CN1382903A - Supersonic swirl boosted propulsion engine - Google Patents
Supersonic swirl boosted propulsion engine Download PDFInfo
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- CN1382903A CN1382903A CN 02116220 CN02116220A CN1382903A CN 1382903 A CN1382903 A CN 1382903A CN 02116220 CN02116220 CN 02116220 CN 02116220 A CN02116220 A CN 02116220A CN 1382903 A CN1382903 A CN 1382903A
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- combustion chamber
- chamber
- eddy combustion
- swirl
- boosted
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Abstract
A very supersonic (M3-13) propulsion engine boosted by swirl is sequentially composed of regulatable inlet channel, swirlgenerator, swirl boosting diameter-variable short pipe, swirl combustion chamber, deswirling unit, convergent segment and expanded tail pipe. Its advantages are high pressure and density of input air of combustion chamber, high reaction rate of combustion reaction.
Description
Technical field
The present invention relates to a kind of motor, particularly relate to a kind of vortex supercharging propelling motor.
Technical background
Explanation of nouns: the M number of speed is meant the ratio of this speed with velocity of sound in the same medium.
Modern aeroengine mainly can be divided into reciprocating engine, gas turbine engine and pressed engine three major types.Gas turbine engine can be divided into turbojet engine, turbofan engine, turboprop engine, turboaxle motor, its common ground is that air-flow is through the gas compressor supercharging, arrive combustion chambers burn again, high-pressure gas from the afterbody ejection, promotes aircraft and advances after driving gas turbine.Pressed engine is divided into subsonic speed, supersonic speed, hypersonic ramjet engine, and its common ground is air-flow process intake duct (having another name called Diffuser) supercharging earlier, arrives combustion chambers burn again, enters the jet pipe ejection at last.Wherein the subsonic speed pressed engine has expansion shape subsonic inlet, constrictor nozzle, and the supercharging air ratio is not more than 1.89, and the M value is not less than 0.5; The supersonic speed pressed engine has supersonic speed super charge road, convergence or con-dinozzle, M value 1-6; Hypersonic ramjet engine M value 5-16, fuel burns in supersonic airstream.The gas turbine engine complex structure, quality is big, and the M number of upper limit flying speed is generally less than 3; And the M number of the upper limit flying speed of pressed engine is generally less than 6.When the M of flying speed number greater than 6 the time, air-flow will pass the firing chamber at a terrific speed, therefore, require fuel under the ultraspeed state, to burn, but because the firing chamber can not be done very longly, air and fuel are too short in the time of contact of firing chamber, can't complete reaction, and cause combustion efficiency to increase and hurried decline with the firing chamber air velocity.Insufficient lifting that restricts its operating rate of burning.So existing aeroengine realizes that in actual applications the M number of its flying speed has great difficulty greater than 6.
Technology contents
The objective of the invention is in order to overcome above deficiency, a kind of vortex supercharging propelling motor is provided, can improve the combustion reaction rate of fuel effectively by the utmost point, thereby promote its upper limit flying speed greatly.
To achieve these goals, the invention provides a kind of supersonic swirl boosted propulsion engine, it comprises that the variable geometry inlet, a cyclone, the vortex supercharging that connect in turn become diameter short tube, eddy combustion chamber, separate cyclone, converging portion and expansion jet pipe; Fuel send endless tube injection back to flow to fuel jet orifice along the mezzanine space of the inside and outside wall of corresponding construction from the fuel collection.
This motor adopts unique vortex pressurized combustion technology, promptly playing cyclone rises air stream and revolves, pressurize through vortex supercharging change diameter short tube again and enter the eddy combustion chamber, the vortex air eddy combustion indoor with spray into fuel biochemical reaction of hybrid concurrency under the vortex flow state of firing chamber, fuel is fully burned, the combustion gas that is generated is untwisted by separating cyclone, and last combustion gas accelerates to the motor ear end face from the expansion of expansion jet pipe do and sprays at a high speed.Because vortex pressurized combustion technology employing in the present invention, compare pressed engine noted earlier, increased the pressure of gas in the firing chamber, prolonged gas being detained the time in the firing chamber, and the combustion reaction of the air mass on the different vortex streamlines is mutually promoted, thereby effectively improved the reactivity of fuel and air, be fit at a cover under the fuel and cooling system support of this system, the Driving force of hypersonic flight can be obtained, and continuous efficient operation can be in the velocity range of M3-13, realized.
Description of drawings
Fig. 1 is the sectional view of embodiments of the invention 1.
Fig. 2 is the through-flow figure of embodiments of the invention 1.
Fig. 3 be embodiments of the invention 1 the vortex supercharging become diameter short tube sectional view.
Fig. 4 is the sectional view of embodiments of the invention 2.
Fig. 5 looks partial sectional view for the master of embodiments of the invention 3.
Fig. 6 is the partial sectional view of overlooking of embodiments of the invention 3.
Specific implementation
The present invention is described in further detail below in conjunction with drawings and Examples.
At first see integral frame of the present invention, comprise that the variable geometry inlet, a cyclone, the vortex supercharging that connect in turn become diameter short tube, eddy combustion chamber, separate cyclone, converging portion and expansion jet pipe.High-speed air flow is entered by variable geometry inlet, tentatively compressed, the cyclone of having flowed through again becomes vortex flow, through entering the eddy combustion chamber behind the vortex supercharging change diameter short tube, fully mix, burn with the fuel that sprays at firing chamber inside vortex air-flow, the combustion gas that is generated is untwisted by separating cyclone, and design makes its M value be not less than 1 when flowing to the smallest cross-sectional of converging portion, last combustion gas accelerates to the motor ear end face from the expansion of expansion jet pipe do and sprays at a high speed, obtains hypersonic thrust power.
Its fuel is to send endless tube to be infused in the interlayer between the inside and outside wall from the fuel collection to spray from fuel jet orifice at last.
Be specifically addressed below in conjunction with embodiment.
Embodiment 1
As shown in Figure 1, (M 〉=1) air stream enters variable geometry inlet (1) from motor head at a high speed, variable geometry inlet has it by the import of intake duct controller (4) adjusting intake duct (1) and requires corresponding to intake area, air stream is tentatively compressed behind variable geometry inlet (1), become vortex flow through playing propeller runner (26) then, vortex flow enters the vortex supercharging and becomes diameter short tube (6) and enter eddy combustion chamber (9) then in the zone of high pressure, fuel jet orifice (23 is arranged in the firing chamber, 24), vortex flow and the past back fuel jet orifice (24,23) Pen Chu fuel mixes under the vortex flow state, reaction forms the vortex combustion gas, combustion gas is flowed out rear driving power turbine (11) end of flowing through again and is separated propeller runner (12) untwisted fully (just separate propeller runner and separate the cyclone of separating that propeller runner is combined into present embodiment with the end) from just separating cyclone, then pass through converging portion (13) and make air-flow M number 〉=1 that flow to throat section (being the smallest cross-sectional of converging portion), last air-flow expands along expansion jet pipe (15) and quickens ejection motor terminal surface.The momentum flow of high speed discharging jet and the momentum difference in flow of inlet stream promptly form jet thrust.This thrust is the summation of the whole component pressures of motor on microcosmic.Certainly final net thrust in fact also should be deducted the outer gas stream resistance of motor.
The fuel of present embodiment is carried again.Present embodiment will be distributed to forward and backward fuel collection from the fuel that petrolift provides and send endless tube (5,14).Preceding fuel collection send the fuel in the endless tube (5) to flow backward along inside and outside wall mezzanine space, sprays into eddy combustion chamber (9) from the preceding fuel jet orifice (24) that is periphery behind the absorption inwall heat.Back fuel collection send the fuel in the endless tube to flow forward and separate propeller runner (12) root at the end along the folded space of inside and outside wall and forms two branches: a continuation flows to the back fuel jet orifice (23) that is periphery forward; spray into the eddy combustion chamber; another separates each blade endoporus of propeller runner (12) along the end; numerous micropores from the blade front portion after the inflow blade interior spray; blade is formed reducing agent film cooling protection adhesive layer; some polymerization in propeller runner center tail cone (16) is separated at the end flows into turbine hub (17) inner chamber; center hole along turbine blade flows in the blade and finally numerous micropores ejections from the blade front portion again, and turbine blade is formed the cooling of reducing agent film.
See the cooling of present embodiment below to other structures.Freezing mixture (generally being nitrogen) is after the center hole injection of eddy impeller blade; part freezing mixture is from numerous micropore ejections of blade front portion; blade is formed freezing mixture film cooling protection; remaining part has then flowed into and has revolved chamber center tube (25); its sub-fraction forward forms the film cooling of Taper Pipe outer wall thereafter from the most advanced and sophisticated spray orifice ejection of propeller runner SMIS nose cone (2).Most of in addition freezing mixture is flowed through backward and is separated core awl (8) (cut apart the core awl and be and make vortex flow only enter the eddy combustion chamber from the zone of high pressure that the vortex supercharging becomes the diameter short tube), center tube (20) and the bead filler that just untwists awl (19) and enter the ear end face perforate (18) that each blade of just separating propeller runner (10) and the first bead filler that untwists are bored (19) along working to revolve chamber center tube (25); The freezing mixture that enters blade sprays from the anterior numerous micropores of blade blade is formed the film cooling, and the freezing mixture that flows out from bead filler awl (10) rear end of just untwisting is then to formation film coolings such as turbine hubs (17).
In addition, present embodiment also has power circulating device, mentions above, and the air-flow after the burning drives power turbine (11) earlier after just separating cyclone, and its mechanical output offers petrolift and generator etc. by output shaft output.
We have got O as shown in Figure 1, A, B, C, D, E, F1, F2 point in embodiment 1, and the calculation of parameter of these points is come out to be summarized as follows table.Be that the vortex supercharging analytic solutions set of equation of according to the form below back provides wherein to the calculating of vortex supercharging.
Symbol definition in the table is:
H---altitude
V
∞---the far-end airspeed
M---Mach number
S
01---01 section area
S
02---02 section area
S
A *---rise and revolve the effective flow area area of latter end
ρ
∞---the far-end current density
P---pressure
ρ---density
T---thermodynamic temperature
V---flow velocity
A---velocity of sound
F---thrust
I
*---equivalent specific impulse
Embodiment 2
Embodiment 2 is with embodiment 1 difference: it is provided with the auxilliary eddy combustion chamber (7 ') in independently anterior main eddy combustion chamber (1 ') and rear portion, as shown in Figure 3.Combuster separation core awl (5 ') is separated by between main eddy combustion chamber and auxilliary eddy combustion chamber, forms the big slightly high pressure transition chamber (2 ') of caliber around firing chamber separation core awl (5 ').The inwall of the auxilliary eddy combustion chamber (7 ') at main eddy combustion chamber, high pressure transition chamber (2 ') and rear portion all has fuel jet orifice.The fuel that pumps into sprays into from above-mentioned fuel jet orifice with the vortex air and mixes, reacts, discharges heat energy in the high-pressure area.The existence that core awl (5 ') is separated in the firing chamber is to make eddy airstream only enter auxilliary eddy combustion chamber from the high-pressure area, makes reaction than the more slap-up purpose of embodiment 1 to reach.
Embodiment 3
As Fig. 6, shown in Figure 7, high velocity air (generally its M number is more than or equal to 2) flows into from variable geometry inlet (1 ") front-end face; the import that intake duct controller (2 ") is regulated variable geometry inlet (1 ") has it and requires corresponding to intake area; air stream is after the end of variable geometry inlet (1 ") is tentatively compressed, the section of revolving of having flowed through (4 ") is done further compression; tangentially enter lower scroll chamber (21 ") again, and form vortex flow therein.The caliber of lower scroll chamber (21 ") is less, and the vortex air that it will play supination becomes diameter short tube (20 ") by the vortex supercharging and sends into the bigger high pressure swirl chamber of caliber (22 ").Gas has maximum pressure near the inwall of high pressure swirl chamber (22 "), pass on bend pipe (5 ") from the high pressure swirl chamber (22 ") draw the transmission of high pressure swirl air-flow and enter the first eddy combustion chamber (17 "), and return to the vortex flow state once more.
The most of structure of present embodiment also has inside and outside wall, is mezzanine space between the inside and outside wall, and the mezzanine space two ends have forward and backward fuel collection and send endless tube.In the past the fuel collection send the fuel that endless tube (3 ") is sent into; the inside and outside wall mezzanine space of the section of revolving of having flowed through (4 "), lower scroll chamber (21 "), high pressure swirl chamber (22 "), the inside and outside wall mezzanine space of bend pipe (5 ") is passed in arrival; bend pipe (the 5 ") inwall that passes on has a lot of fuel jet orifices, fuel is sprayed into by this spray orifice and passes in the bend pipe (5 "), mixes with high pressure air flow; The fuel that send endless tube (10 ") to send into from back fuel collection; the inside and outside wall mezzanine space of (19 "); arrive the inside and outside wall mezzanine space of the first eddy combustion chamber (17 ") through expansion jet pipe (9 "), converging portion (8 "), the section of untwisting (7 "), the second eddy combustion chamber, the first eddy combustion chamber (17 ") inwall has many fuel jet orifices, and fuel is sprayed into to mix with the high pressure swirl air-flow by this spray orifice and is incorporated in fully burning under the vorticity.Clean-burning high pressure swirl air-flow flows into the second eddy combustion chamber (19 "), after tangentially enter the section of untwisting (7 "), the air-flow (non-vortex flow) of separating supination enters converging portion (8 "), is not less than 1 in the air-flow velocity M of the smallest cross-sectional place of converging portion value.At last, gas flow expands along expansion jet pipe (9 ") and accelerates to the motor ear end face and spray at a high speed.
In the second eddy combustion chamber (19 "), be provided with power turbine (15 ") in addition along the axis outside, the turbine shaft of power turbine (15 ") (16 ") be hollow, the inside and outside wall of (12 ") of the dome plate of power turbine (15 ") has mezzanine space, and each turbine blade (15 ") inside has vestibule, front portion that numerous micropores is arranged.Freezing mixture pumps into turbine shaft (16 ") endoporus from the outside, be conveyed in the mesopore of each turbine blade through the mezzanine space of the inside and outside wall of turbine dome plate (12 "), from the anterior numerous micropores ejection of blade, blade is carried out the film cooling at last.
The mechanical output that turbine (15 ") produces can be driven pump that will use required for the present invention or generator, thereby be formed the circulatory system of a relative closure by hollow vortex wheel shaft (16 ") output.
The useless combustion gas of flowing out from turbine is discharged through turbine exhaust discharge pipe (11 ").
Claims (5)
1, a kind of supersonic swirl boosted propulsion engine is characterized in that: it comprises that the variable geometry inlet, a cyclone, the vortex supercharging that connect in turn become diameter short tube, eddy combustion chamber, separate cyclone, converging portion and expansion jet pipe; Be provided with fuel jet orifice and igniter in the eddy combustion chamber interior walls.
2, supersonic swirl boosted propulsion engine according to claim 1, it is characterized in that: the outlet end that becomes diameter short tube (6) in described vortex supercharging is provided with separation core awl (8), described spinning has been changed to propeller runner (26), separates cyclone and comprises and just separate propeller runner (10) and propeller runner (12) is separated at the end; Just separate propeller runner (10) and end and separate dynamic turbine (11) between the propeller runner (12).
3, supersonic swirl boosted propulsion engine according to claim 2, it is characterized in that: described eddy combustion chamber comprises the auxilliary eddy combustion chamber (7 ') that is positioned at anterior main eddy combustion chamber (1 ') and is positioned at the rear portion, combuster separation core awl (5 ') is separated by between the auxilliary eddy combustion chamber at main eddy combustion chamber and rear portion, forms the big slightly high pressure transition chamber (2 ') of caliber around firing chamber separation core awl (5 ');
The inwall of high pressure transition chamber (2 ') has fuel jet orifice (3 ').
4, supersonic swirl boosted propulsion engine according to claim 1, it is characterized in that: play the lower scroll chamber that spinning has been changed to the section of revolving (4 ") and has been attached thereto (21 "), the lower scroll chamber becomes diameter short tube (20) and high pressure swirl chamber (22 ") by the vortex supercharging and links to each other, and high pressure swirl chamber (22 ") are by passing on bend pipe (5 ") access eddy combustion chamber; The eddy combustion chamber comprises that the vortex supercharging of the first eddy combustion chamber that is linked in sequence (17 "), contrary usefulness becomes diameter short tube (18 ") and the second eddy combustion chamber (19 "), and the caliber of the second eddy combustion chamber (19 ") is less than the caliber of high pressure swirl firing chamber (17 "); Separate cyclone for separating coil (7 "), separate that coil is terminal to link to each other with converging portion (8 "); The inwall of bend pipe (5 ") of passing on has fuel jet orifice (6 "); Outer end, the second eddy combustion chamber (19 ") is provided with power turbine (15 ").
5, supersonic swirl boosted propulsion engine according to claim 1 is characterized in that: described vortex supercharging becomes the inwall aperture of an end inwall aperture of diameter short tube less than the other end.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 02116220 CN1382903A (en) | 2002-03-21 | 2002-03-21 | Supersonic swirl boosted propulsion engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN 02116220 CN1382903A (en) | 2002-03-21 | 2002-03-21 | Supersonic swirl boosted propulsion engine |
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| Publication Number | Publication Date |
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| CN1382903A true CN1382903A (en) | 2002-12-04 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN 02116220 Pending CN1382903A (en) | 2002-03-21 | 2002-03-21 | Supersonic swirl boosted propulsion engine |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102817715A (en) * | 2011-06-06 | 2012-12-12 | 王长存 | Third-generation heavy fighter novel gas inlet channel lip |
| CN105221295A (en) * | 2015-11-06 | 2016-01-06 | 西南科技大学 | A kind of punching press-turbojet compound aeroengine |
| CN114486273A (en) * | 2021-12-27 | 2022-05-13 | 国网浙江省电力有限公司电力科学研究院 | Park flexibility reforms transform unit hydrogen and burns test device thoughtlessly |
-
2002
- 2002-03-21 CN CN 02116220 patent/CN1382903A/en active Pending
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102817715A (en) * | 2011-06-06 | 2012-12-12 | 王长存 | Third-generation heavy fighter novel gas inlet channel lip |
| CN105221295A (en) * | 2015-11-06 | 2016-01-06 | 西南科技大学 | A kind of punching press-turbojet compound aeroengine |
| CN114486273A (en) * | 2021-12-27 | 2022-05-13 | 国网浙江省电力有限公司电力科学研究院 | Park flexibility reforms transform unit hydrogen and burns test device thoughtlessly |
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