CN114607525A - Hydrogen fuel rotary ramjet turbofan engine - Google Patents
Hydrogen fuel rotary ramjet turbofan engine Download PDFInfo
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- CN114607525A CN114607525A CN202210339985.5A CN202210339985A CN114607525A CN 114607525 A CN114607525 A CN 114607525A CN 202210339985 A CN202210339985 A CN 202210339985A CN 114607525 A CN114607525 A CN 114607525A
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
- F02K7/10—Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
- F02K7/16—Composite ram-jet/turbo-jet engines
Abstract
The invention relates to a hydrogen fuel rotary ramjet turbofan engine, which comprises a fairing stator system, a ducted fan system and a rotary propulsion turbine rotor system, wherein the fairing stator system is connected with a fan inlet of a fan inlet; the fairing stator system comprises a fairing shell, a hollow shaft is arranged in the fairing shell, and a primary static flow sheet and a secondary static flow sheet are arranged on the hollow shaft; the ducted fan system comprises a fan; the rotary propulsion turbine rotor system comprises connecting shafts, the outer end of each connecting shaft is provided with a stamping propulsion runner, and the middle part and the tail part of an inner cavity of a pipe body of each stamping propulsion runner are respectively provided with a first spark plug and a second spark plug. The invention comprehensively utilizes the technologies of ducted fans, stamping propulsion, rotary propulsion, hydrogen fuel and the like to be integrated, researches a technology of a hydrogen fuel rotary stamping jet turbofan engine, and can greatly simplify the structure of the engine, reduce the manufacturing difficulty of the engine and expand the application of the hydrogen fuel in the aviation field.
Description
Technical Field
The invention relates to the field of aircraft engines, in particular to a hydrogen fuel rotary ramjet turbofan engine.
Background
At present, the turbine engine is mainly divided into a turbojet type, a turbofan type, a turboshaft type and the like, the structure of the turbine engine generally comprises a multistage compressor and a turbine mechanism, and the turbine needs to bear high rotating speed and high load caused by high-temperature, high-pressure and high-speed airflow, so that the engine is difficult to manufacture and high in price.
On the other hand, under the great trend of carbon reduction, hydrogen is used as power, and the problem of modification of the existing engine is solved.
Disclosure of Invention
The invention aims to provide a hydrogen fuel rotary ramjet turbofan engine which adopts hydrogen fuel as power and is applied to an aviation airplane. The invention provides a brand-new turbofan engine system architecture according to the characteristics of easy diffusion, high combustion speed and wide combustion concentration range of hydrogen fuel and by using the characteristics of simple structure and high compression efficiency at supersonic speed of the ramjet engine. The fan is a first-stage compressor; the plurality of stamping unit flows which are tangentially and symmetrically arranged form a rotary stamping engine, and the stamping engine works in an ideal working environment due to the supersonic tangential air flow; meanwhile, the tail gas of the ramjet engine is mixed with the cold air flow of the fan and then sprayed out backwards to provide final thrust, and the turbofan engine with the inner duct as a flow passage of the rotary ramjet engine and the outer duct as the outer duct outside the rotary ramjet engine is formed.
The invention is realized by the following technical scheme: the hydrogen fuel rotary ramjet turbofan engine comprises a fairing stator system, a ducted fan system and a rotary propulsion turbine rotor system;
the stator system of the fairing comprises a fairing shell, wherein the fairing shell is provided with a lip and a tail nozzle, a hollow shaft is arranged in the fairing shell along the extending direction from the lip to the tail nozzle, two ends of the hollow shaft are of a closed structure, the inner cavity of the hollow shaft can be connected and connected with a hydrogen source, a plurality of primary static flow sheets are radially arranged on the hollow shaft close to the lip, a plurality of secondary static flow sheets are radially arranged on the hollow shaft at the tail nozzle, the outer end parts of the primary static flow sheets and the secondary static flow sheets are fixedly connected with the inner wall of the fairing shell, and the inner end parts of the primary static flow sheets and the secondary static flow sheets are in rotating fit with the hollow shaft;
the ducted fan system comprises a fan which is fixedly arranged on a hollow shaft at a lip and consists of a plurality of blades, and the angle of the blades of the fan relative to the hollow shaft can enable air to enter from the lip and be sprayed out through a tail nozzle;
the rotary propulsion turbine rotor system comprises at least two connecting shafts fixedly arranged on a hollow shaft, the outer end part of each connecting shaft is correspondingly provided with a bent-tube-shaped stamping propulsion flow passage, the bending direction of the stamping propulsion flow passage enables an air inlet to be close to a first-stage static flow sheet and a nozzle to be close to a second-stage static flow sheet, the bending direction of the stamping propulsion flow passage can promote a fan to rotate along with the hollow shaft, the middle part and the tail part of a pipe body inner cavity of the stamping propulsion flow passage are respectively provided with a first spark plug and a second spark plug, the cross section area of the pipe body inner cavity of the stamping propulsion flow passage at the second spark plug is gradually increased from the air inlet direction to the air injection direction, the middle part of each connecting shaft is provided with a cavity communicated with the inner cavity of the hollow shaft, a starting air inlet pipe and a working air inlet pipe are arranged in the cavity of each connecting shaft, and valves are respectively arranged on the starting air inlet pipe and the working air inlet pipe, and the starting air inlet pipe can be communicated to the position of a second spark plug of the stamping propulsion flow passage, and the working air inlet pipe can be communicated to the position of a first spark plug of the stamping propulsion flow passage.
As a further improvement of the technical scheme of the invention, the cross-sectional area of the inner cavity of the tube body of the stamping propulsion runner is gradually reduced from the air inlet and then gradually increased to form a stamping combustion chamber, and then gradually reduced and gradually increased when reaching the nozzle; the first spark plug is located within the ram combustion chamber.
As a further improvement of the technical scheme of the invention, the cross sectional area of the inner cavity of the tube body of the stamping propulsion flow passage at the air inlet is larger than that of the inner cavity of the tube body of the stamping propulsion flow passage at the nozzle.
As a further improvement of the technical scheme of the invention, the hydrogen source is an external hydrogen storage tank arranged outside the rectifying shell.
As a further improvement of the technical scheme of the invention, a hydrogen conveying pipeline which can be communicated with an external hydrogen storage tank is arranged in the rectifying shell body, a static flow sheet hydrogen conveying pipeline which can be communicated with the hydrogen conveying pipeline is arranged in the body of at least one secondary static flow sheet, and the static flow sheet hydrogen conveying pipeline can be communicated with the inner cavity of the hollow shaft.
As a further improvement of the technical scheme of the invention, at least one electric heating wire is arranged in the body of the second-stage static flow sheet corresponding to the static flow sheet hydrogen conveying pipeline.
As a further improvement of the technical scheme of the invention, the first-stage static flow sheet and the second-stage static flow sheet both have symmetrical airfoil-shaped thin plate structures, and the blunt end of each thin plate structure faces the lip and the blade end faces the tail nozzle.
As a further improvement of the technical scheme of the invention, the outer diameter of the rectifying shell is gradually reduced after gradually increasing from the lip to the tail nozzle.
As a further improvement of the technical scheme of the invention, the first-stage static flow sheet is in running fit with the hollow shaft through a bearing, and the second-stage static flow sheet is in running fit with the hollow shaft through a rotary joint.
Compared with the prior art, the hydrogen fuel rotary ramjet turbofan engine has the following beneficial effects:
1. the invention comprehensively utilizes the technologies of ducted fans, stamping propulsion, rotary propulsion, hydrogen fuel and the like to be integrated, researches a technology of a hydrogen fuel rotary stamping jet turbofan engine, and can greatly simplify the structure of the engine, reduce the manufacturing difficulty of the engine and expand the application of the hydrogen fuel in the aviation field.
2. The working environment of the invention is still under the subsonic speed condition, and the characteristic of the linear velocity of the outer diameter of the high-speed rotating impeller is only artificially utilized, and the ramjet engine is ingeniously utilized to propel the ducted fan to rotate, namely the prior engine utilizes axial high-speed airflow to propel the turbine to rotate, and utilizes circumferential propulsion instead, so that the multistage air compressing mechanism can be simplified, and the processing and manufacturing difficulty of the impeller, namely the turbine, can be reduced.
3. The invention reduces the ramjet engine to the nozzle of the ramjet propulsion runner in equal proportion, namely, the axial direction of the combustion chamber is shortened, the mixing time of fuel and air is shortened, but the defects of good hydrogen diffusivity, high burning speed and wide burning concentration (4-74%) are overcome.
Drawings
In order to more clearly illustrate the embodiments of the present invention or the technical solutions in the prior art, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are some embodiments of the present invention, and other drawings can be obtained by those skilled in the art without creative efforts.
FIG. 1 is an exploded schematic view of a hydrogen fueled rotary ramjet turbofan engine according to the present invention.
FIG. 2 is a schematic view of the internal structure of a hydrogen fueled rotary ramjet turbofan engine according to the present invention.
FIG. 3 is a schematic structural view of the dome stator system.
FIG. 4 is a top view of the dome stator system.
FIG. 5 is a schematic view of a ducted fan system in cooperation with a cowl stator system.
FIG. 6 is a front view of the ducted fan system.
FIG. 7 is an external schematic view of the rotary propulsion turbine rotor system.
FIG. 8 is a detailed schematic connection diagram of the rotary propulsion turbine rotor system.
Fig. 9 is a schematic view of the connection between one of the connecting shafts and the ram propulsion runner.
Fig. 10 is a schematic structural view of the punching propulsion runner.
Fig. 11 is a schematic connection diagram of the hydrogen pipeline and the static flow sheet hydrogen pipeline.
In the figure: 1-a fairing stator system, 101-a fairing shell, 102-a primary static flow sheet, 103-a secondary static flow sheet, 104-a hollow shaft, 105-a bearing, 106-a rotary joint, 107-a hydrogen conveying pipeline, 108-a static flow sheet hydrogen conveying pipeline and 109-a heating wire;
2-ducted fan system, 201-fan;
3-rotating propulsion turbine rotor system, 301-connecting shaft, 302-ram propulsion flow channel, 303-starting air inlet pipe, 304-working air inlet pipe, 305-starting air inlet valve, 306-working air inlet valve, 307-first spark plug, 308-air inlet, 309-ram combustion chamber, 310-nozzle and 311-second spark plug.
Detailed Description
The technical solutions of the present invention are described clearly and completely below, and it is obvious that the described embodiments are some, not all embodiments of the present invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.
In the description of the present invention, it should be noted that the terms "first" and "second" are used for descriptive purposes only and are not to be construed as indicating or implying relative importance.
In the description of the present invention, it should be noted that, unless otherwise explicitly specified or limited, the terms "mounted," "connected," and "connected" are to be construed broadly, e.g., as meaning either a fixed connection, a removable connection, or an integral connection; can be mechanically or electrically connected; they may be connected directly or indirectly through intervening media, or they may be interconnected between two elements. The specific meanings of the above terms in the present invention can be understood in specific cases to those skilled in the art.
1-11, the present invention provides a specific embodiment of a hydrogen fueled rotary ramjet turbofan engine, comprising a cowling stator system 1, a ducted fan system 2, a rotary propulsion turbine rotor system 3;
the fairing stator system 1 comprises a fairing shell 101, wherein the fairing shell 101 is provided with a lip and a tail nozzle, a hollow shaft 104 is arranged in the fairing shell 101 along the extending direction from the lip to the tail nozzle, two ends of the hollow shaft 104 are of a closed structure, the inner cavity of the hollow shaft 104 can be connected with a hydrogen source, a plurality of primary static flow sheets 102 are radially arranged on the hollow shaft 104 close to the lip, a plurality of secondary static flow sheets 103 are radially arranged on the hollow shaft 104 at the tail nozzle, the outer end parts of the primary static flow sheets 102 and the secondary static flow sheets 103 are fixedly connected with the inner wall of the fairing shell 101, and the inner end parts of the primary static flow sheets 102 and the secondary static flow sheets 103 are in rotating fit with the hollow shaft 104;
the ducted fan system 2 comprises a fan 201 which is fixedly arranged on a hollow shaft 104 at a lip and is composed of a plurality of blades, and the angle of the blades of the fan 201 relative to the hollow shaft 104 can enable air to enter from the lip and be sprayed out through a tail nozzle;
the rotary propulsion turbine rotor system 3 comprises at least two connecting shafts 301 fixedly arranged on the hollow shaft 104, the outer end of each connecting shaft 301 is correspondingly provided with a bent-tube-shaped stamping propulsion flow passage 302, the bending direction of the stamping propulsion flow passage 302 enables an air inlet 308 to be close to the first-stage static flow sheet 102 and a nozzle 310 to be close to the second-stage static flow sheet 103, the bending direction of the stamping propulsion flow passage 302 can promote the fan 201 to rotate along with the hollow shaft 104, the middle part and the tail part of the inner cavity of the tube body of the stamping propulsion flow passage 302 are respectively provided with a first spark plug 307 and a second spark plug 311, the cross-sectional area of the inner cavity of the tube body of the stamping propulsion flow passage 302 at the second spark plug 311 is gradually increased from the air inlet direction to the air injection direction, the middle part of the connecting shaft 301 is provided with a cavity communicated with the inner cavity of the hollow shaft 104, and a starting air inlet pipe 303 and a working air inlet pipe 304 are arranged in the cavity of the connecting shaft 301, valves are respectively arranged on the starting air inlet pipe 303 and the working air inlet pipe 304, the starting air inlet pipe 303 can be communicated to the position of a second spark plug 311 of the ram propulsion flow passage 302, and the working air inlet pipe 304 can be communicated to the position of a first spark plug 307 of the ram propulsion flow passage 302.
Specifically, in the present embodiment, the start intake valve 305 is provided in the start intake pipe 303, and the work intake valve 306 is provided in the work intake pipe 304. In order to adapt the amount of intake air in the start intake pipe 303 and the working intake pipe 304 to the operating conditions, it is preferable that the inner diameter of the working intake pipe 304 is larger than the inner diameter of the start intake pipe 303.
As shown in fig. 8 to 10, taking a ramjet engine formed by one of the connecting shaft 301 and the ram propulsion runner 302 as an example, during the starting process, the working intake valve 306 is closed, the starting intake valve 305 is opened, hydrogen enters the starting intake pipe 303 through the connecting shaft 301, then enters the tail portion of the ram propulsion runner 302, the hydrogen entering the tail portion of the ram propulsion runner 302 is mixed with air and then ignited by the second spark plug 311, since the cross-sectional area of the inner cavity of the pipe body of the ram propulsion runner 302 at the second spark plug 311 gradually increases from front to back, and is in a flared shape, the hot air flow after the combustion at the tail portion of the ram propulsion runner 302 is ejected downward and rearward, and further the rotary propulsion turbine rotor system 3 is pushed to rotate (clockwise rotation as shown in fig. 8), the hollow shaft 104 fixedly connected with the connecting shaft 301 is driven to rotate, and further the fan 201 in the ducted fan system 2 is driven to rotate, the fan 201 rotating at a high speed can introduce air into the rectifying case 101 from the lip after pressurizing the air; after the rotation speed of the fan 201 is increased to the rated working rotation speed (that is, the relative flow rate of the gas at the air inlet 308 of the stamping propulsion flow channel 302 reaches supersonic speed), the starting air inlet valve 305 is closed, the working air inlet valve 306 is opened, the hydrogen enters the middle part of the stamping propulsion flow channel 302 through the working air inlet pipe 304, the hydrogen entering the middle part of the stamping propulsion flow channel 302 is mixed with the air entering from the front part of the stamping propulsion flow channel 302 and then is ignited through the first spark plug 307, and the hot air flow formed by combustion is ejected downwards and backwards to enter a normal working state.
When the thrust of the rotary propulsion turbine rotor system 3 needs to be adjusted, the working air inlet valve 306 is a flow valve, and the flow of hydrogen entering the stamping propulsion flow channel 302 can be adjusted by controlling the working air inlet valve 306, so as to control the rotating speed of the rotary propulsion turbine rotor system 3, thereby realizing the adjustment of the engine thrust.
In the present embodiment, the first-stage static flow vanes 102 function to rectify the vortex flow introduced into the rectifying casing 101 into a stable laminar flow. The secondary static flow sheet 103 plays a role in rectifying the eddy current of the hot air flow into a stable laminar flow.
As shown in fig. 8 to 10, in order to enable the ram propulsion runner 302 to enter the working state more quickly during the high-speed rotation process, the cross-sectional area of the inner cavity of the tube body of the ram propulsion runner 302 is gradually reduced from the air inlet 308, gradually increased to form the ram combustion chamber 309, then gradually reduced, and gradually increased when reaching the nozzle 310; the first spark plug 307 is located within a ram combustion chamber 309. The inlet 308 is of a closed type, and mainly functions that in a high-speed rotation process, the linear speed of the inlet 308 moves in a supersonic speed state, and the closed type inlet 308 reduces supersonic speed airflow to a subsonic speed state and enters the stamping combustion chamber 309. The stamping combustion chamber 309 is in a configuration of flaring before closing, the first spark plug 307 is located at the position where the cross-sectional area of the inner cavity of the tube body is maximum, air entering from the air inlet 308 is reduced to subsonic speed, the flow speed is continuously reduced at the flaring section, then the air is mixed with hydrogen, ignition combustion is carried out through the first spark plug 307, and high-temperature and high-pressure subsonic air flow enters the nozzle 310 after being lifted to supersonic speed through the closing section. The nozzle 310 is in a flared horn shape, the high-temperature and high-pressure supersonic air flow expands through the flared nozzle 310 to continuously increase the flow rate, and finally the supersonic air flow is ejected outwards to provide a rotary thrust for the rotary propulsion turbine rotor system 3, the rotary thrust acts on the rotary propulsion turbine rotor system 3 to drive the hollow shaft 104 and the ducted fan system 2 to rotate, and the hot air flow ejected from the nozzle 310 is mixed with cold air compressed by the fan 201 of the ducted fan system 2 and then ejected backwards to provide power for the engine.
In order to facilitate air to enter the ram propulsion runner 302 more smoothly, the cross-sectional area of the inner cavity of the ram propulsion runner 302 at the air inlet 308 is larger than that of the inner cavity of the ram propulsion runner 302 at the nozzle 310.
Specifically, the hydrogen source is an external hydrogen storage tank disposed outside the rectification housing 101. The external hydrogen storage tank may be specifically installed in the fuselage of the aircraft.
The invention also provides a communication mode of the external hydrogen storage tank and the hollow shaft 104, namely a hydrogen conveying pipeline 107 capable of being communicated with the external hydrogen storage tank is arranged in the shell body of the rectifying shell 101, a static flow sheet hydrogen conveying pipeline 108 capable of being communicated with the hydrogen conveying pipeline 107 is arranged in the body of at least one second-stage static flow sheet 103, and the static flow sheet hydrogen conveying pipeline 108 can be communicated with the inner cavity of the hollow shaft 104. In this embodiment, a plurality of air inlets are circumferentially opened on the hollow shaft 104 located at the position of the hydrogen transport pipe 108 of the static flow sheet, and even in the process of high-speed rotation of the hollow shaft 104, the hydrogen transport pipe 108 of the static flow sheet can supply air into the hollow shaft 104 through the air inlets.
When the external hydrogen storage tank stores liquid hydrogen in the embodiment, in order to ensure that the liquid hydrogen flowing out of the external hydrogen storage tank is gaseous hydrogen when reaching the hollow shaft 104, at least one heating wire 109 is arranged in the sheet body of the second-stage static flow sheet 103 corresponding to the static flow sheet hydrogen conveying pipeline 108. In this embodiment, not only the heating wire 109 can heat the ultra-low temperature liquid hydrogen, but also the hot air flow formed by combustion at the stamping propulsion runner 302 can heat the liquid hydrogen in the static flow sheet hydrogen transmission pipeline 108 at the secondary static flow sheet 103, so that the liquid hydrogen can be vaporized by heat exchange.
Referring to fig. 4, the present invention provides an embodiment of the primary static flow sheet 102 (which can also be an embodiment of the secondary static flow sheet 103), wherein the primary static flow sheet 102 and the secondary static flow sheet 103 both present a thin plate structure with symmetrical airfoil shape, and the blunt end of the thin plate structure faces the lip and the cutting edge faces the tail nozzle. In this embodiment, preferably, the first-stage static flow sheets 102 and the second-stage static flow sheets 103 correspond to each other in number and direction.
As shown in fig. 2, the primary static sheet 102 in the present embodiment is located in the rectifying casing 101 at the total length (height of the rectifying casing 101) from the lip 1/3.
In order to optimize the flow field, in the present embodiment, the outer diameter of the fairing body 101 gradually increases from the lip to the tail nozzle and then gradually decreases.
In order to facilitate the hollow shaft 104 to rotate along the center of the primary static sheet 102 and the secondary static sheet 103, the primary static sheet 102 is rotatably engaged with the hollow shaft 104 through a bearing 105, and the secondary static sheet 103 is rotatably engaged with the hollow shaft 104 through a rotary joint 106. When a static flow sheet hydrogen conveying pipeline 108 capable of being communicated with the hydrogen conveying pipeline 107 is arranged in the sheet body of the secondary static flow sheet 103, in order to facilitate the static flow sheet hydrogen conveying pipeline 108 to be communicated with the inner cavity of the hollow shaft 104, the rotary joint 106 adopts a pneumatic rotary joint which is a mechanism for conveying stator end gas to a rotary end, the inner structure of the pneumatic rotary joint comprises a bearing and a sealing structure, the hollow shaft 104 only needs to be connected with the rotary end shaft of the pneumatic rotary joint to convey the stator end hydrogen into the hollow shaft 104, and hydrogen is guaranteed not to be leaked. As will occur to those skilled in the art.
For a particular application, a control system may be employed to control the opening and closing of the start intake valve 305, the service intake valve 306, the external hydrogen tank, and the respective spark plugs.
Finally, it should be noted that: the above embodiments are only used to illustrate the technical solution of the present invention, and not to limit the same; while the invention has been described in detail and with reference to the foregoing embodiments, it will be understood by those skilled in the art that: the technical solutions described in the foregoing embodiments may still be modified, or some or all of the technical features may be equivalently replaced; and the modifications or the substitutions do not make the essence of the corresponding technical solutions depart from the scope of the technical solutions of the embodiments of the present invention.
Claims (9)
1. The hydrogen fuel rotary ramjet turbofan engine is characterized by comprising a fairing stator system (1), a ducted fan system (2) and a rotary propulsion turbine rotor system (3);
the stator system (1) of the fairing comprises a fairing shell (101), wherein the fairing shell (101) is provided with a lip and a tail nozzle, a hollow shaft (104) is arranged in the fairing shell (101) along the extending direction from the lip to the tail nozzle, two ends of the hollow shaft (104) are of a closed structure, the inner cavity of the hollow shaft (104) can be connected with a hydrogen source, a plurality of primary static flow sheets (102) are radially arranged on the hollow shaft (104) close to the lip, a plurality of secondary static flow sheets (103) are radially arranged on the hollow shaft (104) at the tail nozzle, the outer end parts of the primary static flow sheets (102) and the secondary static flow sheets (103) are fixedly connected with the inner wall of the fairing shell (101), and the inner end parts of the primary static flow sheets (102) and the secondary static flow sheets (103) are in running fit with the hollow shaft (104);
the ducted fan system (2) comprises a fan (201) which is fixedly arranged on a hollow shaft (104) at a lip and is composed of a plurality of blades, wherein the angle of the blades of the fan (201) relative to the hollow shaft (104) can enable air to enter from the lip and be sprayed out through a tail nozzle;
the rotary propulsion turbine rotor system (3) comprises at least two connecting shafts (301) fixedly arranged on a hollow shaft (104), the outer end of each connecting shaft (301) is correspondingly provided with a bent-tube-shaped stamping propulsion flow passage (302), the bending direction of each stamping propulsion flow passage (302) enables an air inlet (308) to be close to a first-stage static flow sheet (102) and a nozzle (310) to be close to a second-stage static flow sheet (103), the bending direction of each stamping propulsion flow passage (302) can promote a fan (201) to rotate along with the hollow shaft (104), the middle part and the tail part of a pipe body inner cavity of each stamping propulsion flow passage (302) are respectively provided with a first spark plug (307) and a second spark plug (311), the cross sectional area of the pipe body inner cavity of each stamping propulsion flow passage (302) at the second spark plug (311) is gradually increased from the air inlet direction to the air outlet direction, and the middle part of each connecting shaft (301) is provided with a cavity communicated with the inner cavity of the hollow shaft (104), and a starting air inlet pipe (303) and a working air inlet pipe (304) are arranged in a cavity of the connecting shaft (301), valves are respectively arranged on the starting air inlet pipe (303) and the working air inlet pipe (304), the starting air inlet pipe (303) can be communicated to the position of a second spark plug (311) of the stamping propulsion flow channel (302), and the working air inlet pipe (304) can be communicated to the position of a first spark plug (307) of the stamping propulsion flow channel (302).
2. The hydrogen-fueled rotary ramjet turbofan engine according to claim 1 wherein the cross-sectional area of the inner cavity of the body of the ramjet runner (302) gradually decreases from the inlet port (308), then gradually increases to form a ramjet combustion chamber (309), then gradually decreases, and then gradually increases to the nozzle (310); the first spark plug (307) is located within a ram combustion chamber (309).
3. The hydrogen-fueled rotary ramjet turbofan engine of claim 1 wherein a cross sectional area of a body lumen of the ramjet motive flow path (302) at the inlet port (308) is greater than a cross sectional area of a body lumen of the ramjet motive flow path (302) at the outlet port (310).
4. The hydrogen-fueled rotary ramjet turbofan engine according to claim 1 wherein the hydrogen source is an external hydrogen storage tank disposed outside of the fairing housing (101).
5. The hydrogen-fueled rotary ramjet turbofan engine according to claim 4, wherein a hydrogen transportation pipe (107) capable of communicating with an external hydrogen storage tank is provided in a body of the rectifying case (101), a static sheet hydrogen transportation pipe (108) capable of communicating with the hydrogen transportation pipe (107) is provided in a body of the at least one secondary static sheet (103), and the static sheet hydrogen transportation pipe (108) is capable of communicating with an inner cavity of the hollow shaft (104).
6. The hydrogen-fueled rotary ramjet turbofan engine according to claim 5, wherein at least one heating wire (109) is provided in a body of the secondary static sheet (103) corresponding to the static sheet hydrogen transportation pipe (108).
7. The hydrogen-fueled rotary ramjet turbofan engine according to claim 1 wherein the primary and secondary static flow vanes (102, 103) each present a thin plate structure of symmetrical airfoil shape with a blunt end facing the lip and a sharp end facing the aft jet.
8. The hydrogen-fueled rotary ramjet turbofan engine according to claim 1 wherein the outer diameter of the fairing housing (101) gradually increases and then gradually decreases from the lip to the jet nozzle.
9. The hydrogen-fueled rotary ramjet turbofan engine according to claim 1 wherein the primary vane (102) is rotationally engaged with the hollow shaft (104) by a bearing (105) and the secondary vane (103) is rotationally engaged with the hollow shaft (104) by a rotary joint (106).
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| Publication number | Priority date | Publication date | Assignee | Title |
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| CN115463566A (en) * | 2022-09-29 | 2022-12-13 | 上海蕙黔新材料科技有限公司 | Oxygen mixer for gas phase carbonyl synthesis of dimethyl carbonate |
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| CN115463566A (en) * | 2022-09-29 | 2022-12-13 | 上海蕙黔新材料科技有限公司 | Oxygen mixer for gas phase carbonyl synthesis of dimethyl carbonate |
| CN115463566B (en) * | 2022-09-29 | 2023-09-26 | 上海蕙黔新材料科技有限公司 | Oxygen mixer for synthesizing dimethyl carbonate by gas phase method carbonyl |
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| CN114607525B (en) | 2022-07-19 |
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