CN201367953Y - Vortex ramjet engine - Google Patents
Vortex ramjet engine Download PDFInfo
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- CN201367953Y CN201367953Y CNU2009200072358U CN200920007235U CN201367953Y CN 201367953 Y CN201367953 Y CN 201367953Y CN U2009200072358 U CNU2009200072358 U CN U2009200072358U CN 200920007235 U CN200920007235 U CN 200920007235U CN 201367953 Y CN201367953 Y CN 201367953Y
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Abstract
The utility model discloses a vortex ramjet engine, which adopts a brand-new air inletting method, fully uses the fluid motion to form a vortex having degressive rotate speed from the center to the periphery in a combustion chamber, and uses the vortex to lead the fuel and the air to be mixed evenly, thus leading the fuel to be fully combusted, reducing the burning loss to the inner wall of the combustion chamber, and forming a jet stream having degressive rotate speed from the center to the periphery simultaneously, wherein the jet stream has faster jet speed and stronger jet thrust. When being exerted with a high-speed air stream, the vortex ramjet engine can realize static state start. The vortex ramjet engine comprises a fuel system and an igniting system; the cross section of the inner chamber of the vortex ramjet engine is round; the inner chamber is provided with the combustion chamber and a jet chamber; the combustion chamber is communicated with the jet chamber, internally installed with an igniter, and provided with an air inlet; and the air inlet is connected with a spiral air inlet chamber.
Description
Technical field
The utility model relates to the air breathing engine field, specifically is a kind of vortex punching jetting engine.
Background technique
Existing air breathing engine mainly contains athodyd and turbojet engine, all there are a lot of defectives in they, for example: athodyd can't start under low speed, the turbojet engine cost is too high, their ubiquity fuel combustions are abundant inadequately, energy consumption is too high, the high inadequately defective of jet velocity.
The model utility content
The utility model provides a kind of vortex punching jetting engine of brand new, it can realize that low speed start also can realize static the startup, need not very high speed can keep burning work, swirl combustion, fuel combustion is abundant, jet velocity is higher, capacity usage ratio is higher, the rotating speed eddy current center of successively decreasing can produce higher temperature and pressure from the center to the periphery, make the hot merit conversion ratio higher, fuel concentrates on the eddy current central burner, concentration of energy is in eddy current center outburst, and the eddy current maskable high temperature that successively decreases of rotating speed can be avoided the casing wall scaling loss from the center to the periphery, wearing and tearing, jet-stream wind is the spiral air flow that successively decreases of rotating speed from the center to the periphery, has jet velocity and jet thrust faster.It is cheap, and it can bring the technological revolution of air breathing engine, can be widely used on various aircrafts, rocket, the aircraft.
The utility model is achieved through the following technical solutions to achieve these goals:
Vortex punching jetting engine comprises fuel system and igniting system, and vortex punching jetting engine inner chamber cross section is rounded, inner chamber is provided with firing chamber and nozzle chamber, and the firing chamber is communicated with nozzle chamber, mounting points firearm in the firing chamber, the firing chamber is provided with suction port, and suction port connects the spirally inlet air chamber.Be provided with gas-entered passageway in the suction port, the gas-entered passageway opening is towards firing chamber cross section tangent direction.The spirally inlet air chamber is provided with the spiral air flow passage.Middle part, spirally inlet air chamber is provided with cone.The vortex punching jetting engine inwall is provided with screw thread.The spirally inlet air chamber connects gas collecting tube.The spirally inlet air chamber connects blower fan, is provided with gas-entered passageway around the blower fan.
Advantage of the present utility model is: it has made full use of circular movement, utilized the effect of eddy current, fuel is fully mixed, fully burning, eddy current has prolonged the holdup time of air-flow in the firing chamber, help keeping burning more, make jet-stream wind form the spiral air flow that a rotating speed rotation of successively decreasing is from the center to the periphery advanced simultaneously, spiral air flow forms a taper sharp side, vertebra point high speed rotating, spiral air flow has fltting speed and bigger thrust faster just as the bullet of rotation, and the opening expansion of nozzle chamber makes jet-stream wind more not be vulnerable to the influence of air-flow on every side, has improved the speed of jet-stream wind more.The rotating speed eddy current center of successively decreasing can produce higher temperature and pressure from the center to the periphery, make the hot merit conversion ratio higher, fuel concentrates on the eddy current central burner, concentration of energy is in eddy current center outburst, and the eddy current maskable high temperature that successively decreases of rotating speed can be avoided casing wall scaling loss, wearing and tearing from the center to the periphery, the supercharging of spirally inlet air chamber has improved intake velocity greatly, make in the firing chamber suction port place form a positive pressure environment, avoided the hot plugging phenomenon greatly, make the vortex punching jetting engine can low speed start.The spirally inlet air chamber connects airduct, and airduct connects blower fan, is provided with gas-entered passageway around the airduct, can vortex punching jetting engine can be applied on all aircraft by static startup of high velocity air realization vortex punching jetting engine of blower fan generation.
Description of drawings
Embodiment
Vortex punching jetting engine comprises fuel system and igniting system, and vortex punching jetting engine inner chamber cross section is rounded, inner chamber is provided with firing chamber 3 and nozzle chamber 5, and the firing chamber is communicated with nozzle chamber, mounting points firearm 4 in the firing chamber, the firing chamber is provided with suction port 2, and suction port connects spirally inlet air chamber 6.Nozzle chamber's air inlet position cross sectional area is less than maximum cross section, firing chamber area.
The utility model vortex punching jetting engine can use pluralities of fuel, can use various liquid, gaseous fuel, also can use solid fuel, solid fuel can be ground into fine particle when using solid fuel, liquid or gaseous fuel can be with the direct transfer the fuels of fuel pipe, and liquid fuel is pressurized delivered a little, and liquid fuel can be established atomizer nozzle at the fuel mouth of pipe, gaseous fuel can utilize gas pressure to carry naturally, and solid fuel can be used gas delivery.Fuel pipe 14 imports can be located in the firing chamber, also can be located in the spirally inlet air chamber, are located in the spirally inlet air chamber to help fuel mix.
Can use coal as aviation fuel, only need coal is worn into fine powder, be purified, carry with high velocity air to get final product, can use the conventional fuel igniting, can use coal dust after the igniting.Use coal can reduce fuel cost greatly, can solve oil crisis.
The utility model vortex punching jetting engine igniting system comprises igniter, circuit, transformer, power supply etc., and igniter can be used spark plug, also available high-field electrode, also available plasma igniter.The igniter connecting circuit, circuit connects transformer and power supply gets final product.Igniter is installed in the firing chamber and gets final product, and can be installed near the puff prot of firing chamber, the tempering in the time of can reducing igniting.The utility model vortex punching jetting engine can prolong the working life of igniting system greatly in case igniting can be closed igniter.
The length ratio of the central axis of firing chamber and nozzle chamber can be selected 0.618: 0.382, the ratio of the length sum of firing chamber and nozzle chamber's central axis and maximum cross section, firing chamber diameter can be selected 1: 0.382, the ratio of the area of the area of firing chamber puff prot and maximum cross section, firing chamber can be selected 0.382: 1, the ratio of the area of firing chamber puff prot and the area of air inlet of combustion chamber can be selected between 1: 1 to 0.618: 1, air inlet of combustion chamber can be selected rectangular, rectangular long limit is parallel with the central axis of firing chamber, and the ratio of the length of the length on rectangular long limit and firing chamber central axis can be selected between 0.618: 1 to 0.382: 1.
Be provided with gas-entered passageway in the suction port, the gas-entered passageway opening is towards firing chamber cross section tangent direction, suction port is located at top of combustion chamber, can make air-flow enter the firing chamber along firing chamber cross section tangent direction, under the effect of firing chamber inwall, in the firing chamber, form the eddy current that successively decreases of rotating speed from the center to the periphery.
Suction port is provided with spirally inlet air chamber 6 outward, the ratio of the diameter of spirally inlet air chamber opening and the diameter of maximum cross section, firing chamber can be selected 1: 0.618, the lip limit of spirally inlet air chamber opening can select outer wall vertical, inwall to be formed slopely very thin blade-like lip limit, can alleviate gas current friction.
The spirally inlet air chamber is provided with the spiral air flow passage.Spirally inlet air chamber bottom angled, along forming a circular spiral air flow passage on the outer wall of combustion chamber screw, the spiral air flow passage forms a spirally inlet air chamber, can make air-flow form a high pressure draught that advances along the outer wall of combustion chamber rotation.
Middle part, spirally inlet air chamber is provided with cone 1, and the cone bottom surface equates that with the outer wall of combustion chamber maximum cross section point angle of cone 1 can be selected 55.62 degree, can make air motion smooth and easy, alleviates gas current friction, improves suction pressure simultaneously.
The vortex punching jetting engine inwall is established screw thread.In order to alleviate the friction of air-flow to the spirally inlet air chamber interior walls, can screw thread be set in spirally inlet air chamber interior walls and cone surface, for alleviating the friction of air-flow to firing chamber, nozzle chamber's inwall, can be in the firing chamber, nozzle chamber's inwall is provided with screw thread, screw thread and air-flow effect, can be in the spirally inlet air chamber, firing chamber, nozzle chamber's inwall form one deck shock wave, can reduce the wearing and tearing and the scaling loss of inwall.
Working principle: the utility model vortex punching motor can start under low-speed conditions, when reaching certain motion speed, air-flow is rushed in the spirally inlet air chamber, in the spirally inlet air chamber, form a high pressure draught that advances to the rotation of suction port direction around outer wall of combustion chamber, air communication is crossed gas-entered passageway and is rushed in the firing chamber along firing chamber cross section tangent direction, under the effect of firing chamber inwall, form the eddy current that successively decreases of rotating speed from the center to the periphery, when each point is made circular movement in the circle, the resistance that is subjected to from the circle center to the circle periphery when increasing progressively, will make gas in the field that enters this circular movement form the eddy current cyclone that successively decreases of rotating speed from the center to the periphery, air-flow needs to do ahead running along the running shaft direction of circular movement simultaneously just can make this eddy current cyclone form and keep existence, vortex movement just as water, the air motion of tornado is similar a bit, the center of eddy current cyclone has fltting speed faster, fltting speed also is to successively decrease from the center to the periphery, this just forms a taper sharp side, makes the swirling eddy at eddy current center have fltting speed and bigger thrust faster.The eddy current cyclone can make the fuel mixture that newly enters enter the eddy current center automatically, fuel produces heat energy in the eddy current central burner, energy can outwards transmit, there is a retardation in its transport velocity, this is because the energy loss in the energy transfer process causes, this just makes the transport velocity of heat energy from the eddy current center to the eddy current periphery have a retardation, making heat energy more accelerate eddy current cyclone rotating speed from the center to the periphery successively decreases, accelerated the rotating speed at eddy current center relatively, make energy more concentrate on the eddy current center, make and be formed centrally higher temperature and pressure in the eddy current, eddy current maskable energy can reduce the temperature and pressure of eddy current cyclone periphery simultaneously, reduction is to the scaling loss of firing chamber inwall, reduction can be used general material to the requirement of vortex punching engine material, can reduce cost greatly.The screw thread of firing chamber inwall can further improve eddy current rotating speed from the center to the periphery relatively and successively decrease, and the heat energy that fuel combustion is produced more concentrates on the eddy current center.
One of the utility model embodiment's structure is: the spirally inlet air chamber connects gas collecting tube 7 on one of embodiment's of the present utility model agent structure basis, gas collecting tube diameter and spirally inlet air chamber equal diameters, the gas collecting tube diameter also can improve suction pressure greater than spirally inlet air chamber diameter.Gas collecting tube and spirally inlet air chamber can be fabricated to one, and the gas collecting tube height can equate with the cone height, also can than circular cone low body some, specifically decide as required, gas collecting tube can increase spirally inlet air chamber air inflow, improves suction pressure.
The utility model embodiment's two structure is: on one of embodiment's of the present utility model architecture basics, the spirally inlet air chamber connects blower fan 9, is provided with gas-entered passageway 11 around the blower fan.The blower fan diameter can be identical with spirally inlet air chamber diameter, and blower fan can be located in the vortex punching motor also can be located at other position, can be connected with the vortex punching motor by airduct.
When blower fan is located in the vortex punching motor, the blower fan diameter can be identical with the firing chamber outer dia, the blower fan air outlet is over against the cone of spirally inlet air chamber, be provided with gas-entered passageway around the blower fan, be connected and fixed with sheet material 10 between blower fan and the vortex punching motor, sheet material constitutes gas-entered passageway each other, the sheet material top connects and is conical, conical point angle can be selected 55.62 degree, and taper shape can make air motion smooth and easy, can avoid foreign matter to enter simultaneously.
Present embodiment can realize that the static state of vortex punching jetting engine starts, start the blower fan rotation with external power supply during use and produce high velocity air, high velocity air makes the vortex punching motor realize igniting, when aircraft movements speed acquires a certain degree, can close blower fan, when aircraft movements speed drops to a certain degree, restart blower fan.For starting the blower fan running, can establish blower fan generating power supply on the aircraft in addition, can establish the generator that a common engine drives, generator for electricity generation is used to drive the blower fan running and also is used for other needs of aircraft simultaneously.
When blower fan is located in the vortex punching motor, also can utilize the blower fan generating, after in a single day aircraft realizes that high-speed motion is closed blower fan, high velocity air can drive the draught fan impeller high speed rotating, can utilize draught fan impeller to drive generator for electricity generation, power coil and actuating coil can be contained in the fan motor simultaneously.
For alleviating the friction of air-flow to the fan motor position, cone-shaped hood can be installed on fan motor, cone-shaped hood awl point is towards air-flow, point angle can be selected 55.62 degree for use, cone-shaped hood and draught fan impeller, gas-entered passageway etc. can be provided with the screw thread that becomes certain angle of inclination with the air motion direction with the position that air-flow produces friction, can alleviate frictional heat.
This programme can be applicable on all aircrafts, can replace existing all turbojet engines, pressed engine, can reduce the airplane engine manufacture cost greatly, cuts down the consumption of energy, reduces discharging greatly, improves flying speed greatly.
The technical solution of the utility model is not restricted in the embodiment's described in the utility model scope.The utility model not technology contents of detailed description is known technology.
Claims (7)
1, vortex punching jetting engine, comprise fuel system and igniting system, it is characterized in that: vortex punching jetting engine inner chamber cross section is rounded, inner chamber is provided with firing chamber (3) and nozzle chamber (5), the firing chamber is communicated with nozzle chamber, mounting points firearm (4) in the firing chamber, the firing chamber is provided with suction port (2), and suction port connects spirally inlet air chamber (6).
2, vortex punching jetting engine according to claim 1 is characterized in that: be provided with gas-entered passageway in the suction port, the gas-entered passageway opening is towards firing chamber cross section tangent direction.
3, vortex punching jetting engine according to claim 1 is characterized in that: the spirally inlet air chamber is provided with the spiral air flow passage.
4, vortex punching jetting engine according to claim 1 is characterized in that: middle part, spirally inlet air chamber is provided with cone (1).
5, vortex punching jetting engine according to claim 1 is characterized in that: the vortex punching jetting engine inwall is provided with screw thread.
6, according to claim 1,2,3,4 or 5 described vortex punching jetting engines, it is characterized in that: the spirally inlet air chamber connects gas collecting tube (7).
7, according to claim 1,2,3,4 or 5 described vortex punching jetting engines, it is characterized in that: the spirally inlet air chamber connects blower fan (9), is provided with gas-entered passageway (11) around the blower fan.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CNU2009200072358U CN201367953Y (en) | 2008-02-05 | 2009-01-21 | Vortex ramjet engine |
Applications Claiming Priority (3)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810014614.X | 2008-02-05 | ||
| CN200810014614 | 2008-02-05 | ||
| CNU2009200072358U CN201367953Y (en) | 2008-02-05 | 2009-01-21 | Vortex ramjet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN201367953Y true CN201367953Y (en) | 2009-12-23 |
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Family Applications (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CNU2009200072358U Expired - Fee Related CN201367953Y (en) | 2008-02-05 | 2009-01-21 | Vortex ramjet engine |
| CN200910003961A Pending CN101545415A (en) | 2008-02-05 | 2009-01-21 | Vortex punching jetting engine |
Family Applications After (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910003961A Pending CN101545415A (en) | 2008-02-05 | 2009-01-21 | Vortex punching jetting engine |
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| Country | Link |
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| CN (2) | CN201367953Y (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104110325A (en) * | 2014-07-30 | 2014-10-22 | 清华大学 | Combined cycle engine |
Families Citing this family (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104131915A (en) * | 2014-07-17 | 2014-11-05 | 张善沐 | Ramjet started in static state |
| US10167088B2 (en) * | 2015-10-19 | 2019-01-01 | General Electric Company | Crosswind performance aircraft engine spinner |
| CN106481457B (en) * | 2016-10-28 | 2017-11-24 | 西安近代化学研究所 | A kind of solid gas starter |
| CN109139297B (en) * | 2018-07-10 | 2019-06-07 | 西北工业大学 | A kind of device combining enhancing blending for solid-rocket scramjet engine |
-
2009
- 2009-01-21 CN CNU2009200072358U patent/CN201367953Y/en not_active Expired - Fee Related
- 2009-01-21 CN CN200910003961A patent/CN101545415A/en active Pending
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104110325A (en) * | 2014-07-30 | 2014-10-22 | 清华大学 | Combined cycle engine |
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| Publication number | Publication date |
|---|---|
| CN101545415A (en) | 2009-09-30 |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C14 | Grant of patent or utility model | ||
| GR01 | Patent grant | ||
| C17 | Cessation of patent right | ||
| CF01 | Termination of patent right due to non-payment of annual fee |
Granted publication date: 20091223 Termination date: 20120121 |