CN114427689B - Disc-shaped rotary detonation combustion chamber capable of realizing supersonic flow field observation - Google Patents
Disc-shaped rotary detonation combustion chamber capable of realizing supersonic flow field observation Download PDFInfo
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- CN114427689B CN114427689B CN202210066087.7A CN202210066087A CN114427689B CN 114427689 B CN114427689 B CN 114427689B CN 202210066087 A CN202210066087 A CN 202210066087A CN 114427689 B CN114427689 B CN 114427689B
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- 238000002485 combustion reaction Methods 0.000 title claims abstract description 66
- 238000005474 detonation Methods 0.000 title claims abstract description 48
- 239000000446 fuel Substances 0.000 claims abstract description 24
- 230000003287 optical effect Effects 0.000 claims abstract description 24
- 239000007921 spray Substances 0.000 claims abstract description 13
- 230000001133 acceleration Effects 0.000 claims description 14
- 230000015572 biosynthetic process Effects 0.000 abstract description 3
- 230000003993 interaction Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 5
- 239000007800 oxidant agent Substances 0.000 description 5
- 230000001590 oxidative effect Effects 0.000 description 5
- 230000000694 effects Effects 0.000 description 4
- 238000002347 injection Methods 0.000 description 4
- 239000007924 injection Substances 0.000 description 4
- 230000008569 process Effects 0.000 description 4
- UFHFLCQGNIYNRP-UHFFFAOYSA-N Hydrogen Chemical compound [H][H] UFHFLCQGNIYNRP-UHFFFAOYSA-N 0.000 description 3
- 239000001257 hydrogen Substances 0.000 description 3
- 229910052739 hydrogen Inorganic materials 0.000 description 3
- 238000005259 measurement Methods 0.000 description 3
- 238000010586 diagram Methods 0.000 description 2
- 239000002737 fuel gas Substances 0.000 description 2
- 239000007789 gas Substances 0.000 description 2
- 238000004088 simulation Methods 0.000 description 2
- 230000009471 action Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 238000004364 calculation method Methods 0.000 description 1
- 238000010276 construction Methods 0.000 description 1
- 238000013461 design Methods 0.000 description 1
- 238000002474 experimental method Methods 0.000 description 1
- 230000002349 favourable effect Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 238000012544 monitoring process Methods 0.000 description 1
- 230000008520 organization Effects 0.000 description 1
- 230000010355 oscillation Effects 0.000 description 1
- 230000000737 periodic effect Effects 0.000 description 1
- 230000000644 propagated effect Effects 0.000 description 1
- 239000003380 propellant Substances 0.000 description 1
- 238000011160 research Methods 0.000 description 1
- 230000035939 shock Effects 0.000 description 1
- 238000012360 testing method Methods 0.000 description 1
- 238000011144 upstream manufacturing Methods 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/28—Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M15/00—Testing of engines
- G01M15/02—Details or accessories of testing apparatus
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- General Physics & Mathematics (AREA)
- Fluidized-Bed Combustion And Resonant Combustion (AREA)
- Pressure-Spray And Ultrasonic-Wave- Spray Burners (AREA)
Abstract
The invention discloses a disc-shaped rotary knocking combustion chamber capable of realizing ultrasonic flow field observation, and particularly relates to the technical field of ramjet engines. The device comprises two cover plates which are arranged at intervals, a disc-shaped cavity is formed between the two cover plates, an air collecting cavity, a supersonic speed accelerating section, an expanding section and a combustion chamber are sequentially arranged from the center to the edge of the cavity, the thickness of the air collecting cavity is larger than that of the supersonic speed accelerating section, one side of the expanding section which is in a horn shape and has a small opening is connected with the supersonic speed accelerating section, a plurality of fuel spray holes are circumferentially distributed in the supersonic speed expanding section, and optical observation windows are arranged on the supersonic speed accelerating section and the combustion chamber; the center of any cover plate is provided with an air inlet communicated with the air collection cavity, each cover plate is provided with a plurality of lifting lugs, and the two lifting lugs corresponding to each other are connected through bolts. The technical scheme of the invention solves the problem that the conventional rotary detonation combustion chamber is unfavorable for the formation and observation of a supersonic flow field, and can be used for observing a specific wave system structure under rotary detonation back pressure.
Description
Technical Field
The invention relates to the technical field of ramjet engines, in particular to a disc-shaped rotary detonation combustor capable of realizing ultrasonic flow field observation.
Background
In a rotary detonation ramjet engine, detonation waves are rotated and propagated at high speed in a combustion chamber, the frequency reaches thousands of hertz, the peak pressure can reach several megapascals, and the combustion chamber pressure has significant differences along the circumferential direction, so that high-frequency periodic pulsating pressure is formed. The complex and severe combustion back pressure environment can influence the flow process in the supersonic speed accelerating section, and can cause choking of an air inlet channel and non-starting under severe conditions; and meanwhile, the combustion back pressure is mutually coupled with the flow, mixing process and the like of the propellant, so that the stable propagation of the rotary detonation wave is greatly influenced. Therefore, the research of interaction between the rotary knock back pressure and the supersonic velocity incoming flow is developed, the fuel injection mixing process under the action of the rotary knock back pressure is clarified, the evolution characteristic of the wave system structure in the supersonic velocity acceleration section along with the propagation of the detonation wave is obtained, and the method has important significance for efficient and stable operation of the rotary knock ramjet engine.
In the experiment, the injection mixing process of fuel and the motion evolution rule of a shock wave system need to be measured by means of optical equipment such as a high-speed camera and schlieren, and the optical path arrangement of the optical equipment generally requires that an optical path is perpendicular to an observed object, so that the influence of light refraction is reduced. The conventional rotary detonation ramjet engine combustion chamber is of a circular ring structure, so that optical observation of interaction of detonation waves and supersonic incoming flows is difficult to develop. In the prior art, a disc-shaped rotary detonation combustion chamber (shown in fig. 1) is convenient for optical observation, and in the combustion chamber, fuel and oxidant directly participate in rotary detonation combustion reaction after injection is completed at the head of the combustion chamber. In addition, most of fuel and oxidant of the conventional disc-shaped rotary detonation combustion chamber are injected from the outer edge of the combustion chamber, combustion products are ejected from the central outlet of the combustion chamber, and the flow channel is in a convergent form, so that the formation of a supersonic flow field is not facilitated.
Disclosure of Invention
The invention aims to provide a disc-shaped rotary detonation combustor capable of realizing ultrasonic flow field observation, and solves the problem that the conventional rotary detonation combustor is unfavorable for ultrasonic flow field formation and observation.
In order to achieve the above purpose, the technical scheme of the invention is as follows: the disc-shaped rotary detonation combustion chamber capable of realizing ultrasonic flow field observation comprises two cover plates which are arranged at intervals, a disc-shaped cavity is formed between the two cover plates, an air collection cavity, an ultrasonic acceleration section, an expansion section and a combustion chamber are sequentially arranged in the cavity from the center to the edge, the thickness of the air collection cavity is larger than that of the ultrasonic acceleration section, one side of the expansion section which is in a horn shape and has a small opening is connected with the ultrasonic acceleration section, a plurality of fuel spray holes are circumferentially distributed in the expansion section, optical observation windows are arranged on the ultrasonic acceleration section and the combustion chamber, and the optical observation windows are used for schlieren or high-speed photographing optical paths; the center of any cover plate is provided with an air inlet hole communicated with the air collection cavity, each cover plate is provided with a plurality of lifting lugs, and the two lifting lugs which correspond to each other are connected through bolts.
Further, the cross sections of the supersonic acceleration section and the combustion chamber are equal straight sections.
Through the arrangement, the optical observation window is conveniently arranged on the supersonic speed accelerating section and the combustion chamber, and meanwhile, as the air flow direction flows from the center of the disc-shaped combustion chamber to the outer diameter direction, the disc-shaped combustion chamber flow passage is integrally shown as an expanding flow passage, the flow area is continuously increased along the flow direction, the acceleration of the air flow in the supersonic speed accelerating section is conveniently realized, and the heat release addition of fuel in the combustion chamber and the timely discharge of combustion products are facilitated.
Further, a plurality of fuel spray holes are uniformly distributed on the expansion section of each cover plate in the circumferential direction.
Through the arrangement, the problem that detonation waves reversely enter a supersonic speed acceleration section at the upstream of the fuel spray hole is avoided, and therefore normal observation of a wave system structure formed by interaction of the detonation pressure of the supersonic speed acceleration Duan Nabao and supersonic speed inflow is ensured. Meanwhile, the fuel spray holes are uniformly distributed along the circumferential direction, so that the fuel mixing effect is enhanced, and the stable propagation of the rotary detonation wave is ensured.
Further, two first thread locating holes which are distributed at intervals are formed in the lifting lug of any one cover plate, and a second thread locating hole which is coaxially arranged with any one first thread locating hole is formed in the lifting lug of the other cover plate.
Through the arrangement, the relative angle of the two cover plates can be adjusted, different arrangement modes (namely, the arrangement modes of the fuel spray holes on two sides are arranged at intervals or aligned) of the fuel spray holes on the two cover plates are ensured, and therefore the combustion chamber has the capability of researching the influence effect of the arrangement modes of the different fuel spray holes.
Further, the detonation tube is tangentially arranged at the 1/4 flow direction position of the combustion chamber.
Through the arrangement, the fuel and the oxidant have a certain mixing distance, so that the mixing effect of the fuel and the oxidant is ensured, and meanwhile, the detonating tube is arranged along the tangential direction, so that the generated heat jet flow can enter the combustion chamber in the tangential direction, and the quick establishment of the rotary detonation flow field structure is facilitated.
Compared with the prior art, the beneficial effect of this scheme:
Compared with a conventional annular rotary detonation combustion chamber, the circular disc-shaped combustion chamber is favorable for light path arrangement, and has great convenience for developing optical observation. Meanwhile, the supersonic speed accelerating section is arranged in the disc-shaped flow channel, so that air flow can be accelerated to a supersonic speed state, and then tissues at the downstream of the supersonic speed accelerating section are subjected to rotary detonation combustion, so that the disc-shaped combustion chamber has the capability of observing a flow field of interaction of detonation waves and supersonic speed incoming flows.
Drawings
FIG. 1 is a cross-sectional view of a disk-shaped rotary detonation combustor of the background art for facilitating optical observations;
FIG. 2 is an isometric view of a disc-shaped rotary detonation combustor for enabling supersonic flow field observations in accordance with example 1;
FIG. 3 is a cross-sectional view of a disc-shaped rotary detonation combustor for achieving supersonic flow field observations in accordance with example 1;
FIG. 4 is a schematic view showing a specific structure of a rotary detonation combustor in embodiment 1;
FIG. 5 is a graph of high frequency pressure of a rotary detonation combustor in example 1;
FIG. 6 is a pressure cloud of the flow field structure in a rotary detonation combustor of example 1;
FIG. 7 is a density gradient cloud of flow field structure in a rotary detonation combustor of example 1;
Fig. 8 is a schematic diagram of the arrangement of the observation optical path of the supersonic flow field in embodiment 1.
Detailed Description
The invention is described in further detail below by way of specific embodiments:
Reference numerals in the drawings of the specification include: the device comprises a cover plate 1, an air collecting cavity 2, a supersonic speed accelerating section 3, an expanding section 4, a combustion chamber 5, a fuel spray hole 6, an air inlet 7, a lifting lug 8, a detonation tube 9, an optical observation window 10, a light source 11, a lens 12, a first concave reflecting mirror 13, a first plane reflecting mirror 14, a second plane reflecting mirror 15, a second concave reflecting mirror 16, a knife edge 17 and a high-speed camera 18.
Example 1
As shown in fig. 2 and 3: a disc-shaped rotary detonation combustor capable of realizing ultrasonic flow field observation comprises two cover plates 1 which are arranged at intervals and have coincident axes. A disc-shaped cavity is formed between the two cover plates 1, and an air collection cavity 2, a supersonic speed accelerating section 3, an expanding section 4 and a combustion chamber 5 are sequentially arranged from the center to the edge of the cavity. The thickness of the air collection cavity 2 is larger than that of the supersonic speed accelerating section 3, one side of the expanding section 4 which is horn-shaped and has a small opening is connected with the supersonic speed accelerating section 3, the cross sections of the supersonic speed accelerating section 3 and the combustion chamber 5 are equal straight sections, the supersonic speed accelerating section 3 and the combustion chamber 5 are respectively provided with an optical observation window 10, and the optical observation windows 10 are used for schlieren or high-speed shooting optical path arrangement. A plurality of fuel spray holes 6 are uniformly distributed on the expansion section 4 in the circumferential direction. The center of the cover plate 1 positioned at the left side is provided with an air inlet hole 7 communicated with the air collecting cavity 2, each cover plate 1 is provided with three lifting lugs 8 distributed at equal intervals along the circumferential direction, and the two lifting lugs 8 corresponding to each other are connected through bolts. Two first thread locating holes which are distributed at intervals are formed in the lifting lug 8 of the left side cover plate 1, and a second thread locating hole which is coaxial with any one of the first thread locating holes is formed in the lifting lug 8 of the right side cover plate 1. The detonation tube 9 is arranged tangentially at the 1/4 flow direction position of the combustion chamber 5.
When the high-pressure air enters the air collection cavity 2 in the center of the disc-shaped combustion chamber 5 and flows to the periphery, the high-pressure air enters the expansion section 4 after being accelerated in the supersonic acceleration section 3, a circle of fuel spray holes distributed in the expansion section 4 can enable fuel to enter the expansion section 4 and then be mixed with air inflow to form combustible mixed gas, the combustible mixed gas enters the combustion chamber 5 and is detonated, stable detonation waves can be formed in the combustion chamber 5, and high-temperature fuel gas generated by detonation combustion is discharged from the periphery of the combustion chamber 5.
To verify the feasibility of rotary detonation of the disc-shaped combustion chamber structure presented in this scheme, numerical simulations were performed on the combustion chamber of this configuration, with the configuration and dimensions of the combustion chamber employed in the numerical simulations being shown in fig. 4. The fuel and oxidant employed are hydrogen and air, respectively. The air entering the air collection cavity 2 is mixed with the injected hydrogen in the expansion section 4 after the acceleration of the supersonic acceleration section 3 is completed, then enters the combustion chamber 5 to jointly organize rotary detonation combustion, and high-temperature fuel gas generated by the combustion is discharged out of the combustion chamber 5 along the periphery. The boundary conditions for the inlet of the air collection chamber 2 and the hydrogen fuel injection are shown in table 1 below, and the back pressure at the outlet of the combustion chamber 5 is 100kPa.
Table 1:
According to the scheme, the disc-shaped combustion chamber 5 is detonated in a tangential detonating mode, and after a certain time of adjustment, a combustion chamber 5 pressure curve with uniform oscillation as shown in fig. 5 is finally obtained, which shows that a stably-propagating detonation wave is formed in the disc-shaped combustion chamber 5. The pressure monitoring data of the combustion chamber 5 shows that the propagation frequency of the detonation wave is 1562.5Hz, and the propagation speed of the detonation wave can be calculated to be about 2258m/s by combining the inner diameter of the disc combustion chamber 5. The flow field structure of the disc combustion chamber 5 shown in fig. 6 and 7 shows that the air is accelerated in the supersonic acceleration section 3, the maximum Mach number can reach Ma2.6, the interaction of detonation wave and supersonic incoming flow forms an obvious wave system structure, and the necessary condition for carrying out optical measurement is shown in the combustion chamber 5 with the configuration.
In general, the disc-shaped rotary detonation combustor 5 provided by the scheme can realize stable organization of rotary detonation waves, and the interaction of rotary detonation back pressure and incoming flow forms an obvious wave system structure, so that the calculation result verifies the rationality of the technical scheme, and a foundation is laid for developing supersonic flow field optical measurement in the next step.
Example 2
This embodiment differs from embodiment 1 only in that: in this embodiment, a reflective schlieren measurement system is adopted, the schematic diagram of the light path arrangement is shown in fig. 8, the lens 12 images the light source 11 at the slit to form the slit light source 11, the slit light source 11 is located at the focal point of the first concave mirror 13, the slit light source 11 is reflected by the first concave mirror 13 to become parallel light, then the direction of the parallel light is changed by the first plane mirror 14, the parallel light passes through the non-uniform flow field to be refracted to different degrees, then the light is reflected to the second concave mirror 16 by the second plane mirror 15, the knife edge 17 is located at the focal point of the second concave mirror 16, the light reflected by the second concave mirror is cut off by half after passing through the knife edge 17, and the rest enters the high-speed camera 18, so as to finally realize the observation of the flow field.
It can be seen that, due to the simple configuration of the combustion chamber 5, the arrangement of the optical paths is very conventional when it is observed in the test, and no additional design is required, which means that there is sufficient convenience when the disc-shaped combustion chamber 5 according to the present invention is optically observed.
The foregoing is merely exemplary of the present application and the details of construction and/or the general knowledge of the structures and/or characteristics of the present application as it is known in the art will not be described in any detail herein. It should be noted that modifications and improvements can be made by those skilled in the art without departing from the structure of the present application, and these should also be considered as the scope of the present application, which does not affect the effect of the implementation of the present application and the utility of the patent. The protection scope of the present application is subject to the content of the claims, and the description of the specific embodiments and the like in the specification can be used for explaining the content of the claims.
Claims (2)
1. A disc-shaped rotary detonation combustor capable of realizing ultrasonic flow field observation is characterized in that: the device comprises two cover plates which are arranged at intervals, a disc-shaped cavity is formed between the two cover plates, an air collecting cavity, a supersonic speed accelerating section, an expanding section and a combustion chamber are sequentially arranged in the cavity from the center to the edge, the thickness of the air collecting cavity is larger than that of the supersonic speed accelerating section, one side of the expanding section which is horn-shaped and has a small opening is connected with the supersonic speed accelerating section, a plurality of fuel spray holes are circumferentially distributed in the expanding section, optical observation windows are respectively arranged on the supersonic speed accelerating section and the combustion chamber, and the optical observation windows are used for schlieren or high-speed shooting optical path arrangement; an air inlet hole communicated with the air collection cavity is formed in the center of any cover plate, a plurality of lifting lugs are arranged on each cover plate, and two lifting lugs corresponding to each other are connected through a bolt;
the cross sections of the supersonic acceleration section and the combustion chamber are equal straight sections;
The expansion section of each cover plate is uniformly distributed with a plurality of fuel spray holes along the circumferential direction;
Two first thread locating holes which are distributed at intervals are formed in the lifting lug of any one cover plate, and a second thread locating hole which is coaxially arranged with any one first thread locating hole is formed in the lifting lug of the other cover plate.
2. The disc-shaped rotary detonation combustor capable of realizing ultrasonic flow field observation according to claim 1, wherein the combustor comprises: detonating tubes are tangentially arranged at 1/4 flow direction positions of the combustion chamber.
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| CN202210066087.7A CN114427689B (en) | 2022-01-20 | 2022-01-20 | Disc-shaped rotary detonation combustion chamber capable of realizing supersonic flow field observation |
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| CN217004537U (en) * | 2022-01-20 | 2022-07-19 | 中国空气动力研究与发展中心空天技术研究所 | Disc-shaped rotary detonation combustion chamber capable of realizing supersonic flow field observation |
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| JP3901629B2 (en) * | 2002-11-11 | 2007-04-04 | 石川島播磨重工業株式会社 | Annular swirl diffusion flame combustor |
| EP1730447A1 (en) * | 2004-03-31 | 2006-12-13 | Alstom Technology Ltd | Burner |
| EP2075508B1 (en) * | 2006-10-20 | 2018-05-23 | IHI Corporation | Gas turbine combustor |
| CN101949551A (en) * | 2010-09-09 | 2011-01-19 | 北京航空航天大学 | Premix and pre-evaporation combustion chamber |
| US8528338B2 (en) * | 2010-12-06 | 2013-09-10 | General Electric Company | Method for operating an air-staged diffusion nozzle |
| JP6086391B2 (en) * | 2011-08-22 | 2017-03-01 | トクァン, マジェドTOQAN, Majed | Annular cylindrical combustor with graded and tangential fuel-air nozzles for use in gas turbine engines |
| CN104870780B (en) * | 2012-10-12 | 2017-03-08 | 阿卜杜拉国王科技大学 | detonation standing wave engine |
| US9134029B2 (en) * | 2013-09-12 | 2015-09-15 | Siemens Energy, Inc. | Radial midframe baffle for can-annular combustor arrangement having tangentially oriented combustor cans |
| CN103868067B (en) * | 2014-03-12 | 2016-08-24 | 中国人民解放军国防科学技术大学 | The gas burner elements of supersonic speed blowtorch |
| JP2017146062A (en) * | 2016-02-19 | 2017-08-24 | 国立大学法人名古屋大学 | Rotation detonation engine |
| US11761635B2 (en) * | 2017-04-06 | 2023-09-19 | University Of Cincinnati | Rotating detonation engines and related devices and methods |
| CN109489070A (en) * | 2018-11-23 | 2019-03-19 | 东方电气集团东方汽轮机有限公司 | A kind of gas-turbine combustion chamber cyclone and component |
| CN109737456B (en) * | 2018-12-25 | 2020-11-20 | 北京动力机械研究所 | Combustion chamber cylinder with annular ribs |
| CN110578603B (en) * | 2019-08-23 | 2021-06-22 | 南京航空航天大学 | A kerosene-based disc rotary detonation turbine engine |
| CN111520761B (en) * | 2020-04-22 | 2022-02-01 | 中国空气动力研究与发展中心 | Rotary detonation combustion chamber capable of realizing observation of flow field structure of isolation section |
| CN213300150U (en) * | 2020-04-22 | 2021-05-28 | 中国空气动力研究与发展中心 | Rotary detonation combustion chamber capable of realizing observation of flow field structure of isolation section |
| CN213272699U (en) * | 2020-06-10 | 2021-05-25 | 中国空气动力研究与发展中心 | Standing vortex combustor value class oil gas matching device |
| CN111765491B (en) * | 2020-08-04 | 2024-05-14 | 中国科学院工程热物理研究所 | Natural gas turbine micro-premixing combustion chamber applied to wet air circulation |
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