CN104033286B - A kind of high-frequency pulse pinking combustion-powered apparatus - Google Patents
A kind of high-frequency pulse pinking combustion-powered apparatus Download PDFInfo
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- CN104033286B CN104033286B CN201410245244.6A CN201410245244A CN104033286B CN 104033286 B CN104033286 B CN 104033286B CN 201410245244 A CN201410245244 A CN 201410245244A CN 104033286 B CN104033286 B CN 104033286B
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Abstract
A kind of high-frequency pulse pinking combustion-powered apparatus of the present invention, comprises the pulse detonation combustor, jet pipe and the plural serial stage pushing structure that are connected successively from left to right; Wherein, pulse detonation combustor comprises the head of combustion chamber end cap, combustion chamber ignition section, the firing chamber section of detonating and the firing chamber pinking section that are connected successively from left to right, and the right-hand member of firing chamber pinking section is connected with jet pipe; Head of combustion chamber end cap is provided with main nozzle, and main nozzle is provided with main nozzle air pipe line and main nozzle fuel conduit; The circumference of combustion chamber ignition section is provided with spark plug; The circumference of the firing chamber section of detonating and firing chamber pinking section in axial direction goes up and is equidistantly provided with some pilot jets, and pilot jet is provided with pilot jet air pipe line and pilot jet fuel conduit.The present invention can reduce the filling time of firing chamber, improves the frequency of okperation of motor, the thrust that the increase motor unit time produces; In addition, devise plural serial stage pushing structure at jet pipe, improve the thrust of motor further.
Description
[technical field]
The present invention relates to technical field of engines, particularly relate to a kind of high-frequency pulse pinking combustion-powered apparatus.
[background technique]
Knocking combustion is the another kind of mode of burning, and they are different from deflagration combustion process, and knocking combustion process is very fast, can produce supersonic combustion ripple, i.e. detonation wave.Pinking wave propagation by shock wave to can pinking mixture successively intense impact compression make its occur high-speed chemical reaction realize, therefore can think that detonation wave is the strong shock of Coupled with Chemical Reaction.The velocity of propagation of knocking combustion is far longer than the velocity of propagation of deflagration burning, generally 10
3m/s magnitude.Compared with burning with deflagration, knocking combustion has from supercharging, flame propagation speed, the advantage such as combustion efficiency is high, pollutant emission is low, knocking combustion is substituted the isobaric combustion in conventional power plants, develop the utilization ratio that the novel power device circulated based on pinking can improve the existing energy.
Pulse-knocking engine is that a kind of intermittent knocking combustion generation high temperature, high-pressure gas of utilizing is to produce the new concept propulsion device of thrust.According to whether carrying oxygenant, pulse-knocking engine is divided into air-breathing pulse detonation engine and rocket type pulse-knocking engine.The detonation mode of knocking combustion is divided into direct initiation and indirectly detonates two kinds, the former needs huge ignition energy, latter forms detonation wave by detonation gradually to pinking transformation, namely less ignition energy is first adopted to form deflagration wave, then by flame and compressional wave, the interaction in detonation chamber finally forms detonation wave, the distance that this section changes from detonation to pinking is called DDT, and the length of DDT determines primarily of parameters such as firing chamber size and fuel characteristics.Consider practicability, pulse-knocking engine generally adopts the mode of indirectly detonating to obtain detonation wave, this makes the length of firing chamber be greater than DDT, and in order to ensure that chamber fuel major part is with knocking combustion heat release, general designed combustion room length is 4 to 5 times of DDT distance.And the intake method of traditional air-inlet type and rocket type pulse-knocking engine all adopts the mode from the air inlet of pulse detonation combustor head, this have impact on the filling time of firing chamber to a certain extent, causes engine operating frequencies to reduce with the increase of chamber length.Simultaneously because work frequency of pulse knocking engine is not high, be in tradition always and fill, compared with the constant-pressure combustion chamber of combustion regime, the fuel that traditional pulse detonation engine firing chamber is filled within the unit time is less, cause the thrust produced in the pulse-knocking engine unit time lower, which prevent the application paces of pulse-knocking engine.
Summary analysis can be found out, although knocking combustion has advantage compared with traditional isobaric combustion, pulse-knocking engine still exists following subject matter: 1) work frequency of pulse knocking engine is low, is subject to chamber length restriction; 2) thrust of pulse-knocking engine unit time generation is less.
[summary of the invention]
The object of the invention is to solve the problems such as low, that frequency limits by chamber length, the motor unit time the produces thrust of traditional pulse detonation engine frequency of okperation is little, provide a kind of high-frequency pulse pinking combustion-powered apparatus, the filling time of its energy chopped pulse detonation combustor, increase the thrust produced in the motor unit time, the problem that engine operating frequencies is limited to chamber length can be solved simultaneously.
For achieving the above object, the technical solution used in the present invention is:
A kind of high-frequency pulse pinking combustion-powered apparatus, comprises the pulse detonation combustor, jet pipe and the plural serial stage pushing structure that are connected successively from left to right; Wherein,
Pulse detonation combustor comprises the head of combustion chamber end cap, combustion chamber ignition section, the firing chamber section of detonating and the firing chamber pinking section that are connected successively from left to right, and the right-hand member of firing chamber pinking section is connected with jet pipe; Head of combustion chamber end cap is provided with main nozzle, and main nozzle is provided with main nozzle air pipe line and main nozzle fuel conduit; The circumference of combustion chamber ignition section is provided with spark plug; The circumference of the firing chamber section of detonating and firing chamber pinking section in axial direction goes up and is equidistantly provided with some pilot jets, and pilot jet is provided with pilot jet air pipe line and pilot jet fuel conduit.
The present invention improves further and is: jet pipe is constrictor nozzle, and contraction ratio is 1.2 to 1.5, and convergence angle is 6 to 10 degree.
The present invention improves further and is: plural serial stage pushing structure comprises the one-level pushing device, secondary pushing device and the three grades of pushing devices that are connected successively from left to right.
The present invention improves further and is: one-level pushing device comprises the first arc air inlet end face and the first axisymmetric straight tube, secondary pushing device comprises the second arc air inlet end face and the second axisymmetric straight tube, and three grades of pushing devices comprise the 3rd arc air inlet end face and the 3rd axisymmetric straight tube; Some plural serial stage pushing structural linkages are evenly arranged on the circumference of the first arc air inlet end face, and one end of some plural serial stage pushing structure support plates is connected with corresponding plural serial stage pushing structural linkages, and its other end is connected with pulse detonation combustor afterbody; Between some first order, pushing device connecting rod is evenly arranged on the circumference of the second arc air inlet end face, and between some first order, one end of pushing device support plate is connected with pushing device connecting rod between the corresponding first order, and its other end is connected with the first axisymmetric straight tube; Between some second level, pushing device connecting rod is evenly arranged on the circumference of the 3rd arc air inlet end face, and between some second level, one end of pushing device support plate is connected with pushing device connecting rod between the corresponding second level, and its other end is connected with the second axisymmetric straight tube.
The present invention improves further and is: the quantity of plural serial stage pushing structure support plate and plural serial stage pushing structural linkages is 4, between the first order, between pushing device support plate and the first order, the quantity of pushing device connecting rod is 4, and between the second level, between pushing device support plate and the second level, the quantity of pushing device connecting rod is 4.
The present invention improves further and is: the inwall of the firing chamber section of detonating is provided with the first spirality obstacle, and the inwall of firing chamber pinking section is provided with the second spirality obstacle, and the pitch of the first spirality obstacle is less than the pitch of the second spirality obstacle.
Compared with prior art, a kind of high-frequency pulse pinking combustion-powered apparatus of the present invention, it is designed with except fuel nozzle except at head of combustion chamber, also equidistantly devise multiple assisted fuel nozzle in the firing chamber section of detonating and pinking section, firing chamber is divided into multiple minizone, and each nozzle is responsible for an interval fuel supply, can reduce the filling time of firing chamber, improve the frequency of okperation of motor, the thrust that the increase motor unit time produces; In addition, devise plural serial stage pushing structure at pulse detonation combustor afterbody, can further improve the thrust of motor.
Further, because firing chamber spiral obstacle detonation wave strengthening structure adopts variable pitch design, the DDT distance that firing chamber detonation changes to pinking can be shortened under the prerequisite reducing engine chamber flow resistance.
[accompanying drawing explanation]
Fig. 1 is the overall pie graph of a kind of high-frequency pulse pinking of the present invention combustion-powered apparatus;
Fig. 2 is the plural serial stage pushing structure diagram representing the power plant shown in Fig. 1; .
Fig. 3 is the A-A direction view of Fig. 2.
Wherein: 1, main nozzle air pipe line; 2, main nozzle fuel conduit; 3, main nozzle; 4, head of combustion chamber end cap; 5, pulse detonation combustor; 6, spark plug; 7, combustion chamber ignition section; 8, pilot jet fuel conduit; 9, pilot jet air pipe line; 10, the firing chamber section of detonating; 11, the first spirality obstacle; 12, pilot jet; 13, the second spirality obstacle; 14, firing chamber pinking section; 15, plural serial stage pushing structure support plate; 16, plural serial stage pushing structural linkages; 17, jet pipe; 18, plural serial stage pushing structure; 19, combustion gas stream; 20, the first arc air inlet end face; 21, the first axisymmetric straight tube; 22, one-level pushing device; 23, pushing device support plate between the first order; 24, pushing device connecting rod between the first order; 25, the second arc air inlet end face; 26, the second axisymmetric straight tube; 27, secondary pushing device; 28, pushing device support plate between the second level; 29, pushing device connecting rod between the second level; 30, the 3rd arc air inlet end face; 31, the 3rd axisymmetric straight tube; 32, three grades of pushing devices.
[embodiment]
Below in conjunction with accompanying drawing, the specific embodiment of the invention is described in detail.
See Fig. 1 to Fig. 3, a kind of high-frequency pulse pinking combustion-powered apparatus of the present invention, comprises the pulse detonation combustor 5, jet pipe 17 and the plural serial stage pushing structure 18 that are connected successively from left to right.
Wherein, pulse detonation combustor 5 comprises the head of combustion chamber end cap 4, combustion chamber ignition section 7, the firing chamber section of detonating 10 and the firing chamber pinking section 14 that are connected successively from left to right, and the right-hand member of firing chamber pinking section 14 is connected with jet pipe 17; Head of combustion chamber end cap 4 is provided with main nozzle 3, and main nozzle 3 is provided with main nozzle air pipe line 1 and main nozzle fuel conduit 2; The circumference of combustion chamber ignition section 7 is provided with spark plug 6; The circumference of the firing chamber section of detonating 10 and firing chamber pinking section 14 in axial direction goes up and is equidistantly provided with some pilot jets 12, and pilot jet 12 is provided with pilot jet air pipe line 9 and pilot jet fuel conduit 8.Such main nozzle 3 and pilot jet 12 can be filled firing chamber simultaneously, make each nozzle only need the fuel in a bit of space, responsible firing chamber to supply, can reduce the firing chamber filling time, improve engine operating frequencies.
Further, jet pipe 17 is constrictor nozzle, and contraction ratio is 1.2 to 1.5, and convergence angle is 6 to 10 degree.The inwall of the firing chamber section of detonating 10 is provided with the first spirality obstacle 11, and the inwall of firing chamber pinking section 14 is provided with the second spirality obstacle 13, and the pitch of the first spirality obstacle 11 is less than the pitch of the second spirality obstacle 13.Because obstacle strengthening structure pitch is less, in firing chamber, burning mixture turbulivity is larger, intensity of heat exchange between air-flow is then stronger, therefore the transition distance DDT of detonation to pinking can be shortened, but more the inner flow resistance of puffer is larger for pitch, therefore, after adopting variable pitch design, DDT distance can be shortened while reduction motor flow resistance.
See Fig. 2 and Fig. 3, plural serial stage pushing structure 18 comprises the one-level pushing device 22, secondary pushing device 27 and the three grades of pushing devices 32 that are connected successively from left to right.Wherein, one-level pushing device 22 comprises the first arc air inlet end face 20 and the first axisymmetric straight tube 21, secondary pushing device 27 comprises the second arc air inlet end face 25 and the second axisymmetric straight tube 26, three grades of pushing devices 32 comprise the 3rd arc air inlet end face 30 and the 3rd axisymmetric straight tube 31; 4 plural serial stage pushing structural linkages 16 are evenly arranged on the circumference of the first arc air inlet end face 20, one end of 4 plural serial stage pushing structure support plates 15 is connected with corresponding plural serial stage pushing structural linkages 16, and its other end is connected with pulse detonation combustor 5 afterbody; Between 4 first order, pushing device connecting rod 24 is evenly arranged on the circumference of the second arc air inlet end face 25, and between 4 first order, one end of pushing device support plate 23 is connected with pushing device connecting rod between the corresponding first order 24, and its other end is connected with the first axisymmetric straight tube 21; Between 4 second level, pushing device connecting rod 29 is evenly arranged on the circumference of the 3rd arc air inlet end face 30, and between 4 second level, one end of pushing device support plate 28 is connected with pushing device connecting rod between the corresponding second level 29, and its other end is connected with the second axisymmetric straight tube 26.
When high-speed pulse pinking combustion gas enters one-level pushing device 22 from jet pipe 17 discharge, due to the effect of air-flow viscous force, the air intake motor of arc air inlet end face 20 upstream must be driven, the dynamic pressure of arc air inlet end face 20 upstream air stagnation pressure is caused to increase, static pressure reduces, and the static pressure of arc air inlet end face 20 air downstream is constant, this must produce additional thrust at arc air inlet end face 20 place due to pressure difference.Wherein, the direction of arrow is combustion gas stream 19.
In order to understand further the present invention, existing the present invention will be further described in conjunction with specific embodiments.
A kind of high-frequency pulse pinking combustion-powered apparatus of the present invention, comprises pulse detonation combustor 5, jet pipe 17 and plural serial stage pushing structure 18.Pulse detonation combustor 5 is formed primarily of head of combustion chamber end cap 4, combustion chamber ignition section 7, the firing chamber section of detonating 10 and firing chamber pinking section 14, and in the present embodiment, chamber diameter is 60mm, long 1300mm; Head of combustion chamber end cap 4 is positioned at the present embodiment foremost, and heart position is provided with main nozzle 3 wherein; Combustion chamber ignition section 7 is positioned at the downstream of head of combustion chamber end cap 4, long 300mm, is provided with igniting spark plug 6 at the middle place of combustion chamber ignition section 7 axial position; The firing chamber section of detonating 10 is positioned at the downstream of combustion chamber ignition section 7, long 400mm, is furnished with the first spirality obstacle 11 that pitch is 50mm, diameter is 8mm therein; Firing chamber pinking section 14 is positioned at the downstream of the firing chamber point section of detonating 10, long 600mm, and the second spirality obstacle 13 that pitch is 80mm, diameter is 8mm is equipped with in inside; Equidistantly devise seven pilot jets 12 at the axial position of the firing chamber section of detonating 10 and firing chamber pinking section 14, the distance between each pilot jet 12 is 120mm simultaneously; Jet pipe 17 is positioned at pinking section downstream, firing chamber, and contraction ratio is 1.5, and convergence angle is 6 degree; Plural serial stage pushing structure 18 and firing chamber are disposed coaxially on jet pipe 17 downstream, and four the plural serial stage pushing structure support plates 15 be evenly arranged by firing chamber pinking section 14 afterbody circumference and plural serial stage pushing structural linkages 16 form an entirety with pulse detonation combustor 5.
Namely the present embodiment can be used for air-breathing pulse detonation engine, is also applicable to rocket type pulse-knocking engine.The working procedure of the present embodiment high-frequency pulse pinking combustion-powered apparatus is: air and the fuel conduit of opening main nozzle 3 and each pilot jet 12, paired pulses detonation combustor 5 Fast Filling fuel, after filling fuels completes, close air and the fuel conduit of main nozzle 3 and each pilot jet 12, simultaneously by the indoor burning mixture of spark plug 6 ignition combustion, deflagration wave is formed in combustion chamber ignition section 7, deflagration wave is through being transformed into detonation wave gradually after the strengthening of fine pitch spirality obstacle 11 in the firing chamber section of detonating 10, detonation wave again after the second spirality obstacle 13 in firing chamber pinking section 14 further strengthening from jet pipe 17 Accelerating Removal, under the effect of air-flow viscous force, the pinking combustion gas of ejection drives jet pipe 17 ambient air to suck motor at a high speed, arc air inlet end face 20 place of one-level pushing device 22 is caused to form differential static pressure, and then generation additional thrust, high-speed fuel gas drives the air of the arc air inlet end face upstream of secondary pushing device 27 and three grades of pushing devices 32 to enter motor further after one-level pushing device 22, and produce additional thrust in the arc air inlet end of pushing structure at different levels, final combustion gas is expelled to air from the axisymmetric straight tube 31 of three grades of pushing devices 32, after pinking combustion gas discharges motor completely, open main nozzle air pipe line 1 and the pilot jet air pipe line 9 of main nozzle 3 and each pilot jet 12, fill in detonation chamber and put out separation gas, and then open main nozzle fuel conduit 2 and the pilot jet fuel conduit 8 of main nozzle 3 and each pilot jet 12, start the filling fuels of new round pulse detonation combustor, iterative cycles work like this.Because have employed 8 fuel nozzles in the present embodiment altogether, compared with the pulse-knocking engine only adopting head of combustion chamber 1 nozzle with tradition, the frequency of okperation of the present embodiment motor at least can improve seven times.
Claims (4)
1. a high-frequency pulse pinking combustion-powered apparatus, is characterized in that: comprise the pulse detonation combustor (5), jet pipe (17) and the plural serial stage pushing structure (18) that are connected successively from left to right; Wherein,
Pulse detonation combustor (5) comprises the head of combustion chamber end cap (4), combustion chamber ignition section (7), the firing chamber section of detonating (10) and the firing chamber pinking section (14) that are connected successively from left to right, and the right-hand member of firing chamber pinking section (14) is connected with jet pipe (17); Head of combustion chamber end cap (4) is provided with main nozzle (3), and main nozzle (3) is provided with main nozzle air pipe line (1) and main nozzle fuel conduit (2); The circumference of combustion chamber ignition section (7) is provided with spark plug (6); The circumference of the firing chamber section of detonating (10) and firing chamber pinking section (14) in axial direction goes up and is equidistantly provided with some pilot jets (12), and pilot jet (12) is provided with pilot jet air pipe line (9) and pilot jet fuel conduit (8);
Jet pipe (17) is constrictor nozzle, and contraction ratio is 1.2 to 1.5, and convergence angle is 6 to 10 degree;
Plural serial stage pushing structure (18) comprises one-level pushing device (22) connected successively from left to right, secondary pushing device (27) and three grades of pushing devices (32).
2. a kind of high-frequency pulse pinking combustion-powered apparatus according to claim 1, it is characterized in that: one-level pushing device (22) comprises the first arc air inlet end face (20) and the first axisymmetric straight tube (21), secondary pushing device (27) comprises the second arc air inlet end face (25) and the second axisymmetric straight tube (26), and three grades of pushing devices (32) comprise the 3rd arc air inlet end face (30) and the 3rd axisymmetric straight tube (31); Some plural serial stage pushing structural linkages (16) are evenly arranged on the circumference of the first arc air inlet end face (20), one end of some plural serial stage pushing structures support plate (15) is connected with corresponding plural serial stage pushing structural linkages (16), and its other end is connected with pulse detonation combustor (5) afterbody; Between some first order, pushing device connecting rod (24) is evenly arranged on the circumference of the second arc air inlet end face (25), between some first order, one end of pushing device support plate (23) is connected with pushing device connecting rod (24) between the corresponding first order, and its other end is connected with the first axisymmetric straight tube (21); Between some second level, pushing device connecting rod (29) is evenly arranged on the circumference of the 3rd arc air inlet end face (30), between some second level, one end of pushing device support plate (28) is connected with pushing device connecting rod (29) between the corresponding second level, and its other end is connected with the second axisymmetric straight tube (26).
3. a kind of high-frequency pulse pinking combustion-powered apparatus according to claim 2, it is characterized in that: plural serial stage pushing structure support plate (15) is 4 with the quantity of plural serial stage pushing structural linkages (16), between the first order, between pushing device support plate (23) and the first order, the quantity of pushing device connecting rod (24) is 4, and between the second level, between pushing device support plate (28) and the second level, the quantity of pushing device connecting rod (29) is 4.
4. a kind of high-frequency pulse pinking combustion-powered apparatus according to any one of claim 1 to 3, it is characterized in that: the inwall of the firing chamber section of detonating (10) is provided with the first spirality obstacle (11), the inwall of firing chamber pinking section (14) is provided with the second spirality obstacle (13), and the pitch of the first spirality obstacle (11) is less than the pitch of the second spirality obstacle (13).
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| CN107044361A (en) * | 2017-05-17 | 2017-08-15 | 西北工业大学 | A kind of pulse detonation rocket engines and control method with combustion-compensating device |
| CN108150305B (en) * | 2018-02-05 | 2023-05-12 | 西安航空学院 | Self-adaptive pulse detonation engine convergent nozzle |
| CN110762556B (en) * | 2019-10-14 | 2020-12-04 | 哈尔滨工程大学 | Gas-liquid two-phase detonating device |
| CN113898458A (en) * | 2021-11-08 | 2022-01-07 | 天津市津聿动力科技有限公司 | Diesel engine two-stage turbine series self-circulation pulse supercharging device and control method |
| CN114060141A (en) * | 2021-11-19 | 2022-02-18 | 天津大学 | Two-stage series pulse combined supercharging device of diesel engine and control method thereof |
| CN114060142A (en) * | 2021-11-19 | 2022-02-18 | 天津大学 | Double-turbine parallel pulse supercharging device of diesel engine and control method thereof |
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