CN103743571B - For the air heating apparatus of long-time supersonic combustion - Google Patents
For the air heating apparatus of long-time supersonic combustion Download PDFInfo
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- CN103743571B CN103743571B CN201310688119.8A CN201310688119A CN103743571B CN 103743571 B CN103743571 B CN 103743571B CN 201310688119 A CN201310688119 A CN 201310688119A CN 103743571 B CN103743571 B CN 103743571B
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Abstract
The present invention discloses a kind of air heating apparatus for long-time supersonic combustion, it comprises spray nozzle plate, firing chamber, circle change side collapsible tube, jet pipe and lighter, spray nozzle plate is provided with several for spraying the coaxial jet nozzle of hydrogen and oxygen-enriched air in firing chamber, described firing chamber in a tubular form, its two ends are separately installed with spray nozzle plate and circle change side collapsible tube, the square opening end of circle change side collapsible tube is provided with jet pipe, the tube wall of the close spray nozzle plate of described firing chamber is provided with lighter and connects mouth, lighter connects mouth and combustion chamber by lighter, to spray into pyrophoric flame to firing chamber, described firing chamber, circle change side collapsible tube is double-layer tube wall structure, cooling water circulation passage is all had between the two-layer tube wall of the two, and the outer wall of the two is provided with water inlet and water delivering orifice, jet pipe is also provided with cooling water circulation passage and water inlet and water delivering orifice.The invention solves existing air heating apparatus dissatisfactory problem in duration etc.
Description
Technical field
The present invention relates to the air heating apparatus for long-time supersonic combustion.
Background technology
Scramjet engine is the core of hypersonic Air-breathing Propulsion, has good application prospect in Aero-Space and national defence.At present, scramjet engine technology is just experiencing moves towards engineering development and flying demonstration stage from laboratory study, and this just needs scramjet engine to carry out a large amount of lecture experiment for a long time on ground.
At present, the main associated mode super burn model engine that adopts of supersonic combustion research carries out, and usually adopt heavy wall face metal material passive type of cooling cooling body temperature, working time is shorter, is generally no more than 10 second-times.
Supersonic combustion experiment table is the basic tool carrying out supersonic combustion experimental study.The capability and qualification of experiment table is mainly reflected in accurate, the reliable and automaticity that stagnation temperature that air heating apparatus can provide, stagnation pressure condition, duration, flow scale and operation control; In addition, realize spontaneous ignition occurring when fuel mixes with air, then the stagnation temperature of firing chamber gasflow mach number, static pressure, static temperature and gas and stagnation pressure have certain limit requirement, and existing air heating apparatus is not ideal enough in duration etc.
Summary of the invention
For existing air heating apparatus dissatisfactory problem in duration etc., the invention provides a kind of air heating apparatus for long-time supersonic combustion.
To achieve these goals, technical scheme of the present invention is as follows:
A kind of air heating apparatus for long-time supersonic combustion, it comprises spray nozzle plate, firing chamber, circle change side collapsible tube, jet pipe and lighter, described spray nozzle plate is provided with several for spraying the coaxial jet nozzle of hydrogen and oxygen-enriched air in firing chamber, described firing chamber in a tubular form, its two ends are separately installed with spray nozzle plate and circle change side collapsible tube, the square opening end of described circle change side collapsible tube is provided with jet pipe, the tube wall of the close spray nozzle plate of described firing chamber is provided with lighter and connects mouth, described lighter connects mouth and combustion chamber by lighter, to spray into pyrophoric flame to firing chamber, described firing chamber, circle change side collapsible tube is double-layer tube wall structure, cooling water circulation passage is all had between the two-layer tube wall of the two, and the outer wall of the two is provided with water inlet and water delivering orifice, described jet pipe is also provided with cooling water circulation passage and water inlet and water delivering orifice.
In order to ensure fully mixing and efficient burning of hydrogen and air, preferably, the length of described firing chamber is 1 ~ 2 times without adjacent nozzle turbulent closure scheme length on spray nozzle plate under fired state.
Preferably, described lighter comprises air inlet disk, mixed combustion pipe and go out flame section, described air inlet disk and go out the two ends that flame section is arranged on mixed combustion pipe respectively, described air inlet disk is provided with a spark plug, five enter air scoop and one enter hydrogen mouth, spark plug is positioned at the central authorities of air inlet disk, five are entered air scoop and one and enter on the same circle that hydrogen mouth is positioned at centered by spark plug, one of them enters the uropore center line angle all at 45 ° with the axis of mixed combustion pipe that the uropore center line of air scoop and enter hydrogen mouth, and this two uropores center line intersects, other four uropore center lines entering air scoop all become 21 ° of angles with the axis of mixed combustion pipe, and this four uropores center line intersects, described go out flame section flare, its small end is provided with flame-out port, and this flame-out port connects mouth with the lighter on firing chamber is connected.
Preferably, described spray nozzle plate, firing chamber, circle change side collapsible tube, jet pipe and lighter are made by the stainless steel material that the Chinese trade mark is 1Cr18Ni9C.
For the temperature and pressure in measuring point firearm, preferably, go out described in flame section and be also provided with temperature-measuring port and pressure tap.
For measuring the temperature and pressure in air heating apparatus, preferably, the described transition section justifying change side's collapsible tube is also provided with thermometric and connects mouth and pressure tap.
For shortening jet pipe length, reduce air-flow thermal loss, preferably, described jet pipe supersonic speed segment type line adopts Foelsch method design.
Spray nozzle plate of the present invention adopts coaxial jet nozzle to firing chamber spray hydrogen and oxygen-enriched air, and it not only can cooled nozzle, and the flame simultaneously formed and wall have a segment distance, can effectively reduce wall heat flux amount; The cooling effect of recirculated water active cooling structure of firing chamber, circle change side's collapsible tube and jet pipe can meet long supersonic combustion ground experiment; Air heating apparatus stagnation temperature stagnation pressure easily regulates, and flow scale easily expands, and ignition trigger is reliable, and completely, flow field is stablized, and thermal loss is few in burning, solves existing air heating apparatus dissatisfactory problem in duration etc.
Accompanying drawing explanation
Fig. 1 is the structural representation of an embodiment of the air heating apparatus for long-time supersonic combustion of the present invention;
Fig. 2 is the structural representation of the spray nozzle plate shown in Fig. 1;
Fig. 3 is the structural representation of the nozzle of coaxial jet shown in Fig. 2;
Fig. 4 is the schematic diagram of the firing chamber shown in Fig. 1;
Fig. 5 is the schematic diagram of the circle change side collapsible tube shown in Fig. 1;
Fig. 6 is the schematic diagram of the jet pipe shown in Fig. 1;
Fig. 7 is the schematic diagram of the lighter shown in Fig. 1;
In figure: 1, spray nozzle plate; 11, coaxial jet nozzle; 111, nozzle center; 112, circular passage; 2, firing chamber; 21, lighter connects mouth; 3, change side's collapsible tube is justified; 31, thermometric connects mouth; 32, pressure tap; 4, jet pipe; 5, lighter; 51, air inlet disk; 510, spark plug; 511, air scoop is entered; 512, hydrogen mouth is entered; 52, mixed combustion pipe; 53, flame section is gone out; 530, flame-out port; 531, temperature-measuring port; 532, pressure tap.
Embodiment
Hereinafter will be described in detail to embodiments of the invention by reference to the accompanying drawings.It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combination in any mutually.
As shown in Figure 1, the air heating apparatus for long-time supersonic combustion of the present embodiment comprises spray nozzle plate 1, firing chamber 2, circle change side collapsible tube 3, jet pipe 4 and lighter 5, described spray nozzle plate is provided with several for spraying the coaxial jet nozzle of hydrogen and oxygen-enriched air in firing chamber, firing chamber 2 in a tubular form, its two ends are separately installed with spray nozzle plate 1 and circle change side collapsible tube 3, the square opening end of circle change side collapsible tube 3 is provided with jet pipe 4, the tube wall of the close spray nozzle plate 1 of firing chamber 2 is provided with lighter and connects mouth 21, lighter 5 connects mouth 21 by lighter and is communicated with firing chamber 2, to spray into pyrophoric flame to firing chamber 2, firing chamber 2 and circle change side collapsible tube 3 are double-layer tube wall structure, cooling water circulation passage is all had between the two-layer tube wall of the two, and the outer wall of the two is provided with water inlet and water delivering orifice, jet pipe 4 is also provided with cooling water circulation passage and water inlet and water delivering orifice, firing chamber 2, circle change side collapsible tube 3 and jet pipe 4 all adopt recirculated water active cooling.
Air heating apparatus adopts the mode of " annealing in hydrogen atmosphere oxygenating " to heat, suitable with the content and normal air that make the oxygen in synthesis air-flow.Sparking mode adopts little fire to draw big fire.According to the requirement of simulated flight Mach number 6 ~ 7 and cooling loss, the technical indicator of air heating apparatus is set as: the highest stagnation temperature T=2200K, the highest stagnation pressure P=5MPa, maximum flow 2kg/s.Adopting CEA(chemicalequilibriumwithapplication) software calculates, and can obtain component and the parameter of hydrogen air burning gas under various design stagnation temperature, as shown in table 1.As seen from the table, for T=2200K, combusted air composition molal quantity ratio is N
2: O
2: H
2o=47:20.9:29.5, mean molecular weight μ=26, gas law constant R=320.
Table 1 hydrogen air burning parameter list (2kg/s flow)
Preferably, spray nozzle plate 1, firing chamber 2, circle change side collapsible tube 3, jet pipe 4 and the lighter 5 stainless steel material manufacture that all adopts the Chinese trade mark to be 1Cr18Ni9C.
spray nozzle plate 1
Because air stagnation temperature is very high, the fuel that regular air heating arrangement adopts and air insufflation mechanism are difficult to the operation of bearing the long period.For this reason, the present invention adopts coaxial jet designs of nozzles, hydrogen by nozzle center 111 spray of coaxial jet nozzle 11, and first with oxygen mix after oxygen-enriched air spray into firing chamber by being wrapped in outer circular passage 112.Like this, on the one hand can by air and hydrogen gas stream cooled nozzle, the combustion flame simultaneously formed after two bursts of air-flow mixing and wall have certain distance, can effectively reduce wall heat flux amount.In order to reduce single-nozzle thermal load, actual employing multiple nozzle composition spray nozzle plate, as Figure 2-3.
firing chamber 2
In order to ensure fully mixing and efficient burning of hydrogen and air, the length of firing chamber 2 is 1 ~ 2 times without adjacent nozzle turbulent closure scheme length on spray nozzle plate under fired state.In the present embodiment, firing chamber 2 adopts tubular to design, internal diameter Φ 220mm, length 600mm, as shown in Figure 4.
circle change side collapsible tube 3
The square opening of 70mm × 70mm is become by the round mouth of Φ 220mm; For measuring the temperature and pressure in air heating apparatus, the transition section of circle change side collapsible tube 3 being also provided with thermometric and connecing mouth 31 and pressure tap 32, as shown in Figure 5.
jet pipe 4
Whole jet pipe adopts two-dimensional design.
Suppose that nozzle throat place stagnation temperature is about 1800K, and static temperature is about 850K because the mixed combustion Guan Yuyuan side of change collapsible tube cools the air stagnation temperature loss caused be about 300 ~ 400K.Adopting CEA(chemicalequilibriumwithapplication) program calculates further, and this potpourri is in temperature (800-1800K) interval, and well heater air ratio ratio of specific heat γ is out about 1.26-1.33.During actual design supersonic nozzle, γ=1.3 of averaging.According to isentropic stream relation, each flow field parameter under design Mach number condition can be obtained, as shown in table 2.The present embodiment actual design parameter is entry of combustion chamber height 50mm, nominal venturi height 16.93mm, and corresponding nozzle exit size (H × W) is 50mm × 70mm.Supersonic nozzle venturi nominal size can be obtained as table 2 according to isentropic relation.
Table 2 isentropic stream parameter list, γ=1.3
Calculate with stagnation temperature 1800K, unit area (mm under unit stagnation pressure (MPa)
2) flow of venturi is:
m＝0.6673×10
6×10
－6/(319.8×1800)
0.5＝0.8795×10
－3kg/s
The flow of firing chamber under various incoming flow stagnation pressure of various sectional dimension and Mach number can be calculated thus, as shown in table 3.Under incoming flow stagnation pressure 1.13MPa and 1.8MPa, this jet pipe air mass flow is respectively about 1.2 and 1.9kg/s.Because air thermal loss cannot accurately predicting, air mass flow is as the criterion with actual measured value.
Table 3 supersonic nozzle discharge relation table
Adopt M=2.5 jet pipe, nozzle exit size (H × W) is 50mm × 70mm.Jet pipe supersonic speed segment type line adopts Foelsch method design, to shorten jet pipe length, reduces air-flow thermal loss; The design of subsonic speed section adopts dull contraction mode, as shown in Figure 6.Jet pipe total length is 200mm.
lighter 5
As shown in Figure 7, lighter 5 comprises air inlet disk 51, mixed combustion pipe 52 and go out flame section 53, mixed combustion pipe 52 in a tubular form, air inlet disk 51 and go out the two ends that flame section 53 is arranged on mixed combustion pipe 52 respectively, air inlet disk 51 is provided with a spark plug 510, five enter air scoop 511 and one enter hydrogen mouth 512, spark plug 510 is positioned at the central authorities of air inlet disk 51, five are entered air scoop 511 and one and enter on the same circle that hydrogen mouth 512 is positioned at centered by spark plug 510, one of them enters the uropore center line angle all at 45 ° with the axis of mixed combustion pipe 52 that the uropore center line of air scoop 511 and enter hydrogen mouth 512, and this two uropores center line intersects, other four uropore center lines entering air scoop 511 all become 21 ° of angles with the axis of mixed combustion pipe 52, and this four uropores center line intersects, go out flame section 53 flare, its small end is provided with flame-out port 530, and this flame-out port 530 and the lighter on firing chamber 2 connect mouth 21 is connected.
Preferably, go out described in flame section 53 and be also provided with temperature-measuring port 531 and pressure tap 532.
Above-mentioned lighter 5 with reference to the design of liquid-propellant rocket engine, stable performance.Air inlet disk 51 adopts mutual slap shot stream nozzle, and it is complete that mutual shock is conducive to mixing and burning.For the shallow bid hydrogen of lighting a fire and the air intake internal layer near spark plug 510, two strands of air-flows intersect before spark plug 510.For preventing spark match 510 and air inlet disk 51 to be burned, hydrogen and the air intersection of igniting have with a certain distance from air inlet disk 51.Air is entered by the air scoop 511 that enters of 5 Φ 2mm communicated, and hydrogen is entered in mixed combustion pipe by the hydrogen mouth 512 that enters of 1 Φ 2mm.
Spray nozzle plate of the present invention adopts coaxial jet nozzle to firing chamber spray hydrogen and oxygen-enriched air, and it not only can cooled nozzle, and the flame simultaneously formed and wall have a segment distance, can effectively reduce wall heat flux amount; The cooling effect of recirculated water active cooling structure of firing chamber, circle change side's collapsible tube and jet pipe can meet long supersonic combustion ground experiment; Air heating apparatus stagnation temperature stagnation pressure easily regulates, and flow scale easily expands, and ignition trigger is reliable, and completely, flow field is stablized, and thermal loss is few in burning, solves existing air heating apparatus dissatisfactory problem in duration etc.
The foregoing is only the preferred embodiments of the present invention, be not limited to the present invention, for a person skilled in the art, the present invention can have various modifications and variations.Within the spirit and principles in the present invention all, any amendment done, equivalent replacement, improvement etc., all should be included within protection scope of the present invention.
Claims (7)
1. the air heating apparatus for long-time supersonic combustion, it is characterized in that: comprise spray nozzle plate, firing chamber, circle change side collapsible tube, jet pipe and lighter, described spray nozzle plate is provided with several for spraying the coaxial jet nozzle of hydrogen and oxygen-enriched air in firing chamber, described firing chamber in a tubular form, its two ends are separately installed with spray nozzle plate and circle change side collapsible tube, the square opening end of described circle change side collapsible tube is provided with jet pipe, the tube wall of the close spray nozzle plate of described firing chamber is provided with lighter and connects mouth, described lighter connects mouth and combustion chamber by lighter, to spray into pyrophoric flame to firing chamber, described firing chamber, circle change side collapsible tube is double-layer tube wall structure, cooling water circulation passage is all had between the double-layer tube wall of the two, and the outer wall of the two is provided with water inlet and water delivering orifice, described jet pipe is also provided with cooling water circulation passage and water inlet and water delivering orifice.
2. the air heating apparatus for long-time supersonic combustion according to claim 1, it is characterized in that: described lighter comprises air inlet disk, mixed combustion pipe and go out flame section, described air inlet disk and go out the two ends that flame section is arranged on mixed combustion pipe respectively, described air inlet disk is provided with a spark plug, five enter air scoop and one enter hydrogen mouth, spark plug is positioned at the central authorities of air inlet disk, five are entered air scoop and one and enter on the same circle that hydrogen mouth is positioned at centered by spark plug, one of them enters the uropore center line angle all at 45 ° with the axis of mixed combustion pipe that the uropore center line of air scoop and enter hydrogen mouth, and this two uropores center line intersects, other four uropore center lines entering air scoop all become 21 ° of angles with the axis of mixed combustion pipe, and this four uropores center line intersects, described go out flame section flare, its small end is provided with flame-out port, and this flame-out port connects mouth with the lighter on firing chamber is connected.
3. the air heating apparatus for long-time supersonic combustion according to claim 1, is characterized in that: the length of described firing chamber is 1 ~ 2 times without adjacent nozzle turbulent closure scheme length on spray nozzle plate under fired state.
4. the air heating apparatus for long-time supersonic combustion according to claim 1, is characterized in that: described spray nozzle plate, firing chamber, circle change side collapsible tube, jet pipe and lighter are made by the stainless steel material that the Chinese trade mark is 1Cr18Ni9C.
5. the air heating apparatus for long-time supersonic combustion according to claim 2, is characterized in that: described in go out in flame section to be also provided with temperature-measuring port and pressure tap.
6. the air heating apparatus for long-time supersonic combustion according to claim 1, is characterized in that: the transition section of described circle change side collapsible tube is also provided with thermometric and connects mouth and pressure tap.
7. the air heating apparatus for long-time supersonic combustion according to claim 1, is characterized in that: described jet pipe supersonic speed segment type line adopts Foelsch method design.
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| CN106765309B (en) * | 2016-12-12 | 2019-07-23 | 中国科学院力学研究所 | A kind of direct-connected gaseous film control device for supersonic combustion |
| CN113375894B (en) * | 2021-06-07 | 2022-06-24 | 北京航空航天大学 | Water circulation cooling type hydrogen and temperature controllable air ground test system |
| CN113958426B (en) * | 2021-10-27 | 2023-03-21 | 西安航天动力研究所 | Thrust chamber scale test device |
| CN115219100B (en) * | 2022-09-21 | 2022-11-25 | 中国空气动力研究与发展中心空天技术研究所 | Total pressure measuring structure of combustion heater |
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| US8746050B2 (en) * | 2008-09-19 | 2014-06-10 | Omar Cueto | Fuel injection feedback system and method |
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| RU2186357C2 (en) * | 2000-06-30 | 2002-07-27 | Открытое акционерное общество "А.Люлька-Сатурн" | Device determining boundary of appearance of instability of operation process in gas generator of liquid-propellant rocket engine |
| CN1664532A (en) * | 2005-04-22 | 2005-09-07 | 中国科学院力学研究所 | Air heater |
| CN101782231A (en) * | 2010-03-22 | 2010-07-21 | 中国科学院广州能源研究所 | Minitype gas turbine burner with secondary air inlet structure |
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Effective date of registration: 20190821 Address after: 230000 Tianmen Lake Industrial Park, West of Tianmen Road and South of Jinxiu Avenue, Hefei Economic and Technological Development Zone, Anhui Province Patentee after: Hefei Zhongke Chongming Technology Co., Ltd. Address before: 100190 Beijing City, North Fourth Ring Road West, No. 15, No. Patentee before: Institute of Mechanics of Chinese Academy of Sciences |