CN101718226A - Non-intermittent detonation rotor of engine - Google Patents
Non-intermittent detonation rotor of engine Download PDFInfo
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- CN101718226A CN101718226A CN200910198225A CN200910198225A CN101718226A CN 101718226 A CN101718226 A CN 101718226A CN 200910198225 A CN200910198225 A CN 200910198225A CN 200910198225 A CN200910198225 A CN 200910198225A CN 101718226 A CN101718226 A CN 101718226A
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Abstract
The invention relates to a non-intermittent detonation rotor of an engine, in particular to a turntable rotating around an axis, comprising a turntable body, a front soleplate and a rear soleplate. The turntable body is provided with a pre-mixing fuel inlet in the center and a combustion ring tube in the middle; the pre-mixing fuel inlet and the combustion ring tube are communicated by a gas inlet branch pipeline; a one-way valve is arranged at the joint; the combustion ring tube is internally provided with diffraction barriers, divided by the diffraction barriers into a plurality of division areas and provided with an igniter; a gas outlet combustion pipeline is arranged between the combustion ring tube and the outer margin of the turntable body. The invention greatly simplifies the structure of the engine, overcomes the difficulty of continuous ignition, greatly enhances the frequency of power provided by combustion, improves the smoothness of output torque, decreases the cost, improves the efficiency and can maximize the combustion efficiency under a detonation combustion state, thereby being applied to the fields of electricity, power or aerospace, and the like.
Description
Technical field:
The present invention relates to a kind of heat engine rotor, the especially a kind of detonation of premixed fuel or non-intermittent detonation rotor of engine that the detonation combustion process is carried out continuous doing work of utilizing.It can be applied in electric power, power or aerospace field.
Background technique:
The present invention comes from the thinking again of conventional engines technology and the investigation of modern engine technology principle.
It is generally acknowledged that motor development has roughly experienced two big historical stages, the phase I is exactly before nineteen fifty, mainly is piston-engined use.Second stage is after World War II, and the turbogenerator fast development is always in occupation of the dominance, it has a lot of mutation, as turbofan engine, turbo oar engine, turboshaft engine etc., but its core technology all is gas compressor-turbine combination, i.e. gas turbine.
The someone proposes very early, and turbogenerator has been crossed summit to be had after the phase and do not have follow-up machine.Why this problem can be proposed? because the human hot machine of being invented up to the present, the overwhelming majority relies on the pressure expansion process to realize the hot merit conversion, and piston engine, turbogenerator are not always the case.And the performance that will improve turbogenerator mainly contains two approach, and one is to improve pressure ratio, and another is to improve turbine inlet temperature, and this is its working principle decision.But raising pressure ratio, raising turbine inlet temperature have certain limitation, and the imagination pressure ratio reaches about 40, and the rotating speed of gas compressor can be very big; Pressure ratio improves simultaneously, and the intensity of blade also is a problem.So no matter from pressure ratio still from temperature, turbogenerator is basically soon near its performance boundary.
To this, at present a lot of new machines have also appearred, and as pulse-knocking engine, pressed engine etc., this is main several research directions, also is to attempt to find the technology that significantly improves aero-engine performance to attempt.But these motors also are in the stage of fumbling.The pulse-knocking engine noise is huge, and frequency of okperation does not just obviously catch up with.Frequency of okperation just is meant the knocking combustion frequency, can produce enough specific impulses about 100 hertz, if do not arrive this frequency, specific impulse is not enough, and comparing with turbo machine does not just have competitive ability.Imagination is in cavity the inside, one second of exhaust, air inlet more than 100 time back and forth, but also the neither one piston pushs out gas, only fills, explodes by inflation process, recharges, blast again, this itself is very difficult.
Many researchers have made effort for improving these situations, specifically can be embodied in the patent that they deliver, as US 4741154 (1988), they propose to rotate the notion of detonation engine, but to how solving knocking combustion frequency and igniting and DDT process (detonation is to detonation conversion (Deflagration to Detonation Transition)) all avoid; CN 100507253C (2007) is the work of Northwestern Polytechnical University, the edge that is connected the wheel wheel that they are adjacent with a plurality of detonation pipes, exist vertical unicom pipeline in order to transmit burning between the detonation pipe, their thought is very good, it is complex structure, and this design avoided problems such as air inlet, and concrete enforcement may have difficulties; That research is more at present is the US7228683B2 (2007) of changeover valve multi-tube design as GE, US 6983586B2 (2006) or the like, but there is its tangible shortcoming in this design, can cause noise and instability by the low deflection vibration that causes of its frequency of okperation.
Summary of the invention:
The objective of the invention is to deficiency, a kind of non-intermittent detonation rotor of engine is provided at the prior art existence.The present invention has developed new engine rotor structure, solved the problem of continuous igniting, improved the continual and steady and flatness of the burning power of putting forward, when saving cost, improved usefulness, can be under the detonation combustion state, obtain the maximization of combustion efficiency, also changed the long-term puzzlement situation of detonation engine DDT process difficulty.
For achieving the above object, design of the present invention is:
Non-intermittent detonation rotor of engine of the present invention has the wheel disk body.
The wheel disk body is the carrier of each pipeline as the core component of rotor, and it can be integrated manufacturing, also can splice or sheet structure is formed by stacking.
Non-intermittent detonation rotor of engine of the present invention, base plate before and after having.
The front and back base plate is the closure of each pipeline, simultaneously the wheel disc body is formed the support effect.The shape of front and back base plate can be varied, also can be some building blocks of functions, as axle, turbine, turbofan etc.
Non-intermittent detonation rotor of engine of the present invention has the premixed fuel inlet.
The premixed fuel inlet provides stable premixed fuel source, the existence of safeguard work medium, premixed fuel is precharge simultaneously, and premixed fuel can be gas or aerosol or gas powder form, and its chemical composition proportioning can satisfy generation detonation or detonation burning.
Non-intermittent detonation rotor of engine of the present invention has the air inlet bypass line.
The air inlet bypass line provides and will have been shunted by the premixed fuel that the premixed fuel inlet enters, and the downstream of air inlet bypass line is provided with one-way cock, and premixed fuel is directed to different burning endless tube pipeline sections by one-way cock.
Non-intermittent detonation rotor of engine of the present invention has the burning endless tube.
The burning endless tube is circular ring pipe or regular polygon shape pipeline, in establish the diffracting obstacles body endless tube that will burn and not exclusively evenly cut apart, outwards connect the combustion pipe of giving vent to anger, ignition device or firing mode that at least one is set simultaneously start the interior premixed fuel burning of burning endless tube.
Non-intermittent detonation rotor of engine of the present invention has one-way cock.
One-way cock control premixed fuel flows to the burning endless tube, and its unlatching can be by initiatively controlling or passive by air inlet bypass line and the control of burning endless tube pressure reduction.The pressure p of air inlet bypass line generally,
Greater than the pressure p in the endless tube pipeline section that do not burn
Combustion pipe-not combustionPressure loss p with one-way cock
Valve-lossSum also will satisfy the requirement of postcombustion simultaneously, therefore should satisfy following relation:
p
＞p
Combustion pipe-not combustion+ p
Valve-loss+ mv
2/ 2,
Wherein m is for filling the burning endless tube and the premixed fuel quality of the combustion pipe of partly giving vent to anger, and v is the mean velocity that fuel is filled.Certainly, p
Also can not ether big, when the burning endless tube burning takes place the time, the pressure in the endless tube that necessarily requires to burn can be closed one-way cock.In addition, v is an amount that pays particular attention to, and fuel is filled and the problem of the time contest between the relay of burning because involve here.Here arranged, fire ring combustion inner pipe t cycle time several times
The combustion pipe, products of combustion is discharged and is checked the time chien shih time t that needs to the one-way cock unlatching
Exhaust decompression, inflationtime t
Inflation, therefore must have
t
Inflation＜t
The combustion pipe/ n-t
Exhaust decompression,
Wherein n is separated interval number for the burning endless tube, so t
InflationThis time may be very weak point, especially work as deflagration wave when in the burning endless tube, propagating with the high speed of about 2000m/s, the motor little to diameter, very fast of the aeration speed v that requires, be certain to bring technical difficulty, but this also is one of significant advantage of the present invention place, compares with general detonation engine, there is the restriction of frequency hardly in our rotor, and this is the reason why the present invention is called non-intermittent detonation rotor.
Non-intermittent detonation rotor of engine of the present invention has ignition device or firing mode.
Ignition device or firing mode are to comprise that laser ignition, spark ignition, sound wave igniting, ignition by shock wave, spark ignition etc. can produce the setting of burning at the burning endless tube.Ignition device main effect in the present invention is to start burning, does not need frequent igniting, at normal running once, only needs once igniting usually.An ignition device generally also only is set.
Non-intermittent detonation rotor of engine of the present invention has the diffracting obstacles body.
The diffracting obstacles body is fixed on the wall of burning endless tube, and its size is not enough to complete closed burning endless tube, ensures that burning is not guaranteed the endless relay between the different cut sections of burning endless tube of detonation wave or deflagration wave in the intensity of cut section when too much weakening.The design of diffractor can design smootherly with meeting the corrugated because of reduce the loss of power as far as possible, the diffraction face design steeper, as the poly-wave structure of oval indent.
Non-intermittent detonation rotor of engine of the present invention has the combustion pipe of giving vent to anger.
The combustion pipe of giving vent to anger forms the arc pipe of outside back-out with the burning endless tube, and the pipeline tail end is opened on the edge or the outside of wheel disk body, and its shape can have special design, as shrinking or expansion or shrink is earlier afterwards expanded etc.
Non-intermittent detonation rotor of engine of the present invention, all around the evenly corresponding distribution of spin axis, quantity is more than two groups for each pipeline (not comprising the burning endless tube), valve, obstacle body.
According to the foregoing invention design, the present invention adopts following technical proposals:
A kind of non-intermittent detonation rotor of engine is a wheel disc around rotational, comprises wheel disk body and the front and back base plate of fitting with wheel disk body front and back sides; Wheel disk body and front and back base plate have center hole to constitute the premixed fuel inlet, in the middle of the wheel disk body burning endless tube are arranged, and have the air inlet bypass line to link up between the premixed fuel inlet, and both jointings are equipped with one-way cock; Be provided with some diffracting obstacles bodies in the burning endless tube, the endless tube that will burn is divided into some districts of cutting; In the burning endless tube ignition device is housed; The burning endless tube is to the combustion pipe of giving vent to anger between the external edge of wheel disc.
Above-mentioned air inlet bypass line, diffracting obstacles body, one-way cock quantity are identical, and along circumferentially uniform, quantity is no less than 2 groups.
Above-mentioned burning endless tube is circular ring pipe or regular polygon pipeline.
Above-mentioned diffracting obstacles body is fixed on the wall of described burning endless tube, and its size is not enough to complete closed burning endless tube, leaves the effective clearance between the adjacent cut section, and guarantees that the cavity of cut section is not too much dwindled.
The above-mentioned combustion pipe of giving vent to anger forms the arc pipe of outside back-out with the burning endless tube, and this pipeline tail end is opened on the edge of wheel disk body or base plate backward laterally.
Above-mentioned ignition device is Laser Igniter or spark lighter or sonic point firearm or shock point firearm or electric spark igniter or jet igniter, is arranged on to produce the burning part at the burning endless tube.
Above-mentioned premixed fuel, its chemical composition proportioning is for satisfying gas or aerosol or the gas powder form fuel that produces detonation or detonation burning.
Above-mentioned premixed fuel should have precharge pressure to guarantee the supply of fuel in the premixed fuel ingress.
The present invention has following conspicuous outstanding substantive distinguishing features and remarkable advantage compared with prior art:
Non-intermittent detonation rotor of engine of the present invention, be a kind of detonation of premixed fuel or motor important component that the detonation combustion process is carried out continuous doing work of utilizing, the endless relay of premixed fuel burning is that detonation wave or deflagration wave realize that by diffracting obstacles body edge diffraction is achieved in the burning endless tube.When premixed fuel is under the detonation combustion working state, can obtain the maximization of combustion efficiency.
The present invention has effectively reduced period of exhaust, and promptly big of exhaust process and gas replenishment process are overlapping, and the frequency of having improved burning is to the situation of simple dependence by the inflation process exhaust.
The present invention has been merged the criticism of traditional two-stroke engine structure and combustion process and the modern science achievement in research to detonation engine, simplified engine structure greatly, the difficulty of continuous igniting has weakened, the frequency of the burning power that provides has been provided greatly, improved the flatness of output torque, reduce cost and raise the efficiency, under the detonation combustion state, can obtain the maximization of combustion efficiency simultaneously.
The present invention has also improved the detonation engine internal combustion and changed (Deflagration to Detonation Transition (DDT process)) requirement to flame tube length dimension and frequent igniting from the detonation to detonation, for the miniaturization of detonation combustion power provides feasible method.
The present invention can be applied in fields such as electric power, power or Aero-Space.
Description of drawings:
Fig. 1 non-intermittent detonation rotor of engine structural representation.
Fig. 2 is an o-A-B place sectional drawing among Fig. 1.
Fig. 3 non-intermittent detonation rotor structural representation.
Fig. 4 non-intermittent detonation rotor and turbine combined engine rotor structure schematic representation.
Fig. 5 N group non-intermittent detonation rotor in parallel or non-intermittent detonation rotor in parallel and turbine combination collaborative work schematic representation.
Embodiment:
Embodiment one: details are as follows in conjunction with the accompanying drawings for the preferred embodiments of the present invention: referring to Fig. 1 and Fig. 2, this non-intermittent detonation rotor of engine is a wheel disc around rotational, comprises wheel disk body 1 and the front and back base plate 9,10 of fitting with wheel disk body front and back sides.Described disk body 1 and the front and back base plate 9,10 of taking turns has center hole to constitute premixed fuel inlet 8; There is a burning endless tube 5 described disk body 1 centre of taking turns, and has air inlet bypass line 2 to link up between the described premixed fuel inlet 8, and both jointings are equipped with one-way cock 6; Be provided with some diffracting obstacles bodies 3 in the described burning endless tube 5, the endless tube 5 that will burn is divided into some districts of cutting; In the burning endless tube 5 ignition device 4 is housed; Described burning endless tube 5 is to the combustion pipe 7 of giving vent to anger between wheel disk body 1 outer rim.Premixed fuel in ignition device or the firing mode 4 ignition combustion endless tubes 5, combustion flame and combustion wave are propagated by two kinds of approach, and a kind of is to combustion pipe 7 motions of giving vent to anger; Another kind is to guide combustion flame and combustion wave into cut apart by diffracting obstacles body 3 in the next burning endless tube 5 not combustion zone at diffracting obstacles body 3 edge generation diffraction and near the transmission of burning endless tube 5 walls diffracting obstacles body 3 edges reflection.Combustion flame and combustion wave move in the combustion pipe 7 of giving vent to anger and finally spray at a high speed for non-intermittent detonation rotor of engine rotates at wheel disk body 1 edge provides torque and power; Combustion flame and combustion wave make burning be maintained in the diffraction and the reflection at diffracting obstacles body 3 edges, and the difficulty of frequent igniting and DDT process is dissolved, and also make rotor not have acting at intermittence process stably continuously and are achieved.
Embodiment two: referring to Fig. 1, Fig. 2 and Fig. 3, present embodiment is identical with embodiment one, and specialization is: front and back base plate 9 and 10 shape change, and the shoulder of base plate 9 and base plate 10 is used as rotatingshaft and is installed on the pedestal 11 by bearing or bearing shell.This structure can be directly as a kind of way of realization of motor.
Embodiment three: referring to Fig. 1, Fig. 2 and Fig. 4, present embodiment is identical with embodiment one, and specialization is: the shape of the combustion pipe 7 of giving vent to anger becomes the slightly sweptback design of combustion-gas flow, and base plate 10 is substituted by turbine structure 12.The high velocity air that the combustion pipe 7 of giving vent to anger sprays also can produce power via turbine structure 12, thereby strengthens the motion of rotor.So this structure can be used as a kind of way of realization of engine rotor.
Embodiment four: referring to Fig. 4, Fig. 1, Fig. 2 and Fig. 5, can be with the structure parallel connection shown in case one or the case three, and perhaps with the structure parallel connection shown in case one and the case three, to realize the multiplication of power, the size of module and combination can be compared flexibly.This structure is a kind of effective way of realization of engine rotor.
Claims (8)
1. a non-intermittent detonation rotor of engine is a wheel disc around rotational, comprises wheel disk body (1) and the front and back base plate (9,10) of fitting with wheel disk body front and back sides, it is characterized in that:
1) described disk body (1) and the front and back base plate (9,10) of taking turns has center hole to constitute premixed fuel inlet (8);
2) there is a burning endless tube (5) described disk body (1) centre of taking turns, and has air inlet bypass line (2) to link up between the described premixed fuel inlet (8), and both jointings are equipped with one-way cock (6);
3) be provided with some diffracting obstacles bodies (3) in the described burning endless tube (5), the endless tube (5) that will burn is divided into some districts of cutting; In the burning endless tube (5) ignition device (4) is housed;
4) described burning endless tube (5) is to the combustion pipe (7) of giving vent to anger between wheel disk body (1) outer rim.
2. non-intermittent detonation rotor of engine according to claim 1 is characterized in that described air inlet bypass line (2), diffracting obstacles body (3), one-way cock (6) quantity are identical, and along circumferentially uniform, quantity is no less than 2 groups.
3. non-intermittent detonation rotor of engine according to claim 1 is characterized in that described burning endless tube (5) is circular ring pipe or regular polygon pipeline.
4. non-intermittent detonation rotor of engine according to claim 1, it is characterized in that described diffracting obstacles body (3) is fixed on the wall of described burning endless tube (5), its size is not enough to complete closed burning endless tube (5), leave the effective clearance between the adjacent cut section, and guarantee that the cavity of cut section is not too much dwindled.
5. non-intermittent detonation rotor of engine according to claim 1, it is characterized in that the described combustion pipe of giving vent to anger (7) forms the arc pipe that outwards screws out with burning endless tube (5), this pipeline tail end is opened on the edge of wheel disk body (1) or base plate (10) backward laterally.
6. non-intermittent detonation rotor of engine according to claim 1, it is characterized in that described ignition device (4) is Laser Igniter or spark lighter or sonic point firearm or shock point firearm or electric spark igniter or jet igniter, be arranged on and produce the burning part at burning endless tube (5).
7. non-intermittent detonation rotor of engine according to claim 1 is characterized in that described premixed fuel, and its chemical composition proportioning is for satisfying gas or aerosol or the gas powder form fuel that produces detonation or detonation burning.
8. non-intermittent detonation rotor of engine according to claim 7 is characterized in that described premixed fuel locates to have precharge pressure to guarantee the supply of fuel at premixed fuel inlet (8).
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| CN2009101982251A CN101718226B (en) | 2009-11-03 | 2009-11-03 | Non-intermittent detonation rotor of engine |
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| CN2009101982251A CN101718226B (en) | 2009-11-03 | 2009-11-03 | Non-intermittent detonation rotor of engine |
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| CN101718226B CN101718226B (en) | 2012-07-04 |
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Cited By (8)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102052153A (en) * | 2010-11-19 | 2011-05-11 | 北京工业大学 | Shock power machine adopting knocking combustion mode |
| CN103306855A (en) * | 2013-06-24 | 2013-09-18 | 谷利伟 | Detonation engine |
| US20140007837A1 (en) * | 2012-07-09 | 2014-01-09 | Isaac Erik Anderson | Shockwave Rotor Detonation (Omni-Engine, Ubiquitous X engine) Multipurpose Engine |
| CN110145409A (en) * | 2019-05-23 | 2019-08-20 | 江苏大学 | A kind of multi-pipe impulse detonation engine high-frequency igniter systems |
| CN111677616A (en) * | 2020-05-07 | 2020-09-18 | 江苏大学 | Laser multipoint ignition system in rotor engine |
| CN112066417A (en) * | 2020-08-20 | 2020-12-11 | 西北工业大学 | Rotary detonation combustion scheme for eliminating gyro moment in flight process |
| CN112483277A (en) * | 2020-01-07 | 2021-03-12 | 姚长水 | Self-adaptive variable-frequency mutual control type pulse detonation aircraft engine |
| CN114320659A (en) * | 2022-01-10 | 2022-04-12 | 江苏海能动力科技有限公司 | Low-cost closed pulse detonation wind source engine |
Family Cites Families (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2890570A (en) * | 1952-10-14 | 1959-06-16 | Georgia Tech Res Inst | Power unit for the conversion of heat energy of fluids into mechanical energy |
| US6983586B2 (en) * | 2003-12-08 | 2006-01-10 | General Electric Company | Two-stage pulse detonation system |
| CN101113688B (en) * | 2007-08-17 | 2011-05-04 | 梁振春 | Whirlwind dual rotors coupling air compressing injector |
| CN201277093Y (en) * | 2008-07-15 | 2009-07-22 | 张启龙 | Isochoric kinetic energy engine |
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Cited By (13)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102052153A (en) * | 2010-11-19 | 2011-05-11 | 北京工业大学 | Shock power machine adopting knocking combustion mode |
| US20140007837A1 (en) * | 2012-07-09 | 2014-01-09 | Isaac Erik Anderson | Shockwave Rotor Detonation (Omni-Engine, Ubiquitous X engine) Multipurpose Engine |
| US9970294B2 (en) * | 2012-07-09 | 2018-05-15 | Isaac Erik Anderson | Shockwave rotor detonation (omni-engine, ubiquitous X engine) multipurpose engine |
| CN103306855A (en) * | 2013-06-24 | 2013-09-18 | 谷利伟 | Detonation engine |
| CN103306855B (en) * | 2013-06-24 | 2015-07-22 | 谷利伟 | Detonation engine |
| CN110145409B (en) * | 2019-05-23 | 2021-11-23 | 江苏大学 | High-frequency igniter system of multi-tube pulse detonation engine |
| CN110145409A (en) * | 2019-05-23 | 2019-08-20 | 江苏大学 | A kind of multi-pipe impulse detonation engine high-frequency igniter systems |
| CN112483277A (en) * | 2020-01-07 | 2021-03-12 | 姚长水 | Self-adaptive variable-frequency mutual control type pulse detonation aircraft engine |
| CN112483277B (en) * | 2020-01-07 | 2023-05-23 | 姚长水 | Self-adaptive variable-frequency inter-control pulse detonation aeroengine |
| CN111677616A (en) * | 2020-05-07 | 2020-09-18 | 江苏大学 | Laser multipoint ignition system in rotor engine |
| CN112066417A (en) * | 2020-08-20 | 2020-12-11 | 西北工业大学 | Rotary detonation combustion scheme for eliminating gyro moment in flight process |
| CN114320659A (en) * | 2022-01-10 | 2022-04-12 | 江苏海能动力科技有限公司 | Low-cost closed pulse detonation wind source engine |
| CN114320659B (en) * | 2022-01-10 | 2023-12-26 | 江苏海能动力科技有限公司 | Low-cost closed pulse detonation wind source engine |
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