CN102174913A - Pulse detonation engine with ejector and method for processing main detonation tube - Google Patents
Pulse detonation engine with ejector and method for processing main detonation tube Download PDFInfo
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- CN102174913A CN102174913A CN2011100516312A CN201110051631A CN102174913A CN 102174913 A CN102174913 A CN 102174913A CN 2011100516312 A CN2011100516312 A CN 2011100516312A CN 201110051631 A CN201110051631 A CN 201110051631A CN 102174913 A CN102174913 A CN 102174913A
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Abstract
The invention provides a pulse detonation engine with an ejector and a method for processing a main detonation tube. The invention is characterized in that one end of an ejector is a horn-shaped expansion section, the wall surface of the expansion section is a 1/4 arch wall surface; the relation between the radius R of an arc section and the inner diameter D of a cylindrical section is as follows: 2/5is less than or equal to R/Dis less than or equal to 3/5; the ejector and a main detonation tube are installed coaxially, the relation between the inner diameter d of the main detonation tubes and D is as follows: 2/5is less than or equal to d/Dis less than or equal to 3/5; L represents the axial distance the main detonation tube stretches into the ejector, the relation between L and d is as follows: 2is less than or equal to L/dis less than or equal to 6; a spiral channel is arranged in the tube wall of the main detonation tube. In the invention, by designing the entrance structure of the ejector, the structural relationship between the main detonation tube and the ejector and the spiral channel in the tube wall of the main detonation tube, reignited fuel oil can be fully heated inside the tube wall, which is conducive to the reduction of DDT (deflagration to detonation transition) distance, the lowering of the temperature of the main detonation tube and the lengthening of the thermal fatigue life of the main detonation tube.
Description
Technical field
The present invention relates to engine art, be specially a kind of pulse-knocking engine and main detonation tube processing method that has ejector.
Background technique
Pulse-knocking engine (PDE) is a kind of new concept engine that utilizes the pulsed detonation wave to produce thrust, because pulse-knocking engine still is in the primary stage of research, so have many aspects to be faced with a challenge and a difficult problem, especially increase the motor power aspect.At present, concerning the PDE of a fixed volume, generally can improve the thrust performance by dual mode: a kind of is to improve recurrence rate, and a kind of is the momentum that improves unit pulse.
For second method, can increase thrust by the structure that changes intake duct, pinking section, jet pipe etc., but from recent years domestic and international research, only by above-mentioned means to significantly improvement of thrust.Increase an ejector and adopt, then can obviously increase the thrust of motor at the motor afterbody.For the ejector structure a lot of researchs are arranged both at home and abroad at present, but when mostly research concentrates on main flow and is stable state, and the research of main flow when being unsteady state is fewer, have only fragmentary report to propose the ejector entrance shape mainly based on circular bluff body, the pneumatic area of this structure is little, be unfavorable for that ejector entrainments surrounding atmosphere, thereby reduced the amount of insinuating, reduced the pushing effect of ejector.In addition, if can light a fire (regnition) pinking once more, also will improve the thrust of motor greatly in ejector inside.
When pulse-knocking engine is worked, the high frequency detonation wave is by the detonation tube inner wall surface, a part of heat is passed to tube wall, cause the engine tube wall temperature sharply to rise, the performance of this part heat paired pulses detonation engine is without any contribution, can make the motor tube wall overheated and aspects such as life-span of its work, stability are produced harm on the contrary.Discover simultaneously when being used for the fuel oil temperature of supply engine when higher, can make fuel oil realize flash distillation easily, thereby reduce conversion (DDT) distance of detonation to pinking.Having studied at present both at home and abroad utilizes fuel oil to come the cooled engine tube wall, absorb tube wall used heat and improve fuel oil temperature, then the fuel delivery motor is used, use fuel oil to cool off to the tube wall under the different detonation frequencies, can reduce the tube wall temperature of motor on the one hand, improve the thermal fatigue life of motor; Use the fuel oil that has absorbed used heat as motor fuel on the other hand, improve the atomizing and the evaporation of fuel oil, be easy to form pinking, shorten the DDT distance simultaneously.But present most heat exchanger structure heat exchange is inhomogeneous, and is mobile poor, has potential safety hazard.
Summary of the invention
The technical problem that solves
In order effectively to improve pulse-knocking engine thrust, the present invention proposes a kind of pulse-knocking engine and main detonation tube processing method that has ejector.
Technological scheme
Technological scheme of the present invention is:
Described a kind of pulse-knocking engine that has ejector, comprise main detonation tube, it is characterized in that: also include ejector, ejector import one end is tubaeform extending section, all the other are cylindrical section, the extending section wall is 1/4 circular arc wall, and the pass of radius of arc R and cylindrical section inside diameter D is: 2/5≤R/D≤3/5; Ejector and the coaxial installation of main detonation tube, and the pass of main detonation tube inner diameter d and ejector cylindrical section inside diameter D is: 2/5≤d/D≤3/5, main detonation tube stretches into the interior end end face of ejector and the axial distance of ejector extending section outer end end face is L, the pass of L and main detonation tube inner diameter d is: 2≤L/d≤6, the tube wall inside of main detonation tube has helical duct, helical duct has import on main detonation tube outer wall, import and oil intake nozzle are connected, helical duct has some outlets on main detonation tube stretches into an end end face in the ejector, outlet is connected with fuel nozzle.
Preferred version of the present invention is characterized in that: the pass of radius of arc R and cylindrical section inside diameter D is: R/D=0.5.
Preferred version of the present invention is characterized in that: the pass of main detonation tube inner diameter d and ejector cylindrical section inside diameter D is: d/D=0.5.
The described processing method that has the main detonation tube of helical duct is characterized in that: at first process main detonation tube tube wall, pipe thickness equals conventional detonation tube pipe thickness and helical duct degree of depth sum; Secondly on the main detonation tube tube wall that processes, leave spiral groove; The sleeve pipe that to process an internal diameter at last be main detonation tube external diameter, embed the main detonation tube of band spiral groove in the sleeve pipe and the two ends welding fixing.
Beneficial effect
The present invention is by the design ejector makeup of the imports and main detonation tube and ejector structural relation, realized injection effect preferably, designed the helical duct in the main detonation tube tube wall simultaneously, make the fuel oil of regnition in tube wall, fully to heat, both helped reducing the DDT distance of secondary pinking, also can reduce the temperature of main detonation tube, improve the thermal fatigue life of main detonation tube.
Description of drawings
Fig. 1: structural representation of the present invention;
Fig. 2: planimetric map of the present invention;
Fig. 3: ejector structural drawing;
Wherein: 1, ejector; 2, fuel nozzle; 3, helical duct; 4, oil intake nozzle; 5, main detonation tube.
Embodiment
Below in conjunction with specific embodiment the present invention is described.
Embodiment:
With reference to accompanying drawing 1 and accompanying drawing 2, present embodiment comprises ejector 1, fuel nozzle 2, helical duct 3, oil intake nozzle 4 and main detonation tube 5.
With reference to accompanying drawing 3, ejector 1 import one end is tubaeform extending section, and all the other are cylindrical section, and the extending section wall is 1/4 circular arc wall, and the pass of radius of arc R and cylindrical section inside diameter D is R/D=0.5.With reference to accompanying drawing 2, ejector 1 and main detonation tube 5 coaxial installations; To the requirement of ejector 1 cylindrical section inside diameter D, one wants to provide the injection secondary flow enough areas, and two will guarantee ejector 1 inside and extraneous pressure reduction, are d/D=0.5 so get the pass of main detonation tube 5 inner diameter d and ejector 1 cylindrical section inside diameter D in the present embodiment; The degree of depth that main detonation tube 5 extend into ejector 1 inside also can exert an influence to the effect of injection effect and regnition, get that main detonation tube 5 stretches into an end end face in the ejector 1 and the axial distance of ejector 1 extending section outer end end face is L, in the present embodiment, the pass of L and main detonation tube inner diameter d is L/d=4.
With reference to accompanying drawing 2, in order to make full use of the fuel oil of the heat heating regnition that produces when main detonation tube 5 is worked, reduce the DDT distance of secondary pinking, have helical duct 3 in main detonation tube 5 tube wall inside, helical duct 3 has import on main detonation tube 5 outer wall, import and oil intake nozzle 4 are connected, and helical duct 3 has three outlets on main detonation tube 5 stretches into an end end face in the ejector 1, and each outlet all with a fuel nozzle 2 is connected.Fuel oil enters helical duct 3 from oil intake nozzle 4, and fully the heating back directly sprays into ejector 1 inside from fuel nozzle 2 ejections therein, utilizes the afterbody flame regnition of main detonation tube 5.
The processing method that has the main detonation tube of helical duct is: at first process main detonation tube tube wall, pipe thickness equals conventional detonation tube pipe thickness and helical duct degree of depth sum; Secondly on the main detonation tube tube wall that processes, leave spiral groove; The sleeve pipe that to process an internal diameter at last be main detonation tube external diameter, weld in the main detonation tube embedding sleeve pipe of band spiral groove and two ends fixing, and the position perforate of corresponding helical duct import on sleeve pipe also has the fuel outlet of UNICOM's helical duct as fuel inlet on the tube wall end face.
During present embodiment work, oil intake nozzle 4 is connected with outer oil pipe, and oil pressure is 0.6MP-0.7MP.The normal master pulse detonation engine that starts, after engine operation was stable, main detonation tube afterbody had the detonation flame ejection, and injection has air to enter in the ejector simultaneously, and be in oil-poor state in the ejector this moment; Feed gasoline then in helical duct, the feeding amount cooperates ejector specifically to hold gas flow, guarantees that can keep equivalent proportion in the ejector is 1; This moment, main detonation tube afterbody fuel nozzle had gasoline ejection, because gasoline heats through helical duct, thus can become gaseous state at short notice, and mix with air-flow that injection advances, be equivalent to the fuel filling process of detonation engine; Final these mixtures are lighted at the flame place of main detonation tube ejection, thereby form the secondary pinking.Because the ejector caliber is bigger, thus directly use the igniter igniting to be difficult to successfully, and use the flame ignition of main detonation tube afterbody effectively to address this problem.Generally speaking, main detonation tube caliber is big more, and cross section connects just big more, just can produce bigger thrust thus, the secondary pinking just is equivalent to produce again a pinking in ejector, so can produce bigger thrust, so in the regular hour, can effectively improve the thrust magnitude of motor integral body.
Claims (4)
1. pulse-knocking engine that has ejector, comprise main detonation tube, it is characterized in that: also include ejector, ejector import one end is tubaeform extending section, all the other are cylindrical section, the extending section wall is 1/4 circular arc wall, and the pass of radius of arc R and cylindrical section inside diameter D is: 2/5≤R/D≤3/5; Ejector and the coaxial installation of main detonation tube, and the pass of main detonation tube inner diameter d and ejector cylindrical section inside diameter D is: 2/5≤d/D≤3/5, main detonation tube stretches into the interior end end face of ejector and the axial distance of ejector extending section outer end end face is L, and the pass of L and main detonation tube inner diameter d is: 2≤L/d≤6; The tube wall inside of main detonation tube has helical duct, and helical duct has import on main detonation tube outer wall, and import and oil intake nozzle are connected, and helical duct has some outlets on main detonation tube stretches into an end end face in the ejector, and outlet is connected with fuel nozzle.
2. a kind of pulse-knocking engine that has ejector according to claim 1 is characterized in that: the pass of radius of arc R and cylindrical section inside diameter D is: R/D=0.5.
3. a kind of pulse-knocking engine that has ejector according to claim 1 is characterized in that: the pass of main detonation tube inner diameter d and ejector cylindrical section inside diameter D is: d/D=0.5.
4. have the main detonation tube processing method of helical duct in the claim 1, it is characterized in that: at first process main detonation tube tube wall, pipe thickness equals conventional detonation tube pipe thickness and helical duct degree of depth sum; Secondly on the main detonation tube tube wall that processes, leave spiral groove; The sleeve pipe that to process an internal diameter at last be main detonation tube external diameter, embed the main detonation tube of band spiral groove in the sleeve pipe and the two ends welding fixing.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100516312A CN102174913A (en) | 2011-03-03 | 2011-03-03 | Pulse detonation engine with ejector and method for processing main detonation tube |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN2011100516312A CN102174913A (en) | 2011-03-03 | 2011-03-03 | Pulse detonation engine with ejector and method for processing main detonation tube |
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| CN102174913A true CN102174913A (en) | 2011-09-07 |
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| CN2011100516312A Pending CN102174913A (en) | 2011-03-03 | 2011-03-03 | Pulse detonation engine with ejector and method for processing main detonation tube |
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Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107762661A (en) * | 2017-11-27 | 2018-03-06 | 西北工业大学 | A kind of pulse-knocking injection ultra-combustion ramjet combined engine |
| CN109209678A (en) * | 2018-09-18 | 2019-01-15 | 西北工业大学 | A kind of pulse-knocking propulsion device based on re-generatively cooled structure |
| CN115217701A (en) * | 2022-08-12 | 2022-10-21 | 西北工业大学 | Porous fuel atomization mixing structure and method for air-breathing pulse detonation engine |
Citations (5)
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|---|---|---|---|---|
| CN86206671U (en) * | 1986-09-02 | 1987-07-22 | 大连工学院 | Automatic pressure-regulating heating-type injector |
| CN2084579U (en) * | 1990-11-14 | 1991-09-11 | 张杰厚 | Gasified oil burning stove |
| US20060174606A1 (en) * | 2005-02-10 | 2006-08-10 | Stram Michael A | High static thrust valveless pulse-jet engine with forward-facing intake duct |
| CN201610802U (en) * | 2010-02-04 | 2010-10-20 | 西北工业大学 | Knocking tube of a spiral type pulse knocking engine |
| CN202023655U (en) * | 2011-03-03 | 2011-11-02 | 西北工业大学 | Pulse detonation engine with ejector |
-
2011
- 2011-03-03 CN CN2011100516312A patent/CN102174913A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN86206671U (en) * | 1986-09-02 | 1987-07-22 | 大连工学院 | Automatic pressure-regulating heating-type injector |
| CN2084579U (en) * | 1990-11-14 | 1991-09-11 | 张杰厚 | Gasified oil burning stove |
| US20060174606A1 (en) * | 2005-02-10 | 2006-08-10 | Stram Michael A | High static thrust valveless pulse-jet engine with forward-facing intake duct |
| CN201610802U (en) * | 2010-02-04 | 2010-10-20 | 西北工业大学 | Knocking tube of a spiral type pulse knocking engine |
| CN202023655U (en) * | 2011-03-03 | 2011-11-02 | 西北工业大学 | Pulse detonation engine with ejector |
Non-Patent Citations (2)
| Title |
|---|
| 黄希桥等: "引射器入口形状对PDE的性能影响实验", 《工程热物理学报》, vol. 29, no. 9, 30 September 2008 (2008-09-30), pages 1486 - 1490 * |
| 黄希桥等: "引射器轴向位置对PDE的性能影响实验", 《推进技术》, vol. 30, no. 2, 30 April 2009 (2009-04-30), pages 219 - 223 * |
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN107762661A (en) * | 2017-11-27 | 2018-03-06 | 西北工业大学 | A kind of pulse-knocking injection ultra-combustion ramjet combined engine |
| CN107762661B (en) * | 2017-11-27 | 2019-05-10 | 西北工业大学 | A kind of pulse-knocking injection ultra-combustion ramjet combined engine |
| CN109209678A (en) * | 2018-09-18 | 2019-01-15 | 西北工业大学 | A kind of pulse-knocking propulsion device based on re-generatively cooled structure |
| CN109209678B (en) * | 2018-09-18 | 2020-12-08 | 西北工业大学 | Pulse detonation propulsion device based on regenerative cooling structure |
| CN115217701A (en) * | 2022-08-12 | 2022-10-21 | 西北工业大学 | Porous fuel atomization mixing structure and method for air-breathing pulse detonation engine |
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Application publication date: 20110907 |