, electrically connected, directly connected, indirectly connected through an intermediate medium, or in communication between two elements. The specific meaning of the above terms in the present invention will be understood in specific cases by those of ordinary skill in the art.
Embodiments of the present invention will be described in detail below with reference to the drawings, but the present invention is not limited thereto.
As shown in fig. 1 to 3, the microminiature turbojet engine with the afterburner comprises a core machine 1, a tail nozzle 3 and an afterburner 2, wherein two ends of the afterburner 2 are respectively connected with the core machine 1 and the tail nozzle 3;
The core machine 1 comprises a compressor impeller 101, a core machine casing 102, a core machine combustion chamber 103, a turbine 104, a turbine guide 105, a main shaft 106, a support bearing 107, a spark plug 108, a core machine fuel pipe 109 and a compressor diffusion disc 110, wherein the compressor impeller 101, the core machine combustion chamber 103 and the turbine 104 are positioned in the core machine casing 102, the compressor impeller 101 and the turbine 104 are jointly installed on the main shaft 106 through the support bearing 107, the compressor impeller 101 is installed at the front end of the core machine casing 102 through the compressor diffusion disc 110 by adopting interference fit, the turbine 104 is installed at the rear end of the core machine casing 102 through the turbine guide 105, the core machine combustion chamber 103 is arranged between the compressor impeller 101 and the turbine 104, the spark plug 108 is installed on the core machine casing 102, the ignition end of the spark plug 108 is installed on the outer side of the core machine combustion chamber 103, the core machine fuel pipe 109 is communicated with the main fuel tank and the core machine combustion chamber 103, the front edge spreads in a ring shape along fuel gas during ignition, and finally, and each evaporation nozzle in the core machine combustion chamber 103 is covered by flame.
As shown in fig. 4, the afterburner 2 includes an afterburner casing 201, a diffusion type flame stagnation combustion stabilizing groove 202, an afterburner fuel pipe 203, a fuel atomizer 204, a gas-introducing hole 205, a gas-introducing one-way valve 206 and an afterburner mating surface 207, the front end of the afterburner 2 is provided with the diffusion type flame stagnation combustion stabilizing groove 202, the front end of the afterburner 2 is provided with the gas-introducing hole 205, the gas-introducing hole 205 corresponds to the position of the diffusion type flame stagnation combustion stabilizing groove 202, the gas-introducing one-way valve 206 is installed in the gas-introducing hole 205, air is introduced through an external air pump to support combustion, and meanwhile, the gas is prevented from overflowing due to the excessive air pressure in the afterburner 2, and the air pump is started to introduce air to participate in combustion under the condition that the fuel is introduced before the fuel is introduced, otherwise, the temperature of the afterburner 2 is difficult to ignite the afterburner after the turbine, the gas is difficult to ignite and cause ignition failure, and the gas-introducing pump is closed under the condition that the afterburner is not opened, and the total temperature and total pressure after the turbine gas is kept to expand in the afterburner 2.
As shown in fig. 9 and fig. 4, the afterburner casing 201 is provided with an afterburner fuel pipe 203, fuel is sprayed into the afterburner 2 through a fuel atomizer 204 distributed in a ring shape, the combustion zone is positioned in front of the tail nozzle 3 behind the diffusion standing flame combustion stabilizing groove 202, the afterburner fuel pipe 203 is not in direct contact with the cylindrical surface of the afterburner casing 201, but is fixed by a bracket on the afterburner casing 201, so that the leakage of fuel due to deformation and rupture of the fuel pipeline caused by uneven heating of the afterburner fuel pipe 203 can be avoided as much as possible, and a flight accident is caused. The afterburned mating surface 207 is positioned in the afterburned casing 201, and a gap exists between the afterburned mating surface 207 and the afterburned casing 201;
As shown in fig. 5, the tail pipe 3 is a subsonic convergent tail pipe, and is composed of a plurality of guide plates 301, and the convergence of the tail pipe 3 is controlled by controlling the rotation angle of the guide plates 301 along the shaft.
Further, the core machine 1 belongs to a centrifugal gas generator. The combustion temperature of the combustion chamber 103 of the core machine is lower, the rotating speed of the main shaft 106 is higher, the temperature before the turbine is lower, and the air flow flows at subsonic speed in the whole course, and it should be noted that the related design of the invention is based on the premise of the centrifugal gas generator.
Further, a support bearing 107 at the compressor impeller 101 connects the main shaft 104 with the compressor diffuser plate 110, and a support bearing 107 at the turbine 104 connects the main shaft 106 with the turbine guide 105 in a 0-2-0 type arrangement.
Further, as shown in fig. 4, 7 and 8, the diffusion type standing-stream flame stabilizing groove 202 is formed by an outer standing-stream combustion stabilizing groove 212 and an inner standing-stream combustion stabilizing groove 222, and the diffusion opening angle of the inner standing-stream combustion stabilizing groove 222 is the same as that of the outer standing-stream combustion stabilizing groove 212. The inner standing-flow combustion stabilizing groove 222 and the outer standing-flow combustion stabilizing groove 212 are adopted to match the afterburned matching surface 207, so that part of fuel gas can pass through a gap between the afterburned matching surface 207 and the afterburned casing 201 to form a gas film, the afterburned casing 201 is effectively cooled, the afterburned casing 201 is ensured not to generate thermal stress deformation, the afterburned casing 201 is caused to be poor in neutrality, the injection direction of the tail nozzle 3 is further influenced, and the thrust direction line and the mass center of the engine are unbalanced.
Further, as shown in fig. 2 and 4, the afterburner casing 201 is formed by multiple sections of casings, and each section of casing is externally connected by a casing external bolt.
Further, the core machine 1, the afterburner 2 and the tail pipe 3 are externally connected by external bolts.
Further, as shown in fig. 2, the afterburner fuel pipe 203 is connected with the core engine fuel pipe 109 through an external fuel pipe, the fuel sources are the same as the main fuel tank, the same type of fuel is used to share one fuel pump and one gas-oil separator, an electromagnetic throttle valve is arranged at the connection part of the core engine fuel pipe 109 and the afterburner fuel pipe 203, the electromagnetic throttle valve is opened when the core engine 1 is in the maximum state and afterburner is in afterburner, the minimum adjustment flow of the electromagnetic throttle valve is the afterburner critical ignition fuel supply amount, and the maximum adjustment flow is the afterburner critical temperature fuel supply amount.
Further, as shown in fig. 5, the diameter of the largest expanding inner wall of the tail pipe 3 is the same as the diameter of the pipe of the afterburner matching surface 207, when the electromagnetic throttle valve is in the minimum throttle state, afterburner is in the critical ignition state, when the tail pipe 3 is in the minimum convergence state, when the electromagnetic throttle valve is in the maximum throttle state, afterburner is in the critical temperature state, when the tail pipe 3 is in the largest expanding state, if the afterburner is not opened, the degree of convergence of the tail pipe 3 can be adjusted according to the state of the core machine.
Further, as shown in fig. 2 and 4, the afterburner 2 is ignited by the gas after passing through the turbine 104. The afterburner 2 is not equipped with an ignition device, and when afterburner is required, the core 1 must be at a maximum, and the post-turbine gas temperature is sufficient to ignite the afterburner fuel. By means of the mode that the fuel oil of the afterburner is ignited by the fuel gas after the turbine, the problem that the afterburner 2 is forcibly ignited when the core machine 1 does not reach the maximum state or when the core machine 1 is not started is avoided, so that the engine is overheated and burnt, and the use safety of the engine is improved.
The foregoing description is only illustrative of the preferred embodiments of the present invention and is not to be construed as limiting the scope of the invention, and it will be appreciated by those skilled in the art that equivalent substitutions and obvious variations may be made using the description and illustrations of the present invention, and are intended to be included within the scope of the present invention.
Claims (9)
1. The microminiature turbojet engine with the afterburner comprises a core machine (1) and a tail nozzle (3), and is characterized by further comprising the afterburner (2), wherein two ends of the afterburner (2) are respectively connected with the core machine (1) and the tail nozzle (3);
The core machine (1) comprises a compressor impeller (101), a core machine casing (102), a core machine combustion chamber (103), a turbine (104), a turbine guider (105), a main shaft (106), a support bearing (107), a spark plug (108), a core machine fuel pipe (109) and a compressor diffusion disc (110), wherein the compressor impeller (101), the core machine combustion chamber (103) and the turbine (104) are positioned in the core machine casing (102), the compressor impeller (101) and the turbine (104) are jointly installed on the main shaft (106) through the support bearing (107), the compressor impeller (101) is installed at the front end of the core machine casing (102) through the compressor diffusion disc (110), the turbine (104) is installed at the rear end of the core machine casing (102) through the turbine guider (105), the core machine combustion chamber (103) is arranged between the compressor impeller (101) and the turbine (104), the spark plug (108) is installed on the core machine casing (102), the ignition end of the spark plug (108) is installed at the core machine combustion chamber (103), and the ignition end of the spark plug (108) is communicated with a fuel tank (109) of the core machine;
The afterburner (2) comprises an afterburner casing (201), a diffusion type flame standing flow combustion stabilizing groove (202), an afterburner fuel pipe (203), a fuel atomizer (204), a gas-entraining hole (205), a gas-entraining one-way valve (206) and an afterburner matching surface (207), wherein the diffusion type flame standing flow combustion stabilizing groove (202) is arranged at the front end of the afterburner (2), the gas-entraining hole (205) corresponds to the position of the diffusion type flame standing flow combustion stabilizing groove (202), the gas-entraining one-way valve (206) is arranged in the gas-entraining hole (205), air is introduced through an external air pump to support combustion, the afterburner casing (201) is provided with the afterburner fuel pipe (203), the fuel is sprayed into the afterburner casing (2) through the annularly distributed fuel atomizer (204), the afterburner matching surface (207) is positioned in front of the tail nozzle (3) behind the diffusion type standing flow combustion stabilizing groove (202), and a clearance exists between the afterburner matching surface (207) and the afterburner casing (201);
The tail nozzle (3) is a subsonic convergent type tail nozzle and consists of a plurality of guide plates (301), and the convergence degree of the tail nozzle (3) is controlled by controlling the rotation angle of the guide plates (301) along the shaft.
2. A microminiature turbojet engine with afterburner according to claim 1, wherein the core engine (1) belongs to a centrifugal gas generator.
3. A micro turbojet engine with afterburner according to claim 1, characterized in that a support bearing (107) at the compressor wheel (101) connects the main shaft (106) with the compressor diffuser plate (110), and a support bearing (107) at the turbine wheel (104) connects the main shaft (106) with the turbine guide (105).
4. A microminiature turbojet engine with afterburner according to claim 1, wherein the diffusion type standing flow flame stabilizing groove (202) is constituted by an outer standing flow combustion stabilizing groove (212) and an inner standing flow combustion stabilizing groove (222), the diffusion opening angle of the inner standing flow combustion stabilizing groove (222) is the same as that of the outer standing flow combustion stabilizing groove (212).
5. A miniature turbojet engine with afterburner according to claim 1, characterized in that the afterburner casing (201) consists of several sections of casing, each section of casing being externally connected by casing external bolts.
6. A microminiature turbojet engine with afterburner according to claim 1, wherein the core (1), afterburner (2) and tail nozzle (3) are externally connected by means of external bolts.
7. The microminiature turbojet engine with the afterburner according to claim 1, wherein the afterburner fuel pipe (203) is connected with the core engine fuel pipe (109) through an external fuel pipeline, the fuel sources are the same as a main fuel tank, the same type of fuel is used for sharing one fuel pump and one gas-oil separator, an electromagnetic throttle valve is arranged at the joint of the core engine fuel pipe (109) and the afterburner fuel pipe (203), the electromagnetic throttle valve is opened when the core engine (1) is in a maximum state and afterburning is carried out, the minimum adjustment flow of the electromagnetic throttle valve is the critical ignition fuel supply amount of the afterburner, and the maximum adjustment flow is the critical temperature fuel supply amount of the afterburner.
8. A microminiature turbojet engine with afterburner according to claim 1, wherein the diameter of the largest diverging inner wall of the jet nozzle (3) is the same as the diameter of the afterburner mating surface (207), the afterburner being in a critical ignition state when the electromagnetic throttle valve is in a minimum throttle state, the jet nozzle (3) being in a minimum convergence state, the afterburner being in a critical temperature state when the electromagnetic throttle valve is in a maximum throttle state, the jet nozzle (3) being in a maximum diverging state, the jet nozzle (3) being also convergent in response to the core engine state if the afterburner is not open.
9. A micro-turbojet engine with afterburner according to claim 1, characterized in that the afterburner (2) is ignited by the gas after passing through the turbine (104).
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| Application Number | Priority Date | Filing Date | Title |
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| CN202510176172.2A CN119957384B (en) | 2025-02-18 | 2025-02-18 | With afterburners micro turbine jet engine |
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| Application Number | Priority Date | Filing Date | Title |
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| CN202510176172.2A CN119957384B (en) | 2025-02-18 | 2025-02-18 | With afterburners micro turbine jet engine |
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| CN119957384A CN119957384A (en) | 2025-05-09 |
| CN119957384B true CN119957384B (en) | 2025-11-18 |
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Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116201656A (en) * | 2023-03-10 | 2023-06-02 | 中国科学院工程热物理研究所 | Turbojet propulsion power system suitable for hypersonic cruising of unmanned aerial vehicle |
| CN118911867A (en) * | 2024-06-20 | 2024-11-08 | 清华大学 | Aeroengine with parallel stress application |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US7475545B2 (en) * | 2005-04-29 | 2009-01-13 | General Electric Company | Fladed supersonic missile turbojet |
| US7424805B2 (en) * | 2005-04-29 | 2008-09-16 | General Electric Company | Supersonic missile turbojet engine |
| CN115854383B (en) * | 2022-11-25 | 2025-05-30 | 四川航天中天动力装备有限责任公司 | An adjustable combined flame stabilization device suitable for turbine engines |
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Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN116201656A (en) * | 2023-03-10 | 2023-06-02 | 中国科学院工程热物理研究所 | Turbojet propulsion power system suitable for hypersonic cruising of unmanned aerial vehicle |
| CN118911867A (en) * | 2024-06-20 | 2024-11-08 | 清华大学 | Aeroengine with parallel stress application |
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