CN103899435A - Combined pulse detonation engine detonation chamber - Google Patents
Combined pulse detonation engine detonation chamber Download PDFInfo
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- CN103899435A CN103899435A CN201410123565.9A CN201410123565A CN103899435A CN 103899435 A CN103899435 A CN 103899435A CN 201410123565 A CN201410123565 A CN 201410123565A CN 103899435 A CN103899435 A CN 103899435A
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Abstract
The invention discloses a combined pulse detonation engine detonation chamber. An ignition combination mode of a two-stage shock wave focusing device and pre-detonation pipes is adopted. A main detonation chamber is connected with an engine, and a first pre-detonation pipe and a second pre-detonation pip are fixed on two sides of the engine, and are mounted parallelly to the main detonation chamber through a first jet pipe and a second jet pipe respectively. Detonation jet led out from pre-detonation pipe outlets by the jet pipes firstly fills the main detonation chamber and a shock wave focusing cavity via an intensively-mixed and atomized gas-oil mixture, after filling, the detonation jet led out from the pre-detonation pipes enters the detonation chamber from outlets of the jet pipes to ignite the oil-gas mixture in the detonation chamber, and deflagration waves with leading shock waves are formed to be propagated forwards. The deflagration waves form strong shock waves under the action of a flow guide ring, and the strong shock waves ignite an explosible oil-gas mixture to form detonation waves and generate high positive thrust. Initiation of explosion of the pulse detonation engine detonation chamber within a short distance is realized, so that the engine is shortened, and working frequency of the pulse detonation engine is increased.
Description
Technical field
The invention belongs to detonation engine technical field, specifically, relate to a kind of combined type pulse detonation engine detonation chamber.
Background technique
The propulsion system of utilizing detonation wave to produce thrust comprises oblique detonation engine, rotation detonation engine, pulse-knocking engine, two-stage pulse-knocking engine etc.Pulse-knocking engine is to utilize periodic detonation wave to produce the propulsion system of thrust.General pulse-knocking engine is to produce deflagration ripple by plug ignition, and deflagration ripple forms local focus after obstacle accelerates, and the High Temperature High Pressure district of the detonation wave of overdriving, then forms stable detonation wave and propagate forward.But flame acceleration need to a very long segment distance to forming local focus, thereby limit the frequency of okperation of motor.What pre-explosion pipe adopted is the self-contained gaseous state easily detonating or liquid oxygenant and fuel, can detonate in very short distance, and the detonation wave that pre-explosion pipe is produced is transitioned into the method that method that main detonation chamber detonates is called pre-explosion pipe igniting.Utilize the method for pre-explosion pipe igniting can shorten the distance of detonating, but want the changeover portion between appropriate design pre-explosion pipe and main detonation chamber.Another scheme of utilizing that pre-explosion pipe is lighted a fire is to draw one thermojet from pre-explosion pipe to light main detonation chamber, and then flame is at main detonation chamber final detonation wave that forms after one section of obstacle accelerates.
The difference of two-stage pulse-knocking engine and general pulse-knocking engine is that it is to utilize shock wave to converge to produce detonation wave, produce high-speed flame by precombustion chamber fuel-rich combustion, then high-speed flame forms annular jet to gather the incident of heart mode by guide ring, after focusing on, concave surface chamber forms strong shock, the High Temperature High Pressure producing by the strong shock fuel gas mixture after fuel-rich combustion that detonates.
Although the frequency of okperation of two-stage pulse-knocking engine is very high, can reach in theory tens Kilohertzs, existing experimental research shows, the combustion mode in concave surface chamber, mainly taking detonation as main, does not form high frequency pinking.Reason is wherein many-sided, and as the burning of precombustion chamber could not produce the flammable mixed gas of the little molecule of high temperature that is rich in activation base, shock wave focus cavity concave surface is not optimum form.At present, major part mainly concentrates on numerical simulation aspect about the research work of two-stage pulse-knocking engine.
Summary of the invention
The deficiency existing for fear of prior art, the present invention proposes a kind of combined type pulse detonation engine detonation chamber, adopt two-stage shock wave focus device and pre-explosion pipe igniting compound mode, realizing pulse-knocking engine detonation chamber is detonating compared with short distance, thereby shorten the length of motor, improve the frequency of okperation of pulse-knocking engine.
The technical solution adopted for the present invention to solve the technical problems is: comprise motor, the first pre-explosion pipe, the second pre-explosion pipe, its feature is also to comprise main detonation chamber, flange, the first jet pipe, the second jet pipe, the first jet pipe outlet, the second jet pipe outlet, pole, shock wave focus cavity, oblique fire discharge orifice, guide ring, jet pipe, main detonation chamber is connected by flange with motor, the first pre-explosion pipe and the second pre-explosion pipe lay respectively at the both sides of motor, and by the first jet pipe and the installation parallel with main detonation chamber respectively of the second jet pipe, two jet pipe one end are positioned at main detonation chamber, two jet pipe end sidewalls have the first jet pipe outlet and the outlet of the second jet pipe, jet pipe exit opening direction is consistent with airintake direction, the other end of two jet pipes lays respectively in the first pre-explosion pipe and the second pre-explosion pipe, the end sidewalls of two jet pipes has pinking jet conduction hole, the pinking jet conduction hole center of circle is coaxial with pre-explosion pipe central shaft, shock wave focus cavity is positioned at main detonation chamber inner outlet position, is connected by pole and main detonation chamber, and guide ring is positioned at main detonation chamber outlet end, is fixedly connected with main detonation chamber by screw thread, and jet pipe is arranged on guide ring by bolt, described shock wave focus cavity is parabolic type, and cavity wall hoop is evenly equipped with multiple oblique fire discharge orifices, and oblique fire discharge orifice central axis gathers in the focus of parabolic type cavity.
The two ends distance that the first jet pipe and the second jet pipe are positioned at main detonation chamber is greater than 1/2 of main detonation chamber radius, but is less than the radius of main detonation chamber.
The first jet pipe outlet is identical with two jet pipe internal diameters with the aperture of the second jet pipe outlet.
The ratio of the cross-section area of shock wave focus cavity and the cross-section area of main detonation chamber is 1/2～1/3.
The channelization angle of guide ring is greater than 5 degree.
Beneficial effect
The combined type pulse detonation engine detonation chamber that the present invention proposes, adopts two-stage shock wave focus device and pre-explosion pipe igniting compound mode; Main detonation chamber is connected and communicates with motor, and the first pre-explosion pipe and the second pre-explosion pipe lay respectively at the both sides of motor, and by the first jet pipe and the installation parallel with main detonation chamber respectively of the second jet pipe; Jet pipe exports the pinking jet of drawing from pre-explosion pipe, gas mixture through fully mixing and atomization is first filled main detonation chamber and shock wave focus cavity, after filling, draw pinking jet from pre-explosion pipe and enter main detonation chamber from jet pipe outlet, the gas mixture igniting in main detonation chamber, forms and propagates forward with the deflagration wave of leading shock wave.Deflagration wave, under the effect of guide ring, forms two strands to heart jet, and heart jet is converged to generation strong shock in the concave surface collision of shock wave focus cavity, and strong shock ignites and can form detonation wave and produce larger positive thrust by quick-fried gas mixture.Detonation wave is propagated to jet pipe, after jet pipe expands, produces thrust, and realize pulse-knocking engine detonation chamber and detonating compared with short distance, thus the length of shortening motor, the frequency of okperation of raising pulse-knocking engine.
Brief description of the drawings
Below in conjunction with drawings and embodiments, a kind of combined type pulse detonation engine of the present invention detonation chamber is described in further detail.
Fig. 1 is combined type pulse detonation engine detonation chamber structural representation of the present invention.
Fig. 2 is shock wave focus cavity of the present invention and guide ring structural representation.
Fig. 3 is embodiments of the invention 1 structural representations.
Fig. 4 is embodiments of the invention 2 structural representations.
In figure:
1. main detonation chamber 2. flange 3. first jet pipe 4. second jet pipe 5. first jet pipe outlet 6. second jet pipes export 7. pole 8. shock wave focus cavitys 9. and slant 22. second groups of pre-explosion pipes of discharge orifice 10. guide ring 11. jet pipe 12. intake duct 13. orifice plate 14. first pre-explosion pipe fuel inlet 15. first pre-explosion pipe 16. second pre-explosion pipe fuel inlet 17. second pre-explosion pipe 18. pinking intensifier 19. 21. first groups of pre-explosion pipes of pinking jet conduction hole 20. motor
Embodiment
Embodiment 1
The present embodiment is the first preferred version, and two jet pipes can timesharing ignition operation; Two pre-explosion pipes are sequentially fired successively, and the frequency of okperation that makes main detonation chamber is the twice of pre-explosion pipe frequency of okperation, thereby improve greatly the frequency of okperation of motor.
Consult Fig. 1, Fig. 2, Fig. 3, the present embodiment combined type pulse detonation engine detonation chamber, by main detonation chamber 1, flange 2, the first jet pipe 3, the second jet pipe 4, the first jet pipe outlet 5, the second jet pipe outlet 6, pole 7, shock wave focus cavity 8, oblique fire discharge orifice 9, guide ring 10, jet pipe 11, intake duct 12, orifice plate 13, the first pre-explosion pipe fuel inlet 14, the first pre-explosion pipe 15, the second pre-explosion pipe fuel inlet 16, the second pre-explosion pipe 17, pinking intensifier 18, pinking jet conduction hole 19, motor 20 forms, main detonation chamber 1 is connected and is communicated by flange 2 with motor 20, the first pre-explosion pipe 15 and the second pre-explosion pipe 17 are separately fixed at the both sides of motor 20, and by the first jet pipe 3 and the second jet pipe 4 respectively with the parallel installation of main detonation chamber 1, one end of two jet pipes is fixed in main detonation chamber 1, in two jet pipe end sidewalls, have the first jet pipe outlet 5 and the second jet pipe outlet 6, jet pipe exit opening direction is consistent with airintake direction, the other end of the first jet pipe 3 and the second jet pipe 4 is separately fixed in the first pre-explosion pipe 15 and the second pre-explosion pipe 17, has pinking jet conduction hole 19 in the end sidewalls of two jet pipes, and pinking jet conduction hole 19 centers of circle are coaxial with pre-explosion pipe central shaft.Shock wave focus cavity 8 is arranged on main detonation chamber 1 inner outlet position, is fixedly connected with main detonation chamber 1 by pole 7; Guide ring 10 is fixed on main detonation chamber 1 outlet end, and is threaded connection with main detonation chamber 1, and jet pipe 11 is arranged on guide ring 10 by bolt.Shock wave focus cavity 8 is parabolic type, and cavity wall hoop is evenly equipped with multiple oblique fire discharge orifices 9, and oblique fire discharge orifice 9 central axis gather in the focus of parabolic type cavity.The oblique fire stream that slants discharge orifice in filling process can accelerate the interior gas mixture of cavity 8 and fill, simultaneously, deflagration wave forms the jet interactions of the poly-heart jet of multiply and guide ring guiding by oblique fire discharge orifice 9, produce strong shock, the High Temperature High Pressure that strong shock produces increases chemical reaction rate, the thermal discharge of chemical reaction increases, and has formed hot localised points and has promoted that deflagration wave changes to detonation wave.Deflagration wave forms the poly-heart jet of multiply by oblique fire discharge orifice 9, has strengthened the turbulivity of zone of combustion, and the blending of accelerating high-temperature fuel gas and not firing product, is of value to the formation of detonation wave.The channelization angle of guide ring 10 is that inclined-plane and the radial direction angulation of guide ring is greater than 5 degree, thereby play good guide functions, the deflagration wave of the leading shock wave of pilot tape converges to cavity, the gas mixture that the shock wave that converges rear generation can be detonated in cavity.
The end of the first pre-explosion pipe 15 has the first pre-explosion pipe fuel inlet 14, the end of the second pre-explosion pipe 17 has the second pre-explosion pipe fuel inlet 16, two independently solenoid valve control respectively the filling of oxygenant and fuel in the first pre-explosion pipe 15 and the second pre-explosion pipe 17, thereby control the frequency of okperation of two pre-explosion pipes.In the first pre-explosion pipe 15 and the second pre-explosion pipe 17, be respectively equipped with pinking intensifier 18 for accelerating flame, ensure that pre-explosion pipe goes out interruption-forming detonation wave, improve the frequency of okperation of pulse-knocking engine.
When engine operation, incoming flow enters main detonation chamber 1 by the intake duct 12 of motor fully to be mixed with fuel oil, in order to ensure the abundant mixing of the fuel-air that enters main detonation chamber 1, orifice plate 13 is installed to strengthen atomization and the blending of liquid fuel above at main detonation chamber 1.After main detonation chamber 1 is filled, the pinking jet attracting from pre-explosion pipe starts main detonation chamber 1 to light a fire, form two strands of deflagration waves with leading shock wave at main detonation chamber 1, deflagration wave continues to propagate forward after walking around the outer surface of shock wave focus cavity 8, under the effect of guide ring 10, form jet, and with the interior poly-heart jet interactions of cavity 8, the final gas mixture that forms one strong shock and detonate in cavity forms detonation wave, detonation wave is propagated to jet pipe under the effect of wall, after jet pipe expands, discharges at a high speed.
Embodiment 2
As shown in Figure 4, as the second preferred version of the present invention, jet pipe number can have multiple, under the permission of bulk, forms and intersects symmetric configuration according to axle centered by motor 20, and this intersection symmetric configuration can ensure the formation of detonation wave.In addition, more jet pipe can be divided into many groups, respectively organizes jet pipe sequentially fired work successively.The frequency of okperation that the frequency of okperation of starting owner's detonation chamber is pre-explosion pipe is multiplied by the number of grouping again, thereby greatly improves the frequency of okperation of motor.In the present embodiment four pre-explosion pipes are divided into two groups, two groups of pre-explosion pipes adopt the means of fixation that intersection is symmetrical, two relative pre-explosion pipes are one group, and two groups of pre-explosion pipes are controlled respectively the filling of fuel and oxygenant by solenoid valve, thereby accurately control the igniting of main detonation chamber 1.In the time that first group of pre-explosion pipe 21 starts main detonation chamber 1 to light a fire, second group of just stage in filling of pre-explosion pipe 22.In the time that second group of pre-explosion pipe 22 starts main detonation chamber 1 to light a fire, first group of pre-explosion pipe 21 is in the filling stage, first group of pre-explosion pipe 21 and second group of pre-explosion pipe 22 are alternately lighted a fire to main detonation chamber 1, the frequency of okperation of main detonation chamber 1 is the twice of pre-explosion pipe frequency of okperation, thereby greatly improves the frequency of okperation of motor.
As the third preferred version of the present invention, jet pipe circularizes layout around main detonation chamber 1, and this annular layout form makes pre-explosion pipe become a kind of little booster, as the assist device of motor supersonic flight.
Combined type pulse detonation engine detonation chamber of the present invention is in the time of work, pre-explosion pipe becomes separately a system, the fuel and the oxygenant that are packed into pre-explosion pipe from the first pre-explosion pipe fuel inlet 14 and the second pre-explosion pipe fuel inlet 16 are accurately controlled by solenoid valve, realize the accurate control of 1 firing time of main detonation chamber.Main detonation chamber 1 is in working unit circulation, fully the fuel air mixture of mixing and atomization starts to fill main detonation chamber 1, after main detonation chamber 1 is filled, the detonation wave that pre-explosion pipe forms starts main detonation chamber to light a fire by the first jet pipe 3 and the second jet pipe 4.Form deflagration wave at main detonation chamber, deflagration wave forms strong shock and forms localized hyperthermia zone of high pressure with the poly-heart jet interactions that oblique fire discharge orifice 9 forms after shock wave focus cavity 8 focuses on, then change detonation wave into and discharge to jet pipe 11, and produce very large thrust on cavity.Detonation wave is discharged at a high speed after jet pipe 11 fully expands, and reflects multiple tracks extensional wave and propagate to main detonation chamber 1, reduces the pressure in main detonation chamber 1.After exhaust process finishes, main detonation chamber restarts to fill fresh fuel oil and air mixture; After filling, the pinking jet that pre-explosion pipe forms also just enters main detonation chamber 1 by the first jet pipe 3 and the second jet pipe 4, and main detonation chamber 1 starts next work cycle.
Claims (5)
1. a combined type pulse detonation engine detonation chamber, comprise motor, the first pre-explosion pipe, the second pre-explosion pipe, characterized by further comprising main detonation chamber, flange, the first jet pipe, the second jet pipe, the first jet pipe outlet, the second jet pipe outlet, pole, shock wave focus cavity, oblique fire discharge orifice, guide ring, jet pipe, main detonation chamber is connected by flange with motor, the first pre-explosion pipe and the second pre-explosion pipe lay respectively at the both sides of motor, and by the first jet pipe and the installation parallel with main detonation chamber respectively of the second jet pipe, two jet pipe one end are positioned at main detonation chamber, two jet pipe end sidewalls have the first jet pipe outlet and the outlet of the second jet pipe, jet pipe exit opening direction is consistent with airintake direction, the other end of two jet pipes lays respectively in the first pre-explosion pipe and the second pre-explosion pipe, the end sidewalls of two jet pipes has pinking jet conduction hole, the pinking jet conduction hole center of circle is coaxial with pre-explosion pipe central shaft, shock wave focus cavity is positioned at main detonation chamber inner outlet position, is connected by pole and main detonation chamber, and guide ring is positioned at main detonation chamber outlet end, is fixedly connected with main detonation chamber by screw thread, and jet pipe is arranged on guide ring by bolt, described shock wave focus cavity is parabolic type, and cavity wall hoop is evenly equipped with multiple oblique fire discharge orifices, and oblique fire discharge orifice central axis gathers in the focus of parabolic type cavity.
2. combined type pulse detonation engine detonation chamber according to claim 1, is characterized in that: the two ends distance that the first jet pipe and the second jet pipe are positioned at main detonation chamber is greater than 1/2 of main detonation chamber radius, but is less than the radius of main detonation chamber.
3. combined type pulse detonation engine detonation chamber according to claim 1, is characterized in that: the first jet pipe outlet is identical with two jet pipe internal diameters with the aperture of the second jet pipe outlet.
4. combined type pulse detonation engine detonation chamber according to claim 1, is characterized in that: the ratio of the cross-section area of shock wave focus cavity and the cross-section area of main detonation chamber is 1/2～1/3.
5. combined type pulse detonation engine detonation chamber according to claim 1, is characterized in that: the channelization angle of guide ring is greater than 5 degree.
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Cited By (11)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104500272A (en) * | 2014-11-26 | 2015-04-08 | 南京航空航天大学 | Low-flow-resistant near-wall small-space annular shock wave focusing direct priming device |
| WO2016062155A1 (en) * | 2014-10-19 | 2016-04-28 | 赵晴堂 | Array multi-point set explosion-type pulse detonation engine |
| CN107605603A (en) * | 2017-08-28 | 2018-01-19 | 江苏大学 | A kind of ignition system for pulse-knocking engine |
| CN109653876A (en) * | 2019-01-14 | 2019-04-19 | 南京航空航天大学 | A kind of compact ignition and detonation device of short distance for continuous rotation detonation engine |
| CN109946086A (en) * | 2019-04-09 | 2019-06-28 | 西北工业大学 | A kind of band barrier detonation chamber design method can be used for PLIF measuring technique |
| CN110131071A (en) * | 2019-05-04 | 2019-08-16 | 西北工业大学 | A kind of pulse-knocking engine combustion chamber and its method of ignition |
| CN110410231A (en) * | 2019-07-08 | 2019-11-05 | 华中科技大学 | A kind of air suction type two-stage shock wave focus igniter motor combustion chamber and its working method |
| CN110516310A (en) * | 2019-07-31 | 2019-11-29 | 中国空气动力研究与发展中心 | Rotate the unsteady numerical simulations method of pinking back-pressure |
| CN112459927A (en) * | 2020-10-23 | 2021-03-09 | 南京理工大学 | Y-shaped small-size bidirectional predetonation ignition tube |
| CN113153569A (en) * | 2021-04-27 | 2021-07-23 | 西北工业大学 | Multi-pipe pulse detonation engine capable of achieving stable exhaust |
| CN114893322A (en) * | 2022-04-08 | 2022-08-12 | 中国人民解放军空军工程大学 | Axial shock wave incident detonation device with a plurality of micro shock tubes uniformly distributed in circumferential direction and operation method |
Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101806260A (en) * | 2010-03-04 | 2010-08-18 | 西北工业大学 | Multitube parallel pulse detonation combustion chamber and ignition detonation method thereof |
| US20110036067A1 (en) * | 2009-08-11 | 2011-02-17 | Rupp George D | Airflow modulation for dual mode combined cycle propulsion systems |
| CN201858046U (en) * | 2010-11-11 | 2011-06-08 | 西北工业大学 | Pulse detonation engine realizing secondary detonation |
| CN202578943U (en) * | 2012-03-31 | 2012-12-05 | 西北工业大学 | Jet ignition device for pulse detonation engine |
-
2014
- 2014-03-28 CN CN201410123565.9A patent/CN103899435B/en not_active Expired - Fee Related
Patent Citations (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US20110036067A1 (en) * | 2009-08-11 | 2011-02-17 | Rupp George D | Airflow modulation for dual mode combined cycle propulsion systems |
| CN101806260A (en) * | 2010-03-04 | 2010-08-18 | 西北工业大学 | Multitube parallel pulse detonation combustion chamber and ignition detonation method thereof |
| CN201858046U (en) * | 2010-11-11 | 2011-06-08 | 西北工业大学 | Pulse detonation engine realizing secondary detonation |
| CN202578943U (en) * | 2012-03-31 | 2012-12-05 | 西北工业大学 | Jet ignition device for pulse detonation engine |
Cited By (15)
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|---|---|---|---|---|
| WO2016062155A1 (en) * | 2014-10-19 | 2016-04-28 | 赵晴堂 | Array multi-point set explosion-type pulse detonation engine |
| CN104500272A (en) * | 2014-11-26 | 2015-04-08 | 南京航空航天大学 | Low-flow-resistant near-wall small-space annular shock wave focusing direct priming device |
| CN107605603A (en) * | 2017-08-28 | 2018-01-19 | 江苏大学 | A kind of ignition system for pulse-knocking engine |
| CN107605603B (en) * | 2017-08-28 | 2019-02-05 | 江苏大学 | A kind of ignition system for pulse-knocking engine |
| CN109653876B (en) * | 2019-01-14 | 2021-05-11 | 南京航空航天大学 | Short-distance compact ignition initiation device for continuous rotation detonation engine |
| CN109653876A (en) * | 2019-01-14 | 2019-04-19 | 南京航空航天大学 | A kind of compact ignition and detonation device of short distance for continuous rotation detonation engine |
| CN109946086A (en) * | 2019-04-09 | 2019-06-28 | 西北工业大学 | A kind of band barrier detonation chamber design method can be used for PLIF measuring technique |
| CN110131071A (en) * | 2019-05-04 | 2019-08-16 | 西北工业大学 | A kind of pulse-knocking engine combustion chamber and its method of ignition |
| CN110410231A (en) * | 2019-07-08 | 2019-11-05 | 华中科技大学 | A kind of air suction type two-stage shock wave focus igniter motor combustion chamber and its working method |
| CN110516310A (en) * | 2019-07-31 | 2019-11-29 | 中国空气动力研究与发展中心 | Rotate the unsteady numerical simulations method of pinking back-pressure |
| CN110516310B (en) * | 2019-07-31 | 2022-10-04 | 中国空气动力研究与发展中心 | Unsteady numerical simulation method for rotary detonation back pressure |
| CN112459927A (en) * | 2020-10-23 | 2021-03-09 | 南京理工大学 | Y-shaped small-size bidirectional predetonation ignition tube |
| CN113153569A (en) * | 2021-04-27 | 2021-07-23 | 西北工业大学 | Multi-pipe pulse detonation engine capable of achieving stable exhaust |
| CN113153569B (en) * | 2021-04-27 | 2022-10-28 | 西北工业大学 | Multi-pipe pulse detonation engine capable of stably exhausting |
| CN114893322A (en) * | 2022-04-08 | 2022-08-12 | 中国人民解放军空军工程大学 | Axial shock wave incident detonation device with a plurality of micro shock tubes uniformly distributed in circumferential direction and operation method |
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