CN110822480B - Ignition device in supersonic concave cavity combustion chamber and scramjet engine - Google Patents
Ignition device in supersonic concave cavity combustion chamber and scramjet engine Download PDFInfo
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- CN110822480B CN110822480B CN201911182357.5A CN201911182357A CN110822480B CN 110822480 B CN110822480 B CN 110822480B CN 201911182357 A CN201911182357 A CN 201911182357A CN 110822480 B CN110822480 B CN 110822480B
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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
Abstract
The invention provides an ignition device in a supersonic concave cavity combustion chamber and a scramjet engine. The fuel jet holes and the concave cavity are arranged in the supersonic combustion chamber, the fuel jet holes are arranged at the upstream of the concave cavity, and the fuel injected by the fuel jet holes is transmitted along the direction of supersonic airflow transmission in a main flow passage of the supersonic combustion chamber; the cavity bottom wall is obliquely provided with a guide plate along the direction of supersonic air flow propagation in the main flow passage, the lower end of the guide plate is connected to the cavity bottom wall, the lower end of the guide plate is provided with a gap, and the cavity bottom wall below the inner side of the guide plate is provided with a spark plug for ignition. The invention applies the guide plate to the interior of the concave cavity to improve the local flow velocity and the equivalence ratio in the concave cavity, thereby realizing the ignition enhancement effect.
Description
Technical Field
The invention relates to the technical field of designing of scramjet engines, in particular to an ignition device in a supersonic concave cavity combustion chamber and a scramjet engine.
Background
The concave cavity flame stabilizer is widely applied to a scramjet engine combustion chamber at present. The supersonic airflow flowing through the concave cavity forms a backflow area in the concave cavity, so that the flame can be always resident in the concave cavity and can be used as a new fire source to continuously ignite the fuel coming upstream, and the flame stabilization is realized. The cavity can integrate the functions of fuel injection, mixing enhancement and flame stabilization in the supersonic combustion chamber, and plays an important role in improving the performance of the scramjet engine.
The fuel injection/ignition/flame stabilization/cooling integrated cavity common in the current engineering comprises fuel injection, ignition and flame stabilization integration, the cavity is used as a basic configuration, fuel is injected at the upstream or/and bottom of the cavity, and a torch/plasma igniter is also arranged at the bottom of the cavity.
The publication number is CN104764045A, which discloses a supersonic combustion chamber concave cavity ignition device and a scramjet engine, and is an invention patent previously applied by the applicant. The triangular wing surface ignition device is mainly characterized in that the triangular wing surface ignition device is arranged on the bottom wall of the concave cavity, and the transportation process of fuel in the concave cavity along with the air flow is changed by reasonably arranging the shape structure of the triangular wing surface, so that the effects of relieving a rich combustion environment near a spark plug and enhancing the mixing of local fuel and air are achieved. In practical application, the technical scheme has the following defects: the flow field structure inside the concave cavity is complex, so that the proper local speed and local equivalence ratio near the ignition position are difficult to ensure, formation and development of initial fire nuclei after ignition of the spark plug are not facilitated, and the ignition failure is easy to occur. Specifically, the spark plug is arranged on the bottom surface of the cavity, a blocking piece is arranged in the downstream direction of the spark plug, and when the spark plug ignites, an initial fire core formed at an ignition position cannot directly propagate along the downstream direction of the bottom surface of the cavity due to the blocking effect, so that the fire core is subjected to more air flow dissipation effects, and the ignition is easy to fail.
Disclosure of Invention
The invention provides an ignition device in a supersonic concave cavity combustion chamber and a scramjet engine. The invention applies the guide plate to the interior of the concave cavity to improve the local flow velocity and the equivalence ratio in the concave cavity, thereby realizing the ignition enhancement effect.
In order to realize the purpose of the invention, the following technical scheme is adopted for realizing the purpose:
an ignition device in a supersonic cavity combustion chamber is provided with a fuel spray hole and a cavity in the supersonic combustion chamber, wherein the fuel spray hole is arranged at the upstream of the cavity, and fuel sprayed out from the fuel spray hole is spread along the direction of supersonic airflow spreading in a main flow passage of the supersonic combustion chamber;
the cavity bottom wall is provided with a guide plate along the propagation direction of the supersonic air flow in the main flow channel, the lower end of the guide plate is connected to the cavity bottom wall, a gap is formed in the lower end of the guide plate, and a spark plug used for ignition is arranged on the cavity bottom wall below the inner side of the guide plate.
According to the invention, fuel injected from the fuel spray holes is sucked into the cavity, and under the action of the guide plate in the cavity, part of the fuel flows into the lower area of the inner side of the guide plate and resides in the lower area of the inner side of the guide plate, and due to the existence of the guide plate, the lower area of the inner side of the guide plate can reside in the fuel and improve the local equivalence ratio of the fuel while forming a local low-speed backflow area, so that the formation and residence of an initial fire core after ignition of a spark plug below the inner side of the guide plate are facilitated, the lower end of the guide plate is provided with a gap, and the fire core can penetrate through the gap along the bottom wall of the.
As a preferred technical scheme of the invention, the bottom side wall of the lower end of the guide plate is connected to the bottom wall of the concave cavity, and a gap is arranged at the lower end of the guide plate or on the guide plate close to the lower end of the guide plate.
As the preferable technical scheme of the invention, the two sides of the lower end of the guide plate are provided with the connecting seats which are connected with the bottom wall of the concave cavity through the connecting seats on the two sides, and a gap is formed between the middle part of the lower end of the guide plate and the bottom wall of the concave cavity.
As a preferable aspect of the present invention, the length direction of the baffle is parallel to the direction in which the supersonic air flow propagates in the main flow passage, and the spark plug is disposed on a centerline in the length direction of the baffle.
As a preferred embodiment of the present invention, the longitudinal direction of the cavity is parallel to the direction of propagation of the supersonic air flow in the primary flow channel, and the cavity has a cavity front wall and a cavity rear wall in the longitudinal direction of the cavity. The cavity front wall is perpendicular to the direction of supersonic air flow propagation in the main flow channel, and the cavity rear wall is obliquely arranged along the direction of supersonic air flow propagation in the main flow channel, preferably, the oblique angle is 45 degrees.
As a preferred technical solution of the present invention, the flow guide plate includes an inclined support plate and a top side plate, a lower end of the inclined support plate is connected to the bottom wall of the cavity, and a gap is formed at a lower end of the inclined support plate, the inclined support plate is arranged obliquely along a direction in which the supersonic air flow in the main flow channel propagates, an upper end of the inclined support plate is connected to one end of the top side plate to form a whole, and an extending direction of the top side plate is consistent with a direction in which the supersonic air flow in the main flow channel propagates.
As a preferable technical scheme of the invention, the inner included angle between the inclined support plate and the top side plate is 120-150 degrees.
As a preferable aspect of the present invention, the longitudinal direction of the slit is parallel to the width direction of the baffle. The length of the gap is 80% -95% of the width of the guide plate, and the width of the gap is 1 mm-5 mm.
The structure form of the guide plate is not limited, and the guide plate can be a flat plate which is obliquely arranged, can also be a curved plate which is obliquely arranged, such as an arc-shaped plate, and can also be designed into a folded plate which is formed by connecting a plurality of flat plates or/and curved plates into a whole according to the requirement.
The scramjet engine comprises a supersonic combustion chamber, wherein an ignition device in the supersonic concave cavity combustion chamber is arranged in the supersonic combustion chamber.
The invention has the advantages that:
the invention provides an ignition device in a supersonic concave cavity combustion chamber and a scramjet engine, which solve the problem that the formation and development of an initial fire core are not facilitated by the local fuel equivalence ratio and the local flow rate of injected fuel sucked to an ignition position in a concave cavity by adopting the upstream wall surface of the concave cavity. The invention can mainly meet the requirement of reliable ignition and combustion in the concave cavity under the Ma6 flight condition, and meanwhile, the device does not cause total pressure loss by being arranged in the concave cavity and has no great influence on the flame stabilization process.
According to the invention, under the condition that fuel is injected at the upstream of the cavity, the guide plate is arranged on the bottom wall of the cavity, so that a local low-speed backflow area can be formed in the guide plate, and fuel is resident to improve the fuel equivalence ratio, thereby facilitating ignition.
The lower end of the guide plate is connected to the bottom wall of the cavity, and the lower end of the guide plate is provided with a gap, so that the initial fire core can pass through the gap along the bottom wall of the cavity and can be spread to the front wall of the cavity after growing.
The structure form of the guide plate is not limited, and the guide plate can be a flat plate which is obliquely arranged, can also be a curved plate which is obliquely arranged, such as an arc-shaped plate, and can also be designed into a folded plate which is formed by connecting a plurality of flat plates or/and curved plates into a whole according to the requirement. The flow guide plate is arranged on the bottom wall of the concave cavity, and the shape structure of the flow guide plate is reasonably arranged, so that a flow field structure near an ignition position is improved, and the effect of forming a local rich combustion backflow area and facilitating formation and propagation of an initial fire core is achieved. The guide plate is simple in structure and easy to process and manufacture, the guide plate is only arranged inside the cavity to cover the local backflow area structure, and the whole cavity backflow area structure is not affected, so that the flame stability of the cavity is kept.
Drawings
In order to more clearly illustrate the technical solutions in the embodiments or the prior art of the present invention, the drawings used in the description of the embodiments or the prior art will be briefly described below, and it is obvious that the drawings in the following description are only some embodiments of the present invention, and for the ordinary skill in the art, other drawings can be obtained according to these drawings without creative efforts.
FIG. 1 is a schematic structural diagram of a first embodiment of the present invention;
fig. 2 is a schematic structural view of a baffle employed in the first embodiment of the present invention;
FIG. 3 is a schematic structural diagram of a second embodiment of the present invention
Fig. 4 is a graph illustrating the effect of baffles on the fuel transport process within the cavity.
Reference numbers in the figures:
1. a concave cavity; 2. a fuel injection hole; 3. a baffle; 4. an ignition plug; 5. a cavity bottom wall; 6. a cavity front wall; 7. a cavity back wall; 8. a gap; 9. inclining the support plate; 10. a top side plate; 11. a connecting seat.
Detailed Description
The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be obtained by a person skilled in the art without making any creative effort based on the embodiments of the present invention, belong to the protection scope of the present invention.
Fig. 1 is a schematic structural diagram of embodiment 1 of the present invention.
A fuel spray hole 2 and a concave cavity 1 are arranged in a supersonic combustion chamber, the fuel spray hole 2 is arranged at the upstream of the concave cavity 1, and fuel sprayed out from the fuel spray hole 2 is spread along the direction of supersonic airflow spreading in a main flow passage of the supersonic combustion chamber.
The length direction of the cavity 1 is parallel to the propagation direction of the supersonic air flow in the main flow channel, and the cavity 1 is provided with a cavity front wall 6 and a cavity rear wall 7 in the length direction of the cavity 1. And the flow guide plate 3 is obliquely arranged on the bottom wall 5 of the concave cavity along the direction of the ultrasonic air flow in the main flow channel. In this embodiment, the guide plate 3 includes an inclined support plate 9 and a top side plate 10, the lower end of the inclined support plate 9 is connected to the cavity bottom wall 5, and a gap 8 is formed at the lower end of the inclined support plate 9. Connecting seats 11 are arranged on two sides of the lower end of the inclined supporting plate 9 and are connected with the cavity bottom wall 5 through the connecting seats 11 on the two sides, and a gap 8 is formed between the middle of the lower end of the inclined supporting plate 9 and the cavity bottom wall 5.
The inclined supporting plate 9 is obliquely arranged along the direction of the supersonic air flow propagation in the main flow channel, the upper end of the inclined supporting plate 9 is connected with one end of the top side plate 10 into a whole, and the extending direction of the other end of the top side plate 10 is consistent with the direction of the supersonic air flow propagation in the main flow channel. A spark plug 4 for ignition is arranged on the bottom wall 5 of the concave cavity below the inner side of the guide plate 3. Preferably, the length direction of the deflector 3 is parallel to the propagation direction of supersonic air flow in the main flow channel, and the spark plug 4 is arranged on the middle line of the length direction of the deflector 3.
Fig. 2 is a schematic structural diagram of a baffle used in the first embodiment of the present invention. The baffle 3 comprises an inclined support plate 9 and a top side plate 10. The internal included angle between the inclined support plate 9 and the top side plate 10 is 135 degrees. The thickness of the guide plate is 2mm, the width of the guide plate is 30mm, the length of the guide plate is 15mm, and the height of the guide plate is 12 mm. The lower end of the guide plate is connected with the cavity bottom wall 5 through two connecting seats 11 with the height of 2mm on two sides, and a gap 8 with the length of 26mm and the width of 2mm exists at the connecting position of the guide plate and the cavity bottom wall 5.
Fig. 3 is a schematic structural diagram of embodiment 2 of the present invention.
A fuel spray hole 2 and a concave cavity 1 are arranged in a supersonic combustion chamber, the fuel spray hole 2 is arranged at the upstream of the concave cavity 1, and fuel sprayed out from the fuel spray hole 2 is spread along the direction of supersonic airflow spreading in a main flow passage of the supersonic combustion chamber.
The length direction of the cavity 1 is parallel to the propagation direction of the supersonic air flow in the main flow channel, and the cavity 1 is provided with a cavity front wall 6 and a cavity rear wall 7 in the length direction of the cavity 1. The cavity front wall 6 is perpendicular to the direction of supersonic air flow propagation in the main flow channel, and the cavity rear wall 7 is obliquely arranged along the direction of supersonic air flow propagation in the main flow channel, and the inclination angle can be set according to the situation, such as being set to 45 degrees. In practice, the form of the cavity is not limited, and may be any one of the forms of the cavity in the prior art, such as a rectangular cavity.
And the flow guide plate 3 is obliquely arranged on the bottom wall 5 of the concave cavity along the direction of the ultrasonic air flow in the main flow channel. In this embodiment, the lower extreme of guide plate 3 is connected on cavity diapire 5 through modes such as welding or joint, transversely has seted up a gap 8 on the guide plate 3 that is close to guide plate 3 lower extreme. A spark plug 4 for ignition is arranged on the bottom wall 5 of the concave cavity below the inner side of the guide plate 3.
Fig. 4 is a graph illustrating the effect of baffles on the fuel transport process within the cavity. When fuel ejected from the fuel spray holes 2 passes through the concave cavity 1, the fuel is sucked into the concave cavity 1, under the action of the guide plate 3 in the concave cavity 1, part of the fuel flows into the lower area on the inner side of the guide plate 3 and resides in the lower area, and due to the existence of the guide plate 3, the lower area on the inner side of the guide plate 3 forms a local low-speed backflow area and resides in the low-speed backflow area, and meanwhile, the fuel is resident to improve the fuel equivalence ratio, so that the formation and residence of an initial fire core after the ignition of a spark plug below the inner side of. The lower end of the deflector 3 is provided with a gap 8, and the fire core passes through the gap 8 along the cavity bottom wall 5 to propagate to the cavity front wall 6, thereby facilitating the propagation of the initial fire core.
Example 3:
the scramjet engine comprises a supersonic combustion chamber, wherein an ignition device in the supersonic concave cavity combustion chamber is arranged in the supersonic combustion chamber.
When a transverse fuel injection scheme at the upstream of the concave cavity is adopted, the position with high local speed at the bottom wall of the concave cavity is formed at the rear edge of the concave cavity, and the local fuel equivalence ratio is also high; while the locally slow position of the bowl bottom wall typically occurs at the bowl leading edge and middle where the local fuel equivalence is relatively low. Therefore, when the fuel flows through the ignition position of the bottom wall of the concave cavity along with the airflow, the local speed and the local equivalence ratio are difficult to ensure to be proper, and the problems of difficult ignition and flameout are easy to occur. According to the invention, the guide plate device is arranged above the ignition position of the bottom wall of the concave cavity, under the condition of fuel injection at the upstream of the same concave cavity, a local reflux area can be formed through the guide plate to reduce the air flow speed, the fuel can be resident in the guide plate to provide a local equivalence ratio, and the gap between the guide plate and the bottom wall of the concave cavity can ensure the mass exchange of the fuel and the air and provide an opening direction for the development of an initial flame kernel to the front edge of the concave cavity, so that the ignition enhancement promotion effect is achieved under the condition of supersonic speed incoming flow.
According to the invention, the guide plate with a certain angle, width and shape is arranged on the bottom wall of the concave cavity, so that the transportation process of the fuel in the concave cavity along with the shear layer is changed, the mixing of the fuel and air is enhanced, and the effect of enhancing the ignition capability of the concave cavity is achieved.
In summary, although the present invention has been described with reference to the preferred embodiments, it should be understood that various changes and modifications can be made by those skilled in the art without departing from the spirit and scope of the invention.
Claims (10)
1. An ignition device in a supersonic concave cavity combustion chamber is characterized in that: the fuel jet holes and the concave cavity are arranged in the supersonic combustion chamber, the fuel jet holes are arranged at the upstream of the concave cavity, and the fuel injected by the fuel jet holes is transmitted along the direction of supersonic airflow transmission in a main flow passage of the supersonic combustion chamber; the cavity bottom wall is obliquely provided with a guide plate along the direction of supersonic air flow propagation in the main flow passage, the lower end of the guide plate is connected to the cavity bottom wall, the lower end of the guide plate is provided with a gap, and the cavity bottom wall below the inner side of the guide plate is provided with a spark plug for ignition.
2. An ignition device in a supersonic cavity combustion chamber as defined in claim 1, wherein: the fuel entrainment that fuel orifice spouts gets into the cavity, under the effect of the guide plate in the cavity, part fuel flows into the inboard below region of guide plate and dwells wherein, because the existence of guide plate makes the inboard below region of guide plate when forming local low-speed backward flow district and dwell fuel and improve the local equivalence ratio of fuel, thereby do benefit to the formation and the dwell of the initial flame kernel after the spark plug ignition of the inboard below of guide plate, the lower extreme of guide plate is equipped with a gap, the flame kernel can pass the gap along the cavity diapire and propagate to the cavity antetheca, thereby do benefit to the propagation of initial flame kernel.
3. An ignition device in a supersonic cavity combustion chamber as defined in claim 1, wherein: the bottom side wall of the lower end of the guide plate is connected to the bottom wall of the concave cavity, and a gap is formed in the lower end of the guide plate or the guide plate close to the lower end of the guide plate.
4. An ignition device in a supersonic cavity combustion chamber as defined in claim 1, wherein: the lower extreme both sides of guide plate are equipped with the connecting seat, are connected through the connecting seat and the cavity diapire of both sides, form a gap between the lower extreme middle part of guide plate and the cavity diapire.
5. An ignition device in a supersonic cavity combustion chamber as defined in any one of claims 1 to 4, wherein: the length direction of the guide plate is parallel to the propagation direction of supersonic air flow in the main flow channel, and the spark plug is arranged on the middle line of the guide plate in the length direction.
6. An ignition device in a supersonic cavity combustion chamber as defined in claim 5, wherein: the length direction of the concave cavity is parallel to the propagation direction of the supersonic speed airflow in the main flow channel, and the concave cavity is provided with a concave cavity front wall and a concave cavity rear wall in the length direction of the concave cavity; the cavity front wall is perpendicular to the direction of supersonic air flow propagation in the main flow channel, and the cavity rear wall is obliquely arranged along the direction of supersonic air flow propagation in the main flow channel, wherein the inclination angle is 45 degrees.
7. An ignition device in a supersonic cavity combustion chamber as defined in claim 1, wherein: the guide plate includes tilt support board and top curb plate, and tilt support board's lower extreme is connected on the cavity diapire and tilt support board's lower extreme is equipped with a gap, and tilt support board is in the same direction slope setting of supersonic velocity air current propagation in the sprue, and tilt support board's upper end is even as an organic whole with the one end of top curb plate, and the extending direction of top curb plate is put unanimously with the direction of supersonic velocity air current propagation in the sprue.
8. An ignition device in a supersonic cavity combustion chamber as defined in claim 7, wherein: the inner included angle between the inclined supporting plate and the top side plate is 120-150 degrees.
9. An ignition device in a supersonic cavity combustion chamber as defined in claim 8, wherein: the length of the gap is 80% -95% of the width of the guide plate, and the height of the gap is 1 mm-5 mm.
10. A scramjet engine comprising a supersonic combustion chamber, characterized in that an ignition device in the supersonic cavity combustion chamber as claimed in claim 1 is provided in the supersonic combustion chamber.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201911182357.5A CN110822480B (en) | 2019-11-27 | 2019-11-27 | Ignition device in supersonic concave cavity combustion chamber and scramjet engine |
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| CN201911182357.5A CN110822480B (en) | 2019-11-27 | 2019-11-27 | Ignition device in supersonic concave cavity combustion chamber and scramjet engine |
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| CN110822480B true CN110822480B (en) | 2020-08-11 |
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Families Citing this family (4)
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| CN112128799B (en) * | 2020-08-18 | 2021-11-23 | 南京航空航天大学 | Film evaporation type flame stabilizer and combustion chamber |
| CN112361379B (en) * | 2020-11-18 | 2022-03-18 | 中国人民解放军国防科技大学 | Ignition structure of supersonic concave cavity combustion chamber and scramjet engine |
| CN112668201B (en) * | 2021-01-11 | 2022-10-18 | 中国人民解放军国防科技大学 | Supersonic combustion chamber fuel injection design method based on non-uniform air flow of air inlet |
| CN112781071B (en) * | 2021-01-14 | 2022-04-22 | 中国人民解放军空军工程大学 | Method for controlling concave cavity flow by exciting arc discharge on different sides |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012013007A (en) * | 2010-07-01 | 2012-01-19 | Mitsubishi Heavy Ind Ltd | Supersonic combustor |
| CN104764045A (en) * | 2015-04-21 | 2015-07-08 | 中国人民解放军国防科学技术大学 | Supersonic combustion chamber cavity ignition device and scramjet engine |
| CN105180211A (en) * | 2015-09-02 | 2015-12-23 | 中国人民解放军国防科学技术大学 | Combustion chamber with cavity flame holder and supersonic combustion ramjet engine |
| CN105180212A (en) * | 2015-09-02 | 2015-12-23 | 中国人民解放军国防科学技术大学 | Combustion chamber of supersonic combustion ramjet engine |
| CN105716115A (en) * | 2016-03-07 | 2016-06-29 | 厦门大学 | Design method for improving fuel injecting and mixing in super-combustion combustion room |
| CN105849382A (en) * | 2013-12-26 | 2016-08-10 | 丰田自动车株式会社 | Combustion chamber structure of spark-ignition internal combustion engine |
-
2019
- 2019-11-27 CN CN201911182357.5A patent/CN110822480B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| JP2012013007A (en) * | 2010-07-01 | 2012-01-19 | Mitsubishi Heavy Ind Ltd | Supersonic combustor |
| CN105849382A (en) * | 2013-12-26 | 2016-08-10 | 丰田自动车株式会社 | Combustion chamber structure of spark-ignition internal combustion engine |
| CN104764045A (en) * | 2015-04-21 | 2015-07-08 | 中国人民解放军国防科学技术大学 | Supersonic combustion chamber cavity ignition device and scramjet engine |
| CN105180211A (en) * | 2015-09-02 | 2015-12-23 | 中国人民解放军国防科学技术大学 | Combustion chamber with cavity flame holder and supersonic combustion ramjet engine |
| CN105180212A (en) * | 2015-09-02 | 2015-12-23 | 中国人民解放军国防科学技术大学 | Combustion chamber of supersonic combustion ramjet engine |
| CN105716115A (en) * | 2016-03-07 | 2016-06-29 | 厦门大学 | Design method for improving fuel injecting and mixing in super-combustion combustion room |
Non-Patent Citations (2)
| Title |
|---|
| 凹腔底壁喷射位置的数值模拟与试验;杨阳;《推进技术》;20120630;第33卷(第3期);418-423 * |
| 导流片与进口壁面的距离对驻涡燃烧室性能影响的研究;魏佳加;《南昌航空大学学报: 自然科学版》;20151231;第29卷(第4期);7-12 * |
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