CN104964310A - Ramjet combustion chamber - Google Patents
Ramjet combustion chamber Download PDFInfo
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- CN104964310A CN104964310A CN201510323981.8A CN201510323981A CN104964310A CN 104964310 A CN104964310 A CN 104964310A CN 201510323981 A CN201510323981 A CN 201510323981A CN 104964310 A CN104964310 A CN 104964310A
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Abstract
The invention belongs to the technical field of ramjets, and discloses a ramjet combustion chamber. The combustion chamber comprises an isolation segment, a sudden expansion segment, a cavity, a constant section segment and a tail spraying pipe which are arranged in sequence and are communicated in sequence. The distances from bottom plates of the isolation segment, the sudden expansion segment and the cavity to the top are sequentially increased; and a supporting plate cavity is formed in a supporting plate structure, and a fuel flow-in opening, a high-temperature airflow leading inlet and a plurality of jet holes communicated with the supporting plate cavity are formed in the supporting plate structure. A combination of the sudden expansion segment, the cavity and the supporting plate structure is adopted, and the mixing effect of fuel and incoming flow air is good; the supporting plate structure is arranged in an inclining manner, and the distribution range of fuel mixed gas sprayed out of the supporting plate structure in a runner is wide; the fuel and the high-temperature led airflow are contact in a supporting plate cavity in advance, the fuel obtains energy, and participates in combustion conveniently and rapidly, and the ignition speed is high; and a continuous stable flame is formed in the cavity, and diffusion and flame stabilizing are facilitated.
Description
Technical field
The present invention relates to sub-burning ramjet technical field, particularly the sub-burning ramjet combustion chamber of one.
Background technology
Punching engine is a kind of air breathing jet engine relying on the deceleration pressurization of head-on air stream at a high speed to carry out work, its simple structure, do not have the complicated rotatable parts as the compressor of turbojet and turbine, the air compressing entering engine obtains by the stagnation (punching press supercharging) of high velocity air.Punching engine mainly can be divided into two types: sub-burning ramjet (subsonic combustion punching engine) and scramjet engine (supersonic combustion ramjet engine).
Combustion chamber is the core component of sub-burning ramjet, because sub-burning ramjet works under high altitude conditions, environment temperature is low, atmospheric density is very low in combustion chamber, entry of combustion chamber air velocity is higher, and these factors cause combustion chamber ignition difficulty, smooth combustion also more difficult.
Summary of the invention
(1) technical problem that will solve
The technical problem to be solved in the present invention is: in order to solve the problem of the igniting of sub-burning ramjet and smooth combustion difficulty.
(2) technical scheme
In order to solve the problems of the technologies described above, the invention provides a kind of sub-burning ramjet combustion chamber, the cross section of described combustion chamber is rectangle, be made up of multistage and its distance from top base plate not etc. bottom it, the length direction order that formed along described combustion chamber arranges and is communicated with successively: distance piece, sudden expansion section, cavity, etc. straight section and jet pipe; A plate structure is provided with in described sudden expansion section and cavity, distance between the base plate of the base plate of described distance piece, sudden expansion section, cavity increases successively apart from the distance at described top, described straight section of Denging and described top is less than the distance between the base plate of described cavity and described top; Be provided with a plate structure in described sudden expansion section and cavity, the bottom of described plate structure is connected with the base plate of described sudden expansion section, and described cavity top is stretched on the top of described plate structure; Be provided with support plate chamber in described plate structure, described plate structure is provided with and is communicated with described support plate chamber: flow in fuel entrance, high temperature bleed inflow entrance and multiple spray-hole.
Wherein, the axis of multiple described spray-hole is all perpendicular to the length direction of described combustion chamber.
Wherein, the bottom of described plate structure is fixedly connected on the base plate of described sudden expansion segment trailer, and the top of described plate structure tilts to described jet pipe direction, and extends to described cavity top.
Wherein, described flow in fuel entrance and described high temperature bleed inflow entrance are all arranged on the base plate of described sudden expansion section.
Wherein, described plate structure by two pieces windward plate and one block of leeward plate surround, described plate is windward all relative with described distance piece, and described leeward plate is relative with described jet pipe; Multiple described spray-hole is arranged at the junction of plate and described leeward plate windward described in two pieces respectively.
Wherein, described in two pieces, plate and leeward plate junction are equipped with the groove along described support plate structure length directional spreding windward, and the bottom land of described groove is communicated with described spray-hole.
Wherein, the angle of the length direction of described plate structure and the length direction of described combustion chamber is 45 degree.
Wherein, gap is left between the top of described plate structure and the top of described combustion chamber.
Wherein, described cavity length, be less than 10 with the ratio of the difference in height of the base plate of described cavity and the base plate of described sudden expansion section; The junction of the base plate of the base plate of described cavity and the straight section such as described is provided with rebound, and the inclination angle of described rebound is 45 degree.
Wherein, described high temperature bleed inflow entrance is used for the high temperature gas flow in turbogenerator to introduce described support plate chamber.
(3) beneficial effect
Technique scheme tool has the following advantages: a kind of sub-burning ramjet combustion chamber of the present invention, and by adopting the combination of sudden expansion section, cavity and a plate structure, make fuel and incoming air good mixing effect, fuel residence time increases; Fuel contacts in support plate chamber in advance with high temperature bleed stream, and make fuel obtain energy, fast and easy participates in burning, and speed of ignition is fast; Form low speed recirculating zone in cavity, contribute to successful ignition, form continual and steady flame, contribute to flame propagation and smooth combustion; High temperature bleed stream is provided by turbogenerator, without the need to being specially equipped with other equipment, effectively utilizes the energy that turbogenerator is discharged, economize energy; Arranging of groove can produce disturbance to incoming air, forms small recirculating zone, makes to mix from spray-hole gaseous mixture out with incoming air, contributes to lengthening the residence time of fuel in combustion chamber.
Accompanying drawing explanation
Fig. 1 is the side view of sub-burning ramjet combustion chamber of the present invention;
Fig. 2 is the upward view of Fig. 1;
Fig. 3 is the close-up schematic view of support plate structure division in Fig. 1;
Fig. 4 is that the A-A of Fig. 3 is to sectional view.
Wherein, 1, distance piece; 2, sudden expansion section; 3, plate structure is propped up; 31, plate windward; 32, leeward plate; 33, flow in fuel entrance; 34, high temperature bleed inflow entrance; 35, spray-hole; 36, groove; 37, support plate chamber; 4, cavity; 5, the straight section such as; 6, jet pipe.
Detailed description of the invention
Below in conjunction with drawings and Examples, the specific embodiment of the present invention is described in further detail.Following examples for illustration of the present invention, but are not used for limiting the scope of the invention.
In describing the invention, it should be noted that, except as otherwise noted, the implication of " multiple " is two or more; Term " on ", D score, "left", "right", " interior ", " outward ", " front end ", " rear end ", " head ", the orientation of the instruction such as " afterbody " or position relationship be based on orientation shown in the drawings or position relationship, only the present invention for convenience of description and simplified characterization, instead of indicate or imply that the device of indication or element must have specific orientation, with specific azimuth configuration and operation, therefore can not be interpreted as limitation of the present invention.In addition, term " first ", " second ", " the 3rd " etc. only for describing object, and can not be interpreted as instruction or hint relative importance.
In describing the invention, also it should be noted that, unless otherwise clearly defined and limited, term " installation ", " being connected ", " connection " should be interpreted broadly, and such as, can be fixedly connected with, also can be removably connect, or connect integratedly; Can be mechanical connection, also can be electrical connection; Can be directly be connected, also indirectly can be connected by intermediary.For the ordinary skill in the art, visual concrete condition understands above-mentioned term concrete meaning in the present invention.
As Figure 1-4, the present invention discloses a kind of sub-burning ramjet combustion chamber, the cross section of described combustion chamber is rectangle, be made up of multistage and its distance from top base plate not etc. bottom it, the length direction order that formed along described combustion chamber arranges and is communicated with successively: distance piece 1, sudden expansion section 2, cavity 4, etc. straight section 5 and jet pipe 6; Described sudden expansion section 2 is provided with a plate structure 3 with cavity 4, distance between the base plate of the base plate of described distance piece 1, sudden expansion section 2, cavity 4 increases successively apart from the distance at described top, described straight section 5 of Denging and described top is less than the distance between the base plate of described cavity 4 and described top; Be provided with a plate structure 3 in described sudden expansion section 2 and cavity 4, the bottom of described plate structure 3 is connected with the base plate of described sudden expansion section 2, and the top of described plate structure 3 is stretched in described cavity 4; Be provided with support plate chamber 37 in described plate structure 3, described plate structure 3 is provided with and is communicated with described support plate chamber 37: flow in fuel entrance 33, high temperature bleed inflow entrance 34 and multiple spray-hole 35.
Setting about cavity 4:
Because punching engine works under high altitude conditions, temperature aloft is low, atmospheric density is very low in combustion chamber, entry of combustion chamber air velocity is very high, and these conditions add the difficulty of combustion chamber ignition and flame stabilization.
Liquid fuel passes through atomization, evaporation, mixing and burning process in punching engine domestic demand; In addition, because the mainstream speed in combustion chamber is very high, make fuel very short at combustion chamber residence time, can only the timing of millisecond unit be used; The firing delay of hydrocarbon fuel is longer simultaneously, adds the difficulty of igniting and flame stabilization.
Therefore, igniting reduces ignition lag distance exactly with the key of flame stabilization technology, sets up the radical source required for chemical reaction in distance short as far as possible, for burning provides a reliable incendiary source, thus realizes smooth combustion in high velocity air.
Flame stabilization technology generally forms recirculating zone to realize by certain mode.In recirculating zone, some local velocity is lower than the spread speed of turbulent flame, has so just possessed the necessary condition of flame stabilization, once the incendiary source having power enough, just flammable mixed gas can be lighted.High-temperature combustion product returns to upstream by recirculating zone, and form the incendiary source of steady and continuous, recirculating zone plays a part heat accumulation, with the form of turbulent mass transfer and heat exchange, is flammable mixed gas transmission heat and active material, makes flame be able to bamboo telegraph in combustion chamber.
Cavity 4 can stabilize the flame, its main mechanism is that cavity 4 provides a low speed recirculating zone, and cavity 4 internal high temperature gas utensil has the effect of incendiary source, and the high-temperature product of burning returns to upstream by recirculating zone, light the gaseous mixture of incoming air and fuel, form a continual and steady flame.
The effect of cavity 4 is equivalent to flameholder, and flameholder is positioned at the edge of runner, can reduce the blocking action of flameholder to main flow largely, thus greatly reduce the pressure loss of air-flow.Simultaneously because cavity 4 is made up of backward and forward direction two steps, recirculating zone is locked in cavity 4, therefore recirculating zone structure is comparatively stable, be conducive to the residence time increasing fuel, make the fuel distribution in recirculating zone be tending towards even, greatly improve igniting and the flame stabilization performance of scramjet combustor.
In the present invention, rebound, namely the size of the trailing edge angle of cavity 4 is chosen is to keep air current flow and flameholding, specifically how to keep, and is to see that concrete Flow Field Distribution and turbulent combustion are reacted, and preferably adopts the rebound of 45 degree of inclination angle structures.
For overcoming the shortcoming existing for wall propellant spray, propose directly at the center spray fuel of high speed incoming air, this can be realized by the plate structure 3 inserting incoming flow center, props up the sweptback large-scale structure of plate structure 3 simultaneously and also contributes to strengthening mixing.Particularly for large runner combustion chamber, the fuel injection scheme of of the present invention plate structure 3 is adopted to seem particularly necessary.
Prop up operation principle and the effect of plate structure 3:
High speed incoming air flows through two blocks of plate structure 3 plates 31 windward, the pressure reduction formed makes incoming air produce at the afterbody of plate 31 windward and flows to vortex, flow to vortex and can entrainment fuel and air in propagates down stream process, increase the fuel of spray-hole 35 ejection and the contact area of incoming air, increase the concentration gradient of local, thus enhance mixing of fuel and incoming air.Plate structure 3 entirety tilts backwards, and adds the effect of two blocks of plates 31 windward, makes the both sides of a plate structure 3 form the region expanded outwardly, flow expansion, larger with the pressure reduction in front, flows to whirlpool stronger, mixing enhancing better effects if.
Because a plate structure 3 for this mode is arranged in the middle of main flow, in the middle of the main flow that directly fuel can be sprayed into high speed incoming air, good fuel space distribution and mixed effect can be provided, especially when combustion chamber runner is larger, the penetration that wall is injected in fuel is difficult to meet the demands, and the advantage of at this moment propping up the propellant spray effect of plate structure 3 is more outstanding; And can be good at producing eddy current through a plate structure 3 for particular design, strengthen mixing further, and certain effect stabilized the flame can be played in the recirculating zone that the bottom of a plate structure 3 is formed.
It is 45 degree that the sweepback angle (angle of inclination) of plate structure 3 is preferably with the angle of the length direction of combustion chamber, concrete tilt angle, be also fixed as the case may be, object, the while of reducing loss, strengthens mixing.
In combustion, prop up the effect that plate structure 3 has " connection flame device ", form the low regime of local after propping up the leeward plate 32 of plate structure 3, contribute to flame and be transmitted to plate structure 3 top along propping up plate structure 3 length direction bottom a plate structure 3, make flame spread to whole combustion chamber runner.
The setting of groove 36:
Groove 36 can produce disturbance to incoming air, forms small recirculating zone, makes to mix from spray-hole 35 gaseous mixture out with incoming air, contributes to lengthening the residence time of fuel in combustion chamber and the penetration depth of fuel in primary air.
The setting of sudden expansion section 2:
Sudden expansion section 2 mainly relies on the recirculating zone of sudden expansion section to stabilize the flame, and does not take combustion chamber mainstream channel, in the flame stabilization mode that this uses a plate structure 3, cavity 4, sudden expansion section 2 to combine, can solve the problem that its flame scope is narrower.
During work, swiftly flowing incoming air enters combustion chamber through distance piece 1, and after entering sudden expansion section 2, circulation area increases, and flow velocity declines, and air pressure raises, and the gas in combustion chamber can be stoped to reflux to distance piece 1 direction; Fuel enters support plate chamber 37 through flow in fuel entrance 33; One high temperature bleed stream sent here by turbogenerator enters in support plate chamber 37 by high temperature bleed inflow entrance 34, flow in fuel in support plate chamber 37 mixes with high temperature bleed stream, fuel rapid temperature increases, obtain the energy needed for fuel vaporization, eliminate the process that fuel is atomized in a combustion chamber and evaporates, obtain the burning extent shorter than normal temperature fuel, ignition ability improves; After fuel mixes in support plate chamber 37 with high temperature bleed, sprayed by spray-hole 35, enter in the recirculating zone of cavity 4 formation, because flow velocity is lower in this recirculating zone, igniting is success easily, so general selection igniter is lighted a fire in recirculating zone, to form continual and steady flame, flame such as to be transmitted to again further at the straight section 5.
Concrete, the axis of multiple described spray-hole 35 is all perpendicular to the length direction of described combustion chamber.The direction of fuel ejection is mutually vertical with the flow direction of incoming air, is more conducive to mixing of fuel and incoming air, is conducive to lighting a fire.
The bottom of described plate structure 3 is fixedly connected on the base plate of described sudden expansion section 2 afterbody, and the top of described plate structure 3 tilts to described jet pipe 6 direction, and extends to cavity 4 top.Described flow in fuel entrance 33 and described high temperature bleed inflow entrance 34 are all arranged on the base plate of described sudden expansion section 2.Described plate structure 3 by two pieces windward plate 31 and one block of leeward plate 32 surround, described plate windward 31 is all relative with described distance piece 1, and described leeward plate 32 is relative with described jet pipe 6; Multiple described spray-hole 35 is arranged at the junction of plate 31 and described leeward plate 32 windward described in two pieces respectively.Described in two pieces, the junction of plate 31 is fillet structure windward.Incoming air through two of plate structure 3 windward plate 31 be separated into two strands of air-flows, then mix with the gaseous mixture of fuel with high temperature bleed at the afterbody of plate 31 windward, two strands of staggered air-flows can fully be contacted.
Further, described in two pieces, plate 31 and leeward plate 32 junction are equipped with the groove 36 distributed along described plate structure 3 length direction windward, and the bottom land of described groove 36 is communicated with described spray-hole 35.The gaseous mixture of fuel and high-temperature gas, after spray-hole 35 sprays, under the little recirculating zone effect first formed in groove 36, with incoming air blending, then spreads to downstream.Compared with spray-hole 35, the contact area of groove 36 is larger, is conducive to mixing of gaseous mixture and incoming flow, is more conducive to lighting a fire.
Preferably, the angle of the length direction of described plate structure 3 and the length direction of described combustion chamber is 45 degree.Gap is left between the top of described plate structure 3 and the top of described combustion chamber.Propping up plate structure 3 top unsettled, and leave gap with top of combustion chamber, even if a plate structure 3 produces distortion when burning, also can carry out deformation buffering by free end, protect a plate structure 3.Fuel is diffused in runner by spray-hole 35 after mixing in support plate chamber 37 with high temperature bleed stream; Because cavity 4 sectional area increases suddenly, a low regime can be formed, in cavity 4, look for one to hold the igniting of ignitable region, flame is by cavity 4 diffusive transport forwards, backwards, the region of propping up plate structure 3 rear portion affects less by Incoming gas, be conducive to flame propagation, make flame along the leeward plate 32 upwards back-propagation extremely straight section 5 such as grade of a plate structure 3, be namely transmitted to whole flow passage area; Prop up plate structure 3 in the technical program, to play the mixing of enhancing air-flow, expand the distributed areas of fuel in runner and the object of " connection flame ".
The length of described cavity 4, be less than 10 with the ratio of the difference in height of the base plate of described cavity 4 and the base plate of described sudden expansion section 2, namely the degree of depth of cavity 4 sudden expansion section 2 is relatively D, and the anterior-posterior length of cavity 4 is L, L/D<10.The junction of the base plate of the base plate of described cavity 4 and the straight section 5 such as described is provided with rebound, and the inclination angle of described rebound is 45 degree, and namely the trailing edge angle of cavity 4 is 45 degree.
Described high temperature bleed inflow entrance 34 is for introducing described support plate chamber 37 by the high temperature gas flow in turbogenerator.Sub-burning ramjet generally will be combined with turbogenerator, and namely when turbogenerator works, fuel, in support plate chamber 37, to preheat fuel, and sprays by support plate chamber 37 by the thermal current introducing one about 600K from turbogenerator.
As can be seen from the above embodiments, in the present invention, high temperature bleed stream is provided by turbogenerator, without the need to being specially equipped with other equipment, effectively utilizes the energy that turbogenerator is discharged, economize energy; Fuel contacts in support plate chamber 37 in advance with high temperature bleed stream, and make fuel obtain energy, fast and easy participates in burning, and speed of ignition is fast; Arranging of groove 36 can produce disturbance to incoming air, forms small recirculating zone, makes to mix from spray-hole 35 gaseous mixture out with incoming air, contributes to mixing and lengthens the residence time of fuel in combustion chamber; The combination of sudden expansion section 2, cavity 4 and a plate structure 3, forms eddy current at spray-hole 35 place, fuel and incoming air good mixing effect; Cavity 4 contributes to successful ignition, forms the stable incendiary source, propagating flame and the smooth combustion that continue.
The above is only the preferred embodiment of the present invention; it should be pointed out that for those skilled in the art, under the prerequisite not departing from the technology of the present invention principle; can also make some improvement and replacement, these improve and replace and also should be considered as protection scope of the present invention.
Claims (10)
1. a sub-burning ramjet combustion chamber, it is characterized in that, the cross section of described combustion chamber is rectangle, be made up of multistage and its distance from top base plate not etc. bottom it, the length direction order that formed along described combustion chamber arranges and is communicated with successively: distance piece (1), sudden expansion section (2), cavity (4), etc. straight section (5) and jet pipe (6); A plate structure (3) is provided with in described sudden expansion section (2) and cavity (4), distance between the base plate of the base plate of described distance piece (1), sudden expansion section (2), cavity (4) increases successively apart from the distance at described top, described straight section of Denging (5) and described top is less than the distance between the base plate of described cavity (4) and described top;
A plate structure (3) is provided with in described sudden expansion section (2) and cavity (4), the bottom of described plate structure (3) is connected with the base plate of described sudden expansion section (5), and described cavity (4) top is stretched on the top of described plate structure (3); Be provided with support plate chamber (37) in described plate structure (3), described plate structure (3) is provided with and is communicated with described support plate chamber (37): flow in fuel entrance (33), high temperature bleed inflow entrance (34) and multiple spray-hole (35).
2. sub-burning ramjet combustion chamber as claimed in claim 1, is characterized in that, the axis of multiple described spray-hole (35) is all perpendicular to the length direction of described combustion chamber.
3. sub-burning ramjet combustion chamber as claimed in claim 2, it is characterized in that, the bottom of described plate structure (3) is fixedly connected on the base plate of described sudden expansion section (2) afterbody, the top of described plate structure (3) tilts to described jet pipe (6) direction, and extends to described cavity (4) top.
4. sub-burning ramjet combustion chamber as claimed in claim 3, is characterized in that, described flow in fuel entrance (33) and described high temperature bleed inflow entrance (34) are all arranged on the base plate of described sudden expansion section (2).
5. sub-burning ramjet combustion chamber as claimed in claim 3, it is characterized in that, by two pieces, plate (31) and one piece of leeward plate (32) surround described plate structure (3) windward, described plate windward (31) is all relative with described distance piece (1), and described leeward plate (32) is relative with described jet pipe (6); Multiple described spray-hole (35) is arranged at the junction of plate (31) and described leeward plate (32) windward described in two pieces respectively.
6. sub-burning ramjet combustion chamber as claimed in claim 5, it is characterized in that, described in two pieces, plate (31) and leeward plate (32) junction are equipped with the groove (36) distributed along described plate structure (3) length direction windward, and the bottom land of described groove (36) is communicated with described spray-hole (35).
7. sub-burning ramjet combustion chamber as claimed in claim 1, is characterized in that, the angle of the length direction of described plate structure (3) and the length direction of described combustion chamber is 45 degree.
8. sub-burning ramjet combustion chamber as claimed in claim 1, is characterized in that, leaves gap between the top of described plate structure (3) and the top of described combustion chamber.
9. sub-burning ramjet combustion chamber as claimed in claim 1, is characterized in that, the length of described cavity (4), is less than 10 with the ratio of the difference in height of the base plate of described cavity (4) and the base plate of described sudden expansion section (2); The junction of the base plate of the base plate of described cavity (4) and the straight section (5) such as described is provided with rebound, and the inclination angle of described rebound is 45 degree.
10. sub-burning ramjet combustion chamber as claimed in claim 1, is characterized in that, described high temperature bleed inflow entrance (34) is for introducing described support plate chamber (37) by the high temperature gas flow in turbogenerator.
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| CN201510323981.8A CN104964310B (en) | 2015-06-12 | 2015-06-12 | A kind of sub- burning ramjet combustion chamber |
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| CN105972639A (en) * | 2016-05-18 | 2016-09-28 | 重庆大学 | Double-concave-cavity flame stabilized-combustion device based on air staging and reverse jetting technology |
| CN109322762A (en) * | 2017-07-31 | 2019-02-12 | 波音公司 | Scramjet and associated aircraft and method |
| CN109539312A (en) * | 2018-10-12 | 2019-03-29 | 南京航空航天大学 | A kind of space cavity Asia combustion guidance combustion chamber and engine chamber |
| CN110686275A (en) * | 2019-09-23 | 2020-01-14 | 中国科学院工程热物理研究所 | Combustion chamber flame stabilizing structure for reinforcing mixing and flame propagation |
| CN112432204A (en) * | 2020-12-04 | 2021-03-02 | 中国人民解放军国防科技大学 | Reentrant structure and scramjet that can internal flow drag reduction |
| CN112577070A (en) * | 2020-12-04 | 2021-03-30 | 中国人民解放军国防科技大学 | Low-resistance and high-efficiency scramjet engine thrust chamber integrated design method |
| CN114484503A (en) * | 2022-01-05 | 2022-05-13 | 中国科学院力学研究所 | Self-adaptive geometric throat combustion chamber of wide-range ramjet engine |
| CN115234944A (en) * | 2022-07-14 | 2022-10-25 | 中国人民解放军国防科技大学 | Swirl combined ramjet combustion chamber with stable flame |
| CN115628464A (en) * | 2022-10-12 | 2023-01-20 | 哈尔滨工业大学 | Three-channel scramjet engine combustion chamber |
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| CN105972639B (en) * | 2016-05-18 | 2018-04-06 | 重庆大学 | Concave-concave chamber flame stabilization burner based on air classification backward jet technology |
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| CN109322762B (en) * | 2017-07-31 | 2023-03-17 | 波音公司 | Supersonic ramjet and related aircraft and method |
| CN109322762A (en) * | 2017-07-31 | 2019-02-12 | 波音公司 | Scramjet and associated aircraft and method |
| CN109539312A (en) * | 2018-10-12 | 2019-03-29 | 南京航空航天大学 | A kind of space cavity Asia combustion guidance combustion chamber and engine chamber |
| CN109539312B (en) * | 2018-10-12 | 2019-08-23 | 南京航空航天大学 | A kind of space cavity Asia combustion guidance combustion chamber and engine chamber |
| CN110686275A (en) * | 2019-09-23 | 2020-01-14 | 中国科学院工程热物理研究所 | Combustion chamber flame stabilizing structure for reinforcing mixing and flame propagation |
| CN112432204A (en) * | 2020-12-04 | 2021-03-02 | 中国人民解放军国防科技大学 | Reentrant structure and scramjet that can internal flow drag reduction |
| CN112577070A (en) * | 2020-12-04 | 2021-03-30 | 中国人民解放军国防科技大学 | Low-resistance and high-efficiency scramjet engine thrust chamber integrated design method |
| CN114484503A (en) * | 2022-01-05 | 2022-05-13 | 中国科学院力学研究所 | Self-adaptive geometric throat combustion chamber of wide-range ramjet engine |
| CN115234944A (en) * | 2022-07-14 | 2022-10-25 | 中国人民解放军国防科技大学 | Swirl combined ramjet combustion chamber with stable flame |
| CN115234944B (en) * | 2022-07-14 | 2024-06-21 | 中国人民解放军国防科技大学 | Ramjet combustion chamber with swirl combined flame stabilization |
| CN115628464A (en) * | 2022-10-12 | 2023-01-20 | 哈尔滨工业大学 | Three-channel scramjet engine combustion chamber |
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