CN108999726B - Ramjet engine with liquid aviation kerosene atomized at high speed in advance - Google Patents

Abstract

The invention discloses a ramjet with liquid aviation kerosene preliminarily atomized at high speed, comprising: a diverter cone, an inlet port wall, a combustion chamber wall, a tail nozzle wall, an oil storage tank and an oil delivery pipe; wherein, the diverter cone passes through the The oil delivery pipe is connected with the oil storage tank; the wall surface of the intake port, the wall surface of the combustion chamber and the wall surface of the tail nozzle are connected in sequence; the diverter cone and the oil storage tank are arranged in the intake port as a part In the cavity formed by the wall surface, the wall surface of the combustion chamber and the wall surface of the tail nozzle; an intake port is formed between the diverter cone and the wall surface of the intake port, and between the diverter cone and the wall surface of the combustion chamber A combustion chamber flow channel is formed, a tail nozzle flow channel is formed between the diverter cone and the wall surface of the tail nozzle, and the intake channel, the combustion chamber flow channel and the tail nozzle flow channel are connected in sequence; The top of the split cone is provided with an air inlet hole. The invention improves the economy and safety of the ramjet.

Description

A ramjet with high-speed atomization of liquid aviation kerosene in advance

technical field

The invention belongs to the field of ramjets, and in particular relates to a ramjet with high-speed atomization of liquid aviation kerosene in advance.

Background technique

With the increasing speed requirements of aircraft, traditional turbojet engines can no longer meet the demand for thrust. The ramjet does not have rotating parts such as compressors and turbines. It uses high-speed flow to stagnate in the intake port to convert kinetic energy into pressure energy to complete the compression process. Therefore, ramjets have become the first choice for supersonic and hypersonic vehicles due to their large thrust-to-weight ratio, simple components, and good economic performance during supersonic flight.

At present, ramjets mostly use solid fuels. Such engines are difficult to control, limited in working time, and difficult to store solid fuels, resulting in extremely high costs. The safety performance of ramjets fueled by liquid hydrogen is greatly limited. Aviation kerosene is a kind of fuel with high calorific value, simple storage, high safety performance and good economy. However, the combustion reaction of liquid aviation kerosene can only be carried out after injection, crushing, atomization and evaporation. At the same time, the ignition delay time of liquid aviation kerosene is also relatively long, and the airflow speed in the combustion chamber of the ramjet is extremely fast. The time is extremely short, which limits the application of aviation kerosene in ramjets and increases the difficulty of design.

SUMMARY OF THE INVENTION

The technical problem solved by the present invention is to overcome the deficiencies of the prior art and provide a ramjet with high-speed atomization of liquid aviation kerosene in advance.

The object of the present invention is achieved through the following technical solutions: a ramjet with high-speed atomization of liquid aviation kerosene in advance, comprising: a diverter cone, a wall of an air inlet, a wall of a combustion chamber, a wall of a tail nozzle, an oil storage tank and an oil delivery pipe; The diverter cone is connected with the oil storage tank through the oil delivery pipe; the wall surface of the intake port, the wall surface of the combustion chamber and the wall surface of the tail nozzle are connected in sequence; the diverter cone and the oil storage tank are arranged as a part In the cavity formed by the wall of the intake port, the wall of the combustion chamber and the wall of the tail nozzle; an intake port is formed between the diverter cone and the wall of the intake port, and the diverter cone and the A combustion chamber flow channel is formed between the combustion chamber walls, a tail nozzle flow channel is formed between the split cone and the tail nozzle wall surface, the intake port, the combustion chamber flow channel and the tail nozzle tube The flow channels are connected in sequence; the top of the flow dividing cone is provided with an air inlet hole.

In the above-mentioned ramjet with high-speed atomization of liquid aviation kerosene in advance, the diverter cone includes a cone wall and a fuel atomizer; wherein, the tip of the cone wall is provided with a number of air intake holes; the interior of the cone wall forms A gas collecting cavity; the inside of the cone wall is provided with a fuel atomizer, the cone wall is provided with a direct injection hole corresponding to the fuel atomizer, and the fuel atomizer communicates with the combustion chamber through the direct injection hole The flow passages communicate with each other; the fuel atomizer is connected with the fuel storage tank through the fuel delivery pipe.

In the above-mentioned ramjet with high-speed atomization of liquid aviation kerosene in advance, the fuel atomizer includes several Laval nozzles; wherein, the number of the direct injection holes is consistent with the number of the Laval nozzles; each The Laval nozzles form a circular radius, and one end of each Laval nozzle is located at the center of the circle; each Laval nozzle is connected with the corresponding direct injection orifice.

In the above-mentioned ramjet with high-speed atomization of liquid aviation kerosene, the Mach number of the inlet port is 2-5, and the momentum ratio of the fuel injected by the direct injection hole to the air in the flow channel of the combustion chamber is 10-100.

In the above-mentioned ramjet with high-speed atomization of liquid aviation kerosene, the ratio of the diameter of the intake port Φa to the outer diameter of the tail nozzle wall Φb is 0.5 to 0.8; the ratio of the length La of the intake port to the length Lb of the combustion chamber flow channel is 0.65～0.95.

In the above-mentioned ramjet with high-speed atomization of liquid aviation kerosene in advance, the ratio of the diameter of the air inlet hole to the diameter of the direct injection hole is 5-10.

In the above-mentioned ramjet in which the liquid aviation kerosene is preliminarily atomized at a high speed, the angle θ of the diverter cone is 15° to 30°.

In the above-mentioned ramjet with high-speed atomization of liquid aviation kerosene in advance, the ratio of the area Sa of the roar of the intake port to the area of the roar of the runner of the exhaust pipe is 0.45-0.85.

In the above ramjet with liquid aviation kerosene pre-atomized at high speed, the ratio of the Laval nozzle inlet diameter Φc to the Laval nozzle roar diameter Φd is 1.5 to 2; the Laval nozzle length Lc and the Laval nozzle inlet diameter Φc The ratio is 3.5 to 4.5.

In the above-mentioned ramjet with high-speed atomization of liquid aviation kerosene in advance, the ratio of the diameter Φe of the oil delivery pipe to the diameter Φd of the roar of the Laval nozzle is 1-1.2.

Compared with the prior art, the present invention has the following beneficial effects:

(1) The present invention uses a gas collecting cavity to stagnate air to form a high pressure source, and its configuration is simple, and can make full use of the incoming high-speed air.

(2) The present invention uses the Laval nozzle to atomize the liquid fuel at high speed, which greatly shortens the ignition delay time and the residence time of the fuel in the combustion chamber.

(3) The present invention adopts the direct injection hole to inject the pre-atomized liquid aviation kerosene into the combustion chamber before participating in the combustion reaction, thereby improving the combustion efficiency and combustion stability.

Description of drawings

Various other advantages and benefits will become apparent to those of ordinary skill in the art upon reading the following detailed description of the preferred embodiments. The drawings are for the purpose of illustrating preferred embodiments only and are not to be considered limiting of the invention. Also, the same components are denoted by the same reference numerals throughout the drawings. In the attached image:

Fig. 1 is the structural representation of the ramjet of liquid aviation kerosene preliminarily high-speed atomization provided by the embodiment of the present invention;

2 is a schematic structural diagram of a fuel atomizer provided by an embodiment of the present invention;

FIG. 3 is a cross-sectional view of the relative positions of the Laval nozzle and the oil delivery pipe according to an embodiment of the present invention.

Detailed ways

Exemplary embodiments of the present disclosure will be described in more detail below with reference to the accompanying drawings. While exemplary embodiments of the present disclosure are shown in the drawings, it should be understood that the present disclosure may be embodied in various forms and should not be limited by the embodiments set forth herein. Rather, these embodiments are provided so that the present disclosure will be more thoroughly understood, and will fully convey the scope of the present disclosure to those skilled in the art. It should be noted that the embodiments of the present invention and the features of the embodiments may be combined with each other under the condition of no conflict. The present invention will be described in detail below with reference to the accompanying drawings and in conjunction with the embodiments.

FIG. 1 is a schematic structural diagram of a ramjet with liquid aviation kerosene preliminarily atomized at high speed according to an embodiment of the present invention. As shown in FIG. 1 , the ramjet with high-speed atomization of liquid aviation kerosene in advance includes: a split cone 1, an inlet port wall 3, a combustion chamber wall 4, a tail nozzle wall 5, an oil storage tank 6 and an oil delivery pipe 14; wherein,

The diverter cone 1 is connected with the oil storage tank 6 through the oil delivery pipe 14; the wall surface 3 of the intake port, the wall surface of the combustion chamber 4 and the wall surface 5 of the tail nozzle are connected in turn; In the cavity formed by the combustion chamber wall surface 4 and the tail nozzle wall surface 5; the intake port 10 is formed between the split cone 1 and the intake port wall surface 3, and the combustion chamber flow channel is formed between the split cone 1 and the combustion chamber wall surface 4 8. A tail nozzle flow channel 7 is formed between the split cone 1 and the tail nozzle wall surface 5, and the intake port 10, the combustion chamber flow channel 8 and the tail nozzle flow channel 7 are connected in sequence; Stomata 2.

The diverter cone 1 includes a cone wall 12 and a fuel atomizer 15; the tip of the cone wall 12 is provided with a number of air intake holes 2; the interior of the cone wall 12 forms a gas collecting cavity 11; the interior of the cone wall 12 is provided with fuel The atomizer 15, the cone wall 12 is provided with a direct injection hole 9 corresponding to the fuel atomizer 15, and the fuel atomizer 15 communicates with the combustion chamber flow channel 8 through the direct injection hole 9; the fuel atomizer 15 It is connected to the oil storage tank 6 through the oil pipeline 14 .

FIG. 2 is a schematic structural diagram of a fuel atomizer provided by an embodiment of the present invention. As shown in FIG. 2 , the fuel atomizer 15 includes a number of Laval nozzles 13 ; wherein the number of direct injection nozzles 9 is consistent with the number of Laval nozzles 13 ; each Laval nozzle 13 constitutes a The radius of the circle, one end of each Laval nozzle 13 is located at the center of the circle; each Laval nozzle 13 is connected with the corresponding direct injection hole 9 .

The incoming air is rectified and divided by the diverter cone 1, and then enters the intake hole 2 and the intake port 10 respectively. Accelerating again, the fuel in the fuel storage tank 6 enters the fuel atomizer 15 through the fuel pipe 14, and is rapidly atomized by the air flow accelerated by the Laval nozzle 13, and then injected into the combustion chamber flow channel 8 from the direct injection hole 9; The converted fuel is mixed with the air pressurized through the intake port 10, and a combustion reaction takes place in the combustion chamber flow path 8, and the generated high-temperature and high-pressure gas is ejected through the tail nozzle flow path 7 to realize the fuel oil. The residence time in the combustion chamber is greatly shortened, and the combustion efficiency and combustion stability are improved.

The Mach number of the inlet port 10 is 2 to 5, the momentum ratio of the fuel injected by the direct injection hole 9 to the air in the combustion chamber flow channel 8 is 10 to 100; The ratio of diameter Φb is 0.5-0.8; the ratio of inlet port length La to combustion chamber length Lb is 0.65-0.95; the ratio of intake hole 2 to the diameter of direct injection hole 9 is 5-10; °～30°; the ratio of the roar area Sa of the intake port to the area Sb of the tail nozzle roar is 0.45 to 0.85.

As shown in FIG. 2 , the fuel atomizer 15 is composed of six Laval nozzles 13 .

As shown in Figure 3, the ratio of the Laval nozzle inlet diameter Φc to the Laval nozzle roar diameter Φd is 1.5 to 2; the ratio of the Laval nozzle length Lc to the Laval nozzle inlet diameter Φc is 3.5 to 4.5; The ratio of the diameter of the oil pipeline Φe to the diameter of the Laval nozzle roar Φd is 1 to 1.2 to ensure that the liquid aviation kerosene can be atomized at high speed.

In this embodiment, the air collecting cavity is used to stagnate the air to form a high pressure source, and its configuration is simple, which can make full use of the incoming high-speed air; this embodiment uses a Laval nozzle to atomize the liquid fuel at a high speed, which greatly shortens the time The ignition delay time of the fuel oil and the residence time in the combustion chamber; this embodiment adopts the direct injection hole to inject the pre-atomized liquid aviation kerosene into the combustion chamber to participate in the combustion reaction, which improves the combustion efficiency and combustion stability.

The above-mentioned embodiments are only preferred specific implementations of the present invention, and general changes and substitutions made by those skilled in the art within the scope of the technical solutions of the present invention should be included in the protection scope of the present invention.

Claims (9)

1. a ramjet with high-speed atomization of liquid aviation kerosene in advance, is characterized in that comprising: shunt cone (1), inlet port wall (3), combustion chamber wall (4), tail nozzle wall (5), storage fuel tank (6) and fuel pipeline (14); wherein, The diverter cone (1) is connected with the oil storage tank (6) through the oil delivery pipe (14); the inlet port wall (3), the combustion chamber wall (4) and the tail nozzle wall (5) are connected in sequence; The diverter cone (1) and the oil storage tank (6) are arranged as a part in the space formed by the wall surface of the intake port (3), the wall surface of the combustion chamber (4) and the wall surface of the tail nozzle (5). cavity; An intake port (10) is formed between the split cone (1) and the wall surface of the intake port (3), and a combustion chamber flow channel is formed between the split cone (1) and the wall surface of the combustion chamber (4). (8), a tail nozzle flow channel (7) is formed between the split cone (1) and the tail nozzle wall surface (5), the intake port (10), the combustion chamber flow channel (8) ) is communicated with the tail nozzle flow channel (7) in turn; An air intake hole (2) is provided on the top of the split cone (1); wherein, The diverter cone (1) includes a cone wall (12) and a fuel atomizer (15); wherein, The tip of the cone wall (12) is provided with a plurality of air inlet holes (2); the inside of the cone wall (12) forms a gas collecting cavity (11); The inside of the cone wall (12) is provided with a fuel atomizer (15), and the cone wall (12) is provided with a direct injection hole (9) corresponding to the fuel atomizer (15). The atomizer (15) is communicated with the combustion chamber flow channel (8) through the direct injection hole (9); The fuel atomizer (15) is connected with the fuel storage tank (6) through the fuel delivery pipe (14). 2. The ramjet with high-speed atomization of liquid aviation kerosene in advance according to claim 1, characterized in that: the fuel atomizer (15) comprises several Laval nozzles (13); wherein, The number of the direct injection nozzles (9) is consistent with the number of the Laval nozzles (13); Each Laval nozzle (13) forms a circular radius, and one end of each Laval nozzle (13) is located at the center of the circle; Each Laval nozzle (13) is connected with a corresponding direct injection nozzle (9). 3. The ramjet with high-speed atomization of liquid aviation kerosene in advance according to claim 1, characterized in that: the inlet Mach number of the air inlet (10) is 2 to 5, and the fuel injected by the direct injection hole (9) The momentum ratio to the air in the combustion chamber flow channel (8) is 10-100. 4. The ramjet with high-speed atomization of liquid aviation kerosene in advance according to claim 1, is characterized in that: the ratio of the diameter Φa of the air inlet to the outer diameter Φb of the wall surface of the tail nozzle is 0.5～0.8; The ratio to the length Lb of the flow passage of the combustion chamber is 0.65 to 0.95. 5 . The ramjet with liquid aviation kerosene preliminarily atomized at high speed according to claim 1 , wherein the ratio of the diameter of the air inlet hole ( 2 ) to the direct injection hole ( 9 ) is 5-10. 6 . 6 . The ramjet with liquid aviation kerosene preliminarily atomized at high speed according to claim 1 , wherein the split cone angle θ is 15° to 30°. 7 . 7. The ramjet of liquid aviation kerosene preliminarily atomized at high speed according to claim 1, characterized in that: the ratio of the area Sa of the intake duct to the area Sb of the roar of the exhaust pipe is 0.45 to 0.85. 8. The ramjet with high-speed atomization of liquid aviation kerosene in advance according to claim 2, characterized in that: the ratio of the Laval nozzle inlet diameter Φc to the Laval nozzle roar diameter Φd is 1.5 to 2; The ratio of the pipe length Lc to the Laval nozzle inlet diameter Φc is 3.5 to 4.5. 9 . The ramjet with high-speed atomization of liquid aviation kerosene in advance according to claim 2 , wherein the ratio of the diameter Φe of the oil delivery pipe to the diameter Φd of the roar of the Laval nozzle is 1-1.2. 10 .

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