CN102966974B - Supersonic combustor wall surface concave cavity structure and engine combustor comprising same - Google Patents
Supersonic combustor wall surface concave cavity structure and engine combustor comprising same Download PDFInfo
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- CN102966974B CN102966974B CN201210552292.0A CN201210552292A CN102966974B CN 102966974 B CN102966974 B CN 102966974B CN 201210552292 A CN201210552292 A CN 201210552292A CN 102966974 B CN102966974 B CN 102966974B
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Abstract
The invention provides a supersonic combustor wall surface concave cavity structure and an engine combustor comprising the same. The supersonic combustor wall surface concave cavity structure comprises a mounting base (10), wherein a combustor wall surface concave cavity (40) is arranged in the mounting base (10); the upstream of the combustor wall surface concave cavity (40), positioned on the air inlet side, is equipped with a flow guiding hole (22); and correspondingly, the downstream of the flow guiding hole (22) is equipped with a concave cavity upstream fuel spray hole (21); the concave cavity upstream fuel spray hole (21) is nearer to the flow guiding hole (22); the downstream of the concave cavity upstream fuel spray hole (21) is equipped with a flow guiding hole outlet (27) which is communicated with the flow guiding hole (22); and the flow guiding hole outlet (27) is communicated with the concave cavity upstream fuel spray hole (21). The supersonic combustor wall surface concave cavity structure provided by the invention has a simple structure, can urge the ignition of fuels in the concave cavity before the ignition, and can reinforce the jet combustion of the fuels after the ignition.
Description
Technical field
The present invention relates to engine ignition technical field, in particular to a kind of supersonic combustor wall surface concave cavity structure and the engine chamber comprising it.
Background technology
Cavity Flame Holder is widely used in scramjet engine combustion chamber at present.Supersonic flow flows through cavity can form recirculating zone in cavity, and flame can be made to reside in wherein all the time, and as the fuel that new burning things which may cause a fire disaster sustained ignition upstream is come, thus realize flame stabilization.Cavity can collect propellant spray in supersonic speed combustion chamber, mixing strengthens and flame stabilization acts on all over the body, in raising Investigation of Scramjet Engine Performance, played important effect.
Propellant spray/igniting/flame stabilization/cooling integration cavity common in current engineering, it contains propellant spray, igniting, flame stabilization integration, using cavity as basic configuration, in cavity upstream or/and bottom spray fuel, torch/plasma igniter is also contained in concave bottom portion.
Patent " a kind of cavities for supersonic speed combustion chamber " (publication number CN101245921) discloses a kind of cavities for supersonic speed combustion chamber, comprise two front side walls, two rear walls and diapire, the equal downstream of surface area of rear wall and front side wall is shunk gradually, form the groove of similar " dovetail " type, this invention mainly reduces the aerodynamic drag that cavities produces.
Patent " a kind of supersonic speed combustion chamber scheme of Tai Jie groove composite injection structure " (publication number CN101435586) discloses a kind of supersonic speed combustion chamber scheme of novel Tai Jie cavity composite injection structure, mainly before combustion chamber step and combustion chamber cavity, increase fuel nozzle, jointly spray for the fuel in combustion chamber and use, this invention is mainly used for the abundant mixing promoting fuel and air, ensures in the igniting of the fuel of supersonic flow and smooth combustion.
Paper " Flame Characteristics and Fuel Entrainment Inside a Cavity Flame Holder in a Scramjet Combustor " lists the scheme that the pneumatic throat of following employing is jammed and spark plug acting in conjunction is lighted a fire.This scheme adopts in cavity internal placement spark plug and cavity sprays H2 as pilot flame, and causes the scheme of promotes igniting of being jammed at the pneumatic venturi of cavity arranged downstream.
Paper " Experimental Study of Cavity ?Strut Combustionin Supersonic Flow " proposes a kind of cavity combinationally used with support plate, support plate is for strengthening the injection of fuel to center main flow area, cavity rear wall sprays the ignition and combustion for strengthening in cavity while adopting air and fuel, spark plug is arranged in the middle of the diapire of cavity.
Can find out, the design of current cavity has had a large amount of version, and corresponding fuel sprays also has kinds of schemes, and generally, suitable cavity design can spatially form suitable recirculating zone, coordinates with propellant spray, thus stable firmly flame.Meanwhile, due to the high temperature low speed environments of cavity inside, igniting is generally arranged on cavity inside.What the scheme that current enhancing is lighted a fire adopted has two kinds usually, and one is directly spray into fuel in cavity inside or fill spray spraying into fuel while into air, makes to there is continuous print gaseous mixture; Two is arrange pneumatic being jammed in downstream, for expanding Disengagement zone, makes the flame of ignition process can be diffused into larger region.Usually the disturbing flow device arranging the types such as support plate for the common scheme of enhanced burning manages to improve the penetration that wall fuel sprays, and ensureing uniform fuel distribution to spurt into main flow center simultaneously.
But adopt above-mentioned method for designing, following shortcoming can be there is:
1. under Supersonic Stream condition, cavity mass exchange rate is low, and the fuel in outside, cavity recirculating zone sprays, and easily form the lean combustion of recirculating zone, the injection in cavity recirculating zone easily forms the fuel-rich of recirculating zone, all unfavorable for igniting;
2. adopt the scheme (air that such as fills spray in cavity inside, downstream arrange pneumatic venturi and be jammed) strengthening igniting to need to increase additional high pressure source of the gas;
3. adopt and improve fuel spray penetration degree thus the scheme of enhanced burning and need to arrange the parts such as support plate, these parts can produce larger resistance, and cause very large difficulty to thermal protection.
Summary of the invention
The present invention aims to provide a kind of supersonic combustor wall surface concave cavity structure and comprises its engine chamber, and structure is simple, can promote that cavity fuel is lighted a fire before ignition, strengthens fuel jet burning after igniting.
To achieve these goals, according to an aspect of the present invention, provide a kind of supersonic combustor wall surface concave cavity structure, comprise mount pad, combustion chamber wall surface cavity is provided with in mount pad, the upstream being positioned at air inlet side of combustion chamber wall surface cavity is provided with pod apertures, the downstream correspondence of pod apertures is provided with cavity upstream fuel spray orifice, cavity upstream fuel spray orifice is near pod apertures, cavity upstream fuel spray orifice downstream is provided with the pod apertures be connected with pod apertures and exports, and pod apertures outlet is to cavity upstream fuel spray orifice.
Further, the air inlet side of combustion chamber wall surface cavity is provided with cavity leading edge step, cavity leading edge step includes cavity upstream fuel spray orifice and the pod apertures of multiple vertical setting, multiple cavity upstream fuel spray orifice is arranged along the first longitudinal surface interval, multiple pod apertures is arranged along the second longitudinal surface interval being parallel to the first longitudinal surface, each cavity upstream fuel spray orifice is all connected to fuel inlet, pod apertures is not connected in cavity leading edge step with cavity upstream fuel spray orifice, wherein, with pocket base wall place plane for horizontal plane, first longitudinal surface vertical level.
Further, combustion chamber wall surface cavity also comprises the vertical spaced multiple pocket base wall fuel jet orifice of the 3rd longitudinal surface along being positioned at combustion chamber wall surface cavity, 3rd longitudinal surface is parallel to the first longitudinal surface, and the bottom of multiple pocket base wall fuel jet orifice is all connected to fuel inlet.
Further, pod apertures outlet is arranged in the horizontal direction, and pod apertures outlet and pocket base wall fuel jet orifice one_to_one corresponding orthorhombic phase pair.
Further, the axis of the outlet of corresponding cavity upstream fuel spray orifice, pod apertures, pod apertures and pocket base wall fuel jet orifice is positioned on the same fore-and-aft plane perpendicular to the first fore-and-aft plane.
Further, the axis perpendicular that exports of pod apertures and pod apertures.
Further, the first lateral connection passage be connected by each cavity upstream fuel spray orifice and the first longitudinal interface channel be connected with fuel inlet by the first lateral connection passage is also provided with in cavity leading edge step.
Further, the first lateral connection passage is arranged near the roof of cavity leading edge step.
Further, combustion chamber wall surface cavity also comprises the second lateral connection passage be connected by multiple pocket base wall fuel jet orifice and the second longitudinal interface channel be connected with fuel inlet by the second lateral connection passage.
Further, pod apertures outlet is arranged near pocket base wall, and pocket base wall fuel jet orifice is arranged near the inner side longitudinal shelf terrace of cavity leading edge step.
Further, cavity leading edge step also includes the 3rd lateral connection passage multiple pod apertures be connected.
According to a further aspect in the invention, provide a kind of engine chamber, comprise distance piece and be arranged on the supersonic combustor wall surface concave cavity structure on distance piece, this supersonic combustor wall surface concave cavity structure is above-mentioned supersonic combustor wall surface concave cavity structure.
Apply technical scheme of the present invention, supersonic combustor wall surface concave cavity structure, comprise mount pad, combustion chamber wall surface cavity is provided with in mount pad, the upstream being positioned at air inlet side of combustion chamber wall surface cavity is provided with pod apertures, and the downstream correspondence of pod apertures is provided with cavity upstream fuel spray orifice, and cavity upstream fuel spray orifice is near pod apertures, cavity upstream fuel spray orifice downstream is provided with the pod apertures be connected with pod apertures and exports, and pod apertures outlet is to cavity upstream fuel spray orifice.After the successful ignition of combustion chamber, after fuel jet orifice jet combustion district sets up and is stable, combustion chamber wall surface cavity is inner due to burning heat release effect formation higher-pressure region, shock train is formed before the higher-pressure region of simultaneously burning, the static pressure at pod apertures place is much smaller than cavity Inner stagnant pressure, combustion gas in cavity is exported through pod apertures reflux by pod apertures and sprays from pod apertures, play the fuel preheating that cavity upstream fuel spray orifice is sprayed, and improve jet penetration, strengthen mixing, promote the effect of burning, efficiency of combustion and the flame stabilization ability of cavity upstream fuel spray orifice burner oil can be strengthened further.
Accompanying drawing explanation
The accompanying drawing forming a part of the present invention is used to provide a further understanding of the present invention, and schematic description and description of the present invention, for explaining the present invention, does not form inappropriate limitation of the present invention.In the accompanying drawings:
Fig. 1 shows the perspective view according to supersonic combustor wall surface concave cavity structure of the present invention;
Fig. 2 shows the sectional structure schematic diagram of supersonic combustor wall surface concave cavity structure at pod apertures place according to the embodiment of Fig. 1;
Fig. 3 shows the sectional structure schematic diagram of supersonic combustor wall surface concave cavity structure at first longitudinal interface channel place according to the embodiment of Fig. 1;
Fig. 4 shows the sectional structure schematic diagram of supersonic combustor wall surface concave cavity structure at second longitudinal interface channel place according to the embodiment of Fig. 1;
Fig. 5 shows supersonic combustor wall surface concave cavity structure of the present invention and is arranged on perspective view on scramjet engine combustion chamber; And
Fig. 6 is the sectional structure schematic diagram of the scramjet engine combustion chamber of installation supersonic combustor wall surface concave cavity structure in Fig. 5.
Detailed description of the invention
Hereinafter also describe the present invention in detail with reference to accompanying drawing in conjunction with the embodiments.It should be noted that, when not conflicting, the embodiment in the application and the feature in embodiment can combine mutually.
In the present embodiment, with the flow direction of air in combustion chamber for reference direction, the inflow direction of air is upstream, and outflow direction is downstream.With pocket base wall place plane for horizontal plane, the plane perpendicular to this horizontal plane is longitudinal surface.
As shown in Figures 1 to 4, according to embodiments of the invention, supersonic combustor wall surface concave cavity structure comprises mount pad 10, combustion chamber wall surface cavity 40 is provided with in mount pad 10, the upstream being positioned at air inlet side of combustion chamber wall surface cavity 40 is provided with pod apertures 22, the downstream correspondence of pod apertures 22 is provided with cavity upstream fuel spray orifice 21, cavity upstream fuel spray orifice 21 is near pod apertures 22, cavity upstream fuel spray orifice 21 downstream is provided with the pod apertures be connected with pod apertures 22 and exports 27, and pod apertures outlet 27 is communicated to cavity upstream fuel spray orifice 21.
The air inlet side of combustion chamber wall surface cavity 40 is provided with cavity leading edge step 20, cavity leading edge step 20 includes cavity upstream fuel spray orifice 21 and the pod apertures 22 of multiple vertical setting, multiple cavity upstream fuel spray orifice 21 is arranged along the first longitudinal surface interval, multiple pod apertures 22 is arranged along the second longitudinal surface interval being parallel to the first longitudinal surface, each cavity upstream fuel spray orifice 21 is all connected to fuel inlet, and pod apertures 22 is not connected in cavity leading edge step 20 with cavity upstream fuel spray orifice 21.
Also be provided with cavity trailing edge step 30 in combustion chamber wall surface cavity 40, cavity leading edge step 20 and cavity trailing edge step 30 are positioned at two opposite sides of mount pad 10.The pocket base wall of combustion chamber wall surface cavity 40 is provided with spark-plug hole 41, cavity leading edge step 20 is positioned at the air inlet side of combustion chamber wall surface cavity 40, cavity leading edge step 20 includes cavity upstream fuel spray orifice 21 and the pod apertures 22 of multiple vertical setting, multiple cavity upstream fuel spray orifice 21 is arranged along the first longitudinal surface interval, multiple pod apertures 22 along be positioned at the first longitudinal surface upstream and be parallel to the first longitudinal surface second longitudinal surface interval arrange, each cavity upstream fuel spray orifice 21 is all connected to fuel inlet, each pod apertures 22 is communicated to combustion chamber wall surface cavity 40 by pod apertures outlet 27, each pod apertures 22 is not connected in cavity leading edge step 20 with cavity upstream fuel spray orifice 21.Preferably, pod apertures 22 and pod apertures export the axis perpendicular of 27.Be extended with flange in the surrounding of mount pad, the flange of surrounding is provided with multiple screwed hole, be convenient to mount pad to be connected on distance piece 50.
Utilize the windward side high pressure that fuel jet orifice burner oil is formed, air before cavity upstream fuel spray orifice is flowed through pod apertures outlet extruding by pod apertures enter bottom cavity leading edge, have air to enter cavity by pod apertures and pod apertures outlet before making igniting and form continuous fresh mixed gas thus strengthen igniting.After the successful ignition of combustion chamber, after fuel jet orifice jet combustion district sets up and is stable, cavity is inner due to burning heat release effect formation higher-pressure region, shock train is formed before the higher-pressure region of simultaneously burning, the static pressure at pod apertures place is much smaller than cavity Inner stagnant pressure, combustion gas in cavity is exported through pod apertures reflux by pod apertures and sprays from pod apertures, play the fuel preheating that cavity upstream fuel spray orifice is sprayed, and improve jet penetration, strengthen mixing, promote the effect of burning, efficiency of combustion and the flame stabilization ability of cavity upstream fuel spray orifice burner oil can be strengthened further.
Combustion chamber wall surface cavity 40 also comprises the vertical spaced multiple pocket base wall fuel jet orifice 42 of the 3rd longitudinal surface along being positioned at combustion chamber wall surface cavity 40,3rd longitudinal surface is parallel to the first longitudinal surface, the bottom of multiple pocket base wall fuel jet orifice 42 is all connected to fuel inlet, and spark-plug hole 41 is arranged in the downstream of pocket base wall fuel jet orifice 42.Pod apertures outlet 27 is arranged in the horizontal direction, and pod apertures outlet 27 and pocket base wall fuel jet orifice 42 one_to_one corresponding orthorhombic phase pair.Preferably, the axis of corresponding cavity upstream fuel spray orifice 21, pod apertures 22, pod apertures outlet 27 and pocket base wall fuel jet orifice 42 is positioned on the same fore-and-aft plane perpendicular to the first fore-and-aft plane, and this fore-and-aft plane extends along the flow direction of air.Cavity upstream fuel spray orifice 21 and pod apertures 22 are positioned at the set-up mode on fore-and-aft plane that this flow direction along air extends, the air before cavity upstream fuel spray orifice 21 is before ignition made to be pressed in cavity by windward side high pressure from pod apertures 22 better, thus obtain better air press-in effect, form the fresh mixed gas of continuous print, strengthen ignition performance.The outlet orthorhombic phase pair of pod apertures outlet 27 and pocket base wall fuel jet orifice 42, and the set-up mode be positioned on fore-and-aft plane that this flow direction along air extends, make from the fresh air of pod apertures outlet 27 outflow and better collisional mixing effect can be had from the fuel that pocket base wall fuel jet orifice 42 flows out, strengthen air and fuel mix efficiency, strengthen ignition performance.
In cavity leading edge step 20, the first lateral connection passage 23 be connected by each cavity upstream fuel spray orifice 21 and the first longitudinal interface channel 24 be connected with fuel inlet by the first lateral connection passage 23 can also be set.Preferably, the first lateral connection passage 23 is arranged near the roof of cavity leading edge step 20.Combustion chamber wall surface cavity 40 can be arranged the second lateral connection passage 43 be connected by multiple pocket base wall fuel jet orifice 42 and the second longitudinal interface channel 44 be connected with fuel inlet by the second lateral connection passage 43.Preferably, pod apertures outlet 27 is arranged near pocket base wall, and pocket base wall fuel jet orifice 42 is arranged near the inner side longitudinal shelf terrace 25 of cavity leading edge step 20.Cavity leading edge step 20 also includes the 3rd lateral connection passage 26 multiple pod apertures 22 be connected.
Respectively the cavity upstream fuel spray orifice 21 of multiple vertical setting, pod apertures 22 and pocket base wall fuel jet orifice 42 are linked together by multiple lateral connection passage, can make in the process flowed at air and fuel, air in each cavity upstream fuel spray orifice 21, pod apertures 22 and pocket base wall fuel jet orifice 42 and fuel mix even, and the flowing of each cavity upstream fuel spray orifice 21, pod apertures 22 and pocket base wall fuel jet orifice 42 is more even, obtains more stable mixed gas supply and ignition effect.
As shown in Figure 5 and Figure 6, according to embodiments of the invention, the supersonic combustor wall surface concave cavity structure that engine chamber comprises distance piece 50 and is arranged on distance piece 50, this supersonic combustor wall surface concave cavity structure is above-mentioned supersonic combustor wall surface concave cavity structure.
According to supersonic combustor wall surface concave cavity structure of the present invention, before enforcement igniting, cavity upstream fuel spray orifice 21 and pocket base wall fuel jet orifice 42 all open spray, utilize the windward side high pressure that cavity upstream fuel spray orifice 21 burner oil is formed, after air before cavity upstream fuel spray orifice 21 is flowed through pod apertures outlet 27 by pod apertures 22, extruding enters bottom cavity leading edge, the fuel sprayed with pocket base wall fuel jet orifice 42 collides, mix and form certain proportioning, play continuous fresh mixed gas nucleus formation, have air to enter combustion chamber wall surface cavity 40 by pod apertures 22 and pod apertures outlet 27 before making igniting form continuous fresh mixed gas thus strengthen igniting.
After the successful ignition of combustion chamber, after cavity upstream fuel spray orifice 21 jet combustion district sets up and be stable, close the spray of pocket base wall fuel jet orifice 42.Cavity is inner due to burning heat release effect formation higher-pressure region, shock train is formed before the higher-pressure region of simultaneously burning, the static pressure at pod apertures 22 place is much smaller than cavity Inner stagnant pressure, combustion gas in cavity is flowed through pod apertures reflux by pod apertures outlet 27 and is sprayed from pod apertures 22, play the fuel preheating that the cavity upstream fuel spray orifice 21 being positioned at pod apertures 3 downstream is sprayed and the effect improving jet penetration, strengthen mixing, promote burning, can the efficiency of combustion of cavity upstream fuel spray orifice 21 burner oil and flame stabilization ability further.
Provide below and adopt supersonic combustor wall surface concave cavity structure of the present invention to light a fire the quantitative estimation of strengthening the property.
According to the result of document " numerically modeling of Mass Exchange Characteristics of Cavity Flameholders For Scramjet Applications " and " the mixing RANS/LES of supersonic combustion cavity mass exchange characteristic simulates ", the residence time of cavity in cold flow and reaction stream all at about 2ms, the mass exchange rate of cavity, the flow rate that enters of air is divided by by the gas capacity of cavity and residence time and is obtained in other words.For an example of the present invention, the cavity getting combustion chamber is of a size of: dark (D) 20mm of long (L) 140mm* wide (W) 230mm*, the volume of combustion chamber cavity is: L*W*D=0.000644m
3.Now get the result of calculation of numerical simulation, under Ma4 condition, (entry of combustion chamber gets Ma=1.92, static temperature T=500K, stagnation temperature T
0=868K), the atmospheric density calculated in cavity is 0.5kg/m
3(Density Distribution in cavity is uneven, and this is the result be averaged).
Air quality so under this condition in cavity is 0.000644m
3* 0.5kg/m
3=0.000322kg, so air enters the flow rate of cavity and is:
according to result by references, the air entering cavity mainly concentrates on the downstream of cavity shear layer, because the flow velocity of cavity leading edge recirculating zone is very low, even if the air entering cavity has also been difficult to the exchange with cavity leading edge stream district.According to the velocity flow profile 5m/s magnitude in leading edge stream district, trailing edge recirculating zone flow velocity is in 150m/s magnitude, and the air rate of cavity leading edge is less than 0.161kg/s*0.1=0.0161kg/s.
Adopt the compression of Φ 2mm single hole the air compressing of such as down-off can be entered pocket base wall.Get the flow coefficient C of pod apertures
d=0.9 (can be improved further by the design of pod apertures), the pressure P of the approximate pressure spray of the front recirculating zone of spray jet
0get 1.0Mpa, the recirculating zone T0=868K before spray jet, single hole area A
0=π (D/2)
2=3.1416e ?006, so
Wherein
for air mass flow, κ is constant entropy characteristic coefficient, for air κ=0.04042.
Then adopt 10 hole compressions, the air mass flow of 0.0776kg/s can be obtained, adopt 20 hole compressions, the air mass flow of 0.1551kg/s can be obtained, if by design employing 30 hole compressions, then can 0.2326kg/s be obtained, therefore can obtain the effect introducing air completely.
As can be seen from document " numerically modeling of Mass Exchange Characteristics of Cavity Flameholders For Scramjet Applications ", recirculating zone that is more stable, low speed is formed (because this feature of leading edge recirculating zone in the place near cavity leading edge, igniting is implemented in usual selection herein), the size of recirculating zone is little, for the entirety of cavity inside transports, transporting of cavity leading edge wants much slow relatively, cavity leading edge is utilized to light a fire, be faced with easily fuel-rich situation, fill into portion of air by pod apertures, more significant improvement result must be had for igniting.
As can be seen from the above description, the above embodiments of the present invention achieve following technique effect: the high pressure utilizing fuel to spray self promotes igniting, need not carry oxidant high-pressure air source device; Utilize the high pressure of combustion zone self to promote fuel spray combustion process, need not the parts such as support plate be set; Employing pod apertures is communicated with pocket base wall, and formed and promote igniting and the successfully rear scheme strengthening fuel jet and burn of lighting a fire before ignition, this scheme has simple, the adaptive feature of structure, is easy to promote.
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 (12)
1. a supersonic combustor wall surface concave cavity structure, it is characterized in that, comprise mount pad (10), combustion chamber wall surface cavity (40) is provided with in described mount pad (10), the upstream being positioned at air inlet side of described combustion chamber wall surface cavity (40) is provided with pod apertures (22), the downstream correspondence of described pod apertures (22) is provided with cavity upstream fuel spray orifice (21), described cavity upstream fuel spray orifice (21) is near described pod apertures (22), described cavity upstream fuel spray orifice (21) downstream is provided with the pod apertures be connected with described pod apertures (22) and exports (27), described pod apertures outlet (27) is communicated to described cavity upstream fuel spray orifice (21).
2. supersonic combustor wall surface concave cavity structure according to claim 1, it is characterized in that, the air inlet side of described combustion chamber wall surface cavity (40) is provided with cavity leading edge step (20), described cavity leading edge step (20) includes described cavity upstream fuel spray orifice (21) and the described pod apertures (22) of multiple vertical setting, multiple described cavity upstream fuel spray orifice (21) is arranged along the first longitudinal surface interval, multiple described pod apertures (22) is arranged along the second longitudinal surface interval being parallel to described first longitudinal surface, each described cavity upstream fuel spray orifice (21) is all connected to fuel inlet, described pod apertures (22) is not connected in described cavity leading edge step (20) with described cavity upstream fuel spray orifice (21), wherein, with pocket base wall place plane for horizontal plane, the vertical described horizontal plane of described first longitudinal surface.
3. supersonic combustor wall surface concave cavity structure according to claim 2, it is characterized in that, described combustion chamber wall surface cavity (40) also comprises the vertical spaced multiple pocket base wall fuel jet orifice (42) of the 3rd longitudinal surface along being positioned at described combustion chamber wall surface cavity (40), described 3rd longitudinal surface is parallel to described first longitudinal surface, and the bottom of multiple described pocket base wall fuel jet orifice (42) is all connected to described fuel inlet.
4. supersonic combustor wall surface concave cavity structure according to claim 3, it is characterized in that, described pod apertures outlet (27) is arranged in the horizontal direction, and described pod apertures outlet (27) and described pocket base wall fuel jet orifice (42) one_to_one corresponding orthorhombic phase pair.
5. supersonic combustor wall surface concave cavity structure according to claim 4, it is characterized in that, corresponding described cavity upstream fuel spray orifice (21), described pod apertures (22), described pod apertures outlet (27) and the axis of described pocket base wall fuel jet orifice (42) are positioned on the same fore-and-aft plane perpendicular to described first fore-and-aft plane.
6. supersonic combustor wall surface concave cavity structure according to any one of claim 1 to 5, is characterized in that, described pod apertures (22) and described pod apertures export the axis perpendicular of (27).
7. the supersonic combustor wall surface concave cavity structure according to any one of claim 2 to 5, it is characterized in that, in described cavity leading edge step (20), be also provided with the first lateral connection passage (23) each described cavity upstream fuel spray orifice (21) be connected and the first longitudinal interface channel (24) be connected with described fuel inlet by described first lateral connection passage (23).
8. supersonic combustor wall surface concave cavity structure according to claim 7, is characterized in that, described first lateral connection passage (23) is arranged near the roof of described cavity leading edge step (20).
9. the supersonic combustor wall surface concave cavity structure according to any one of claim 3 to 5, it is characterized in that, described combustion chamber wall surface cavity (40) also comprises the second lateral connection passage (43) multiple described pocket base wall fuel jet orifice (42) be connected and the second longitudinal interface channel (44) be connected with described fuel inlet by described second lateral connection passage (43).
10. supersonic combustor wall surface concave cavity structure according to claim 9, it is characterized in that, described pod apertures outlet (27) is arranged near described pocket base wall, and described pocket base wall fuel jet orifice (42) is arranged near inner side longitudinal shelf terrace (25) of described cavity leading edge step (20).
11. supersonic combustor wall surface concave cavity structure according to any one of claim 2 to 5, it is characterized in that, described cavity leading edge step (20) also includes the 3rd lateral connection passage (26) multiple described pod apertures (22) be connected.
12. 1 kinds of engine chambers, the supersonic combustor wall surface concave cavity structure comprising distance piece (50) and be arranged on described distance piece (50), it is characterized in that, the supersonic combustor wall surface concave cavity structure of described supersonic combustor wall surface concave cavity structure according to any one of claim 1 to 11.
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| JP2012141107A (en) * | 2011-01-05 | 2012-07-26 | Hitachi Ltd | Gas turbine combustor |
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| WO2016127813A1 (en) * | 2015-02-13 | 2016-08-18 | 中国人民解放军国防科学技术大学 | Large-scale scramjet engine and three-dimensional petal-shaped section combustor thereof |
| CN109253470A (en) * | 2018-09-11 | 2019-01-22 | 中国人民解放军国防科技大学 | Supersonic mixing reinforcing device |
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