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

Ramjet engine with liquid aviation kerosene atomized at high speed in advance Download PDF

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Publication number
CN108999726B
CN108999726B CN201810502304.6A CN201810502304A CN108999726B CN 108999726 B CN108999726 B CN 108999726B CN 201810502304 A CN201810502304 A CN 201810502304A CN 108999726 B CN108999726 B CN 108999726B
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Prior art keywords
wall surface
air inlet
combustion chamber
cone
nozzle
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CN108999726A (en
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赵永胜
欧平
张江
吴军飞
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China Academy of Aerospace Aerodynamics CAAA
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China Academy of Aerospace Aerodynamics CAAA
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    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K7/00Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof
    • F02K7/10Plants in which the working fluid is used in a jet only, i.e. the plants not having a turbine or other engine driving a compressor or a ducted fan; Control thereof characterised by having ram-action compression, i.e. aero-thermo-dynamic-ducts or ram-jet engines
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F02COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
    • F02KJET-PROPULSION PLANTS
    • F02K1/00Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
    • F02K1/78Other construction of jet pipes
    • F02K1/82Jet pipe walls, e.g. liners
    • FMECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F23COMBUSTION APPARATUS; COMBUSTION PROCESSES
    • F23RGENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
    • F23R3/00Continuous combustion chambers using liquid or gaseous fuel
    • F23R3/28Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply
    • F23R3/286Continuous combustion chambers using liquid or gaseous fuel characterised by the fuel supply having fuel-air premixing devices

Abstract

The invention discloses a ramjet engine for high-speed atomization of liquid aviation kerosene in advance, which comprises: the device comprises a splitter cone, an air inlet channel wall surface, a combustion chamber wall surface, a tail nozzle wall surface, an oil storage tank and an oil conveying pipe; the flow distribution cone is connected with the oil storage tank through the oil conveying pipe; the wall surface of the air inlet passage, the wall surface of the combustion chamber and the wall surface of the tail nozzle are sequentially connected; the splitter cone and the oil storage tank are arranged in a cavity formed by the wall surface of the air inlet channel, the wall surface of the combustion chamber and the wall surface of the tail nozzle as a part; an air inlet channel is formed between the splitter cone and the wall surface of the air inlet channel, a combustion chamber flow channel is formed between the splitter cone and the wall surface of the combustion chamber, a tail nozzle flow channel is formed between the splitter cone and the wall surface of the tail nozzle, and the air inlet channel, the combustion chamber flow channel and the tail nozzle flow channel are sequentially communicated; and an air inlet hole is formed in the top of the shunting cone. The invention improves the economy and the safety of the ramjet.

Description

Ramjet engine with liquid aviation kerosene atomized at high speed in advance
Technical Field
The invention belongs to the field of ramjet engines, and particularly relates to a ramjet engine with liquid aviation kerosene atomized at high speed in advance.
Background
With the ever-increasing demands on aircraft speed, conventional turbojet engines have been unable to meet the thrust requirements. The ramjet engine has no rotating parts such as a gas compressor, a turbine and the like, and utilizes high-speed incoming flow to stagnate in an air inlet channel to convert kinetic energy into pressure energy to complete the compression process. Therefore, the ramjet has the characteristics of large thrust-weight ratio, simple parts, good economic performance in supersonic flying and the like, and becomes the first choice of supersonic and hypersonic aircrafts.
At present, the ramjet mostly adopts solid fuel, the control of the ramjet is difficult, the working time is limited, meanwhile, the solid fuel is difficult to store, and the cost is extremely high; the safety performance of the ramjet engine using liquid hydrogen as fuel is greatly limited. Aviation kerosene is a fuel with high heat value, simple storage, high safety performance and good economical efficiency. However, the combustion reaction of the liquid aviation kerosene can be carried out only after the liquid aviation kerosene is injected, crushed, atomized and evaporated, the ignition delay time of the liquid aviation kerosene is relatively long, and the air flow velocity in a combustion chamber of the ramjet engine is extremely high, so that the residence time of the fuel is extremely short, the application of the aviation kerosene in the ramjet engine is limited, and the design difficulty is increased.
Disclosure of Invention
The technical problem solved by the invention is as follows: the defects of the prior art are overcome, the ramjet with the liquid aviation kerosene atomized at high speed in advance is provided, and the economical efficiency and safety of the ramjet are improved by the working mode of high-speed atomization in advance.
The purpose of the invention is realized by the following technical scheme: a ramjet engine for high-speed pre-atomization of liquid aviation kerosene comprising: the device comprises a splitter cone, an air inlet channel wall surface, a combustion chamber wall surface, a tail nozzle wall surface, an oil storage tank and an oil conveying pipe; the flow distribution cone is connected with the oil storage tank through the oil conveying pipe; the wall surface of the air inlet passage, the wall surface of the combustion chamber and the wall surface of the tail nozzle are sequentially connected; the splitter cone and the oil storage tank are arranged in a cavity formed by the wall surface of the air inlet channel, the wall surface of the combustion chamber and the wall surface of the tail nozzle as a part; an air inlet channel is formed between the splitter cone and the wall surface of the air inlet channel, a combustion chamber flow channel is formed between the splitter cone and the wall surface of the combustion chamber, a tail nozzle flow channel is formed between the splitter cone and the wall surface of the tail nozzle, and the air inlet channel, the combustion chamber flow channel and the tail nozzle flow channel are sequentially communicated; and an air inlet hole is formed in the top of the shunting cone.
In the ramjet engine for high-speed atomization of the liquid aviation kerosene in advance, the shunting cone comprises a cone wall and a fuel atomizer; wherein, the tip of the conical wall is provided with a plurality of air inlets; a gas collecting cavity is formed inside the conical wall; a fuel atomizer is arranged inside the conical wall, a direct injection type spray hole corresponding to the fuel atomizer is formed in the conical wall, and the fuel atomizer is communicated with a combustion chamber flow passage through the direct injection type spray hole; the fuel atomizer is connected with the oil storage tank through the oil delivery pipe.
In the ramjet engine for high-speed atomization of the liquid aviation kerosene in advance, the fuel atomizer comprises a plurality of Laval nozzles; wherein the number of the direct injection holes is consistent with that of the Laval nozzles; each Laval nozzle forms a circular radius, and one end of each Laval nozzle is positioned at the position of the center of a circle; each Laval nozzle is connected with the corresponding direct injection hole.
In the ramjet engine with the liquid aviation kerosene atomized at high speed in advance, the Mach number of an inlet of the air inlet channel is 2-5, and the momentum ratio of fuel oil injected by the direct injection type spray holes to air in a runner of a combustion chamber is 10-100.
In the ramjet engine in which the liquid aviation kerosene is atomized at a high speed in advance, the ratio of the diameter phi a of the air inlet channel to the outer diameter phi b of the wall surface of the tail nozzle is 0.5-0.8; the ratio of the length La of the intake passage to the length Lb of the combustion chamber flow passage is 0.65 to 0.95.
In the ramjet engine in which the liquid aviation kerosene is atomized at a high speed in advance, the diameter ratio of the air inlet to the direct injection orifice is 5-10.
In the ramjet engine with the liquid aviation kerosene atomized at high speed in advance, the angle theta of the splitter cone is 15-30 degrees.
In the ramjet engine in which the liquid aviation kerosene is atomized at a high speed in advance, the ratio of the area Sa of the throat of the air inlet to the area Sb of the throat of the exhaust nozzle is 0.45-0.85.
In the ramjet engine in which the liquid aviation kerosene is atomized at a high speed in advance, the ratio of the inlet diameter phi c of the Laval nozzle to the throat diameter phi d of the Laval nozzle is 1.5-2; the ratio of the length Lc of the Laval nozzle to the inlet diameter Phic of the Laval nozzle is 3.5-4.5.
In the ramjet engine in which the liquid aviation kerosene is atomized at a high speed in advance, the ratio of the diameter phi e of the oil delivery pipe to the diameter phi d of the throat of the laval nozzle is 1-1.2.
Compared with the prior art, the invention has the following beneficial effects:
(1) the invention adopts the air collecting cavity to stagnate the air to form high pressure origin, has simple structure and can fully utilize the incoming high-speed air.
(2) The invention adopts the Laval nozzle to atomize the liquid fuel at high speed, thereby greatly shortening the ignition delay time of the fuel and the residence time in the combustion chamber.
(3) The invention adopts the direct injection type spray holes to inject the liquid aviation kerosene atomized in advance into the combustion chamber to participate in the combustion reaction, thereby improving the combustion efficiency and the combustion stability.
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 only for purposes of illustrating the preferred embodiments and are not to be construed as limiting the invention. Also, like reference numerals are used to refer to like parts throughout the drawings. In the drawings:
FIG. 1 is a schematic structural diagram of a ramjet engine with high-speed liquid aviation kerosene atomization in advance provided by the embodiment of the invention;
FIG. 2 is a schematic structural view of a fuel atomizer provided in an embodiment of the present invention;
fig. 3 is a cross-sectional view of the relative positions of a laval nozzle and an oil pipeline provided in an embodiment of the present invention.
Detailed Description
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 to the embodiments set forth herein. Rather, these embodiments are provided so that this disclosure will be thorough and complete, and will fully convey the scope of the disclosure to those skilled in the art. It should be noted that the embodiments and features of the embodiments may be combined with each other without conflict. The present invention will be described in detail below with reference to the embodiments with reference to the attached drawings.
FIG. 1 is a schematic structural diagram of a ramjet engine with high-speed liquid aviation kerosene atomization in advance provided by the embodiment of the invention. As shown in fig. 1, the ramjet engine in which liquid jet fuel is atomized at a high speed in advance includes: the device comprises a splitter cone 1, an air inlet channel wall surface 3, a combustion chamber wall surface 4, a tail nozzle wall surface 5, an oil storage tank 6 and an oil conveying pipe 14; wherein the content of the first and second substances,
the shunt cone 1 is connected with the oil storage tank 6 through an oil delivery pipe 14; the wall surface 3 of the air inlet channel, the wall surface 4 of the combustion chamber and the wall surface 5 of the tail nozzle are connected in sequence; the splitter cone 1 and the oil storage tank 6 are arranged in a cavity formed by the wall surface 3 of the air inlet channel, the wall surface 4 of the combustion chamber and the wall surface 5 of the tail nozzle as a part; an air inlet channel 10 is formed between the splitter cone 1 and the wall surface 3 of the air inlet channel, a combustion chamber flow channel 8 is formed between the splitter cone 1 and the wall surface 4 of the combustion chamber, a tail nozzle flow channel 7 is formed between the splitter cone 1 and the wall surface 5 of the tail nozzle, and the air inlet channel 10, the combustion chamber flow channel 8 and the tail nozzle flow channel 7 are sequentially communicated; the top of the diffluence cone 1 is provided with an air inlet 2.
The flow distribution cone 1 comprises a cone wall 12 and a fuel atomizer 15; wherein, the tip of the conical wall 12 is provided with a plurality of air inlets 2; the interior of the conical wall 12 forms a gas collecting cavity 11; a fuel atomizer 15 is arranged inside the conical wall 12, the conical wall 12 is provided with a direct injection type spray hole 9 corresponding to the fuel atomizer 15, and the fuel atomizer 15 is communicated with the combustion chamber flow passage 8 through the direct injection type spray hole 9; the fuel atomizer 15 is connected to the oil reservoir 6 via an oil line 14.
Fig. 2 is a schematic structural diagram of a fuel atomizer provided in an embodiment of the present invention. As shown in fig. 2, the fuel atomizer 15 includes a plurality of laval nozzles 13; wherein, the number of the direct injection holes 9 is consistent with that 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 position of the center of a circle; each laval nozzle 13 is connected to a corresponding direct injection orifice 9.
The incoming air is rectified by the splitter cone 1 and then split and respectively enters the air inlet 2 and the air inlet channel 10; the air flow entering the air inlet 2 is decelerated and pressurized in the air collecting cavity 11, then enters the fuel oil atomizer 15, is accelerated again, fuel oil in the oil storage tank 6 enters the fuel oil atomizer 15 through the oil conveying pipe 14, is rapidly atomized by the air flow accelerated by the Laval nozzle 13, and then is injected into the combustion chamber runner 8 from the direct injection type spray hole 9; atomized fuel oil and air flow pressurized by the air inlet channel 10 are mixed and subjected to combustion reaction in the combustion chamber flow channel 8, and generated high-temperature and high-pressure fuel gas is sprayed out through the tail nozzle flow channel 7, so that the residence time of the fuel oil in the combustion chamber is greatly shortened, and the combustion efficiency and the combustion stability are improved.
Wherein the Mach number of an inlet of the air inlet channel 10 is 2-5, and the momentum ratio of fuel injected from the direct injection holes 9 to air in the combustion chamber flow channel 8 is 10-100; the ratio of the diameter phi a of the inlet channel to the outer diameter phi b of the tail nozzle casing is 0.5-0.8; the ratio of the length La of the intake passage to the length Lb of the combustion chamber is 0.65 to 0.95; the diameter ratio of the air inlet 2 to the direct injection orifice 9 is 5-10; the angle theta of the diversion cone is 15-30 degrees; the ratio of the inlet throat area Sa to the tail nozzle throat area Sb is 0.45-0.85.
As shown in fig. 2, the fuel atomizer 15 is composed of 6 laval nozzles 13.
As shown in FIG. 3, the ratio of the inlet diameter Phic of the Laval nozzle to the throat diameter Phid of the Laval nozzle is 1.5-2; the ratio of the length Lc of the Laval nozzle to the inlet diameter phi c of the Laval nozzle is 3.5-4.5; the ratio of the diameter phi e of the oil delivery pipe to the diameter phi d of the throat of the laval nozzle is 1-1.2, so that the liquid aviation kerosene can be atomized at high speed.
The air collection cavity is adopted to stagnate air to form high-pressure origin, the structure is simple, and incoming high-speed air can be fully utilized; in the embodiment, the Laval nozzle is adopted to atomize the liquid fuel at a high speed, so that the ignition delay time of the fuel and the residence time in a combustion chamber are greatly shortened; the embodiment adopts the direct injection type spray holes to inject the liquid aviation kerosene atomized in advance into the combustion chamber to participate in the combustion reaction, thereby improving the combustion efficiency and the combustion stability.
The above-described embodiments are merely preferred embodiments of the present invention, and general changes and substitutions by those skilled in the art within the technical scope of the present invention are included in the protection scope of the present invention.

Claims (9)

1. A ramjet engine for high-speed atomization of liquid aviation kerosene in advance is characterized by comprising: the device comprises a flow dividing cone (1), an air inlet channel wall surface (3), a combustion chamber wall surface (4), a tail nozzle wall surface (5), an oil storage tank (6) and an oil delivery pipe (14); wherein the content of the first and second substances,
the flow dividing cone (1) is connected with the oil storage tank (6) through the oil conveying pipe (14);
the wall surface (3) of the air inlet channel, the wall surface (4) of the combustion chamber and the wall surface (5) of the tail nozzle are sequentially connected;
the flow dividing cone (1) and the oil storage tank (6) are arranged in a cavity formed by the wall surface (3) of the air inlet channel, the wall surface (4) of the combustion chamber and the wall surface (5) of the tail nozzle as a part;
an air inlet channel (10) is formed between the flow distribution cone (1) and the air inlet channel wall surface (3), a combustion chamber flow channel (8) is formed between the flow distribution cone (1) and the combustion chamber wall surface (4), a tail nozzle flow channel (7) is formed between the flow distribution cone (1) and the tail nozzle wall surface (5), and the air inlet channel (10), the combustion chamber flow channel (8) and the tail nozzle flow channel (7) are sequentially communicated;
the top of the shunting cone (1) is provided with an air inlet (2); wherein the content of the first and second substances,
the flow dividing cone (1) comprises a cone wall (12) and a fuel atomizer (15); wherein the content of the first and second substances,
the tip part of the conical wall (12) is provided with a plurality of air inlets (2); the interior of the conical wall (12) forms a gas collecting cavity (11);
a fuel atomizer (15) is arranged inside the conical wall (12), the conical wall (12) is provided with a direct injection type spray hole (9) corresponding to the fuel atomizer (15), and the fuel atomizer (15) is communicated with the combustion chamber flow passage (8) through the direct injection type spray hole (9);
the fuel atomizer (15) is connected with the oil storage tank (6) through the oil conveying pipe (14).
2. The liquid jet fuel pre-high-speed atomized ramjet engine of claim 1, wherein: the fuel atomizer (15) comprises a plurality of Laval nozzles (13); wherein the content of the first and second substances,
the number of the direct injection holes (9) is consistent with that of the Laval nozzles (13);
each Laval nozzle (13) forms a circular radius, and one end of each Laval nozzle (13) is positioned at the position of the center of a circle;
each Laval nozzle (13) is connected with the corresponding direct injection hole (9).
3. The liquid jet fuel pre-high-speed atomized ramjet engine of claim 1, wherein: the Mach number of an inlet of the air inlet channel (10) is 2-5, and the momentum ratio of fuel injected from the direct injection type spray holes (9) to air in a combustion chamber flow channel (8) is 10-100.
4. The liquid jet fuel pre-high-speed atomized ramjet engine of claim 1, wherein: the ratio of the diameter phi a of the air inlet channel to the outer diameter phi b of the wall surface of the tail nozzle is 0.5-0.8; the ratio of the length La of the intake passage to the length Lb of the combustion chamber flow passage is 0.65 to 0.95.
5. The liquid jet fuel pre-high-speed atomized ramjet engine of claim 1, wherein: the diameter ratio of the air inlet (2) to the direct injection hole (9) is 5-10.
6. The liquid jet fuel pre-high-speed atomized ramjet engine of claim 1, wherein: the angle theta of the diversion cone is 15-30 degrees.
7. The liquid jet fuel pre-high-speed atomized ramjet engine of claim 1, wherein: the ratio of the inlet throat area Sa to the exhaust nozzle throat area Sb is 0.45-0.85.
8. The liquid jet fuel pre-high-speed atomized ramjet engine of claim 2, wherein: the ratio of the inlet diameter phi c of the Laval nozzle to the throat diameter phi d of the Laval nozzle is 1.5-2; the ratio of the length Lc of the Laval nozzle to the inlet diameter Phic of the Laval nozzle is 3.5-4.5.
9. The liquid jet fuel pre-high-speed atomized ramjet engine of claim 2, wherein: the ratio of the diameter phi e of the oil delivery pipe to the diameter phi d of the throat of the laval nozzle is 1-1.2.
CN201810502304.6A 2018-05-23 2018-05-23 Ramjet engine with liquid aviation kerosene atomized at high speed in advance Active CN108999726B (en)

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CN109595078A (en) * 2018-12-27 2019-04-09 中国人民解放军总参谋部第六十研究所 A kind of water injection structure for turbojet engine
CN113967806B (en) * 2021-10-28 2023-03-24 湖北三江航天江北机械工程有限公司 Welding deformation control method for large-size shunt cone

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CN101576025B (en) * 2009-06-11 2010-11-03 北京航空航天大学 Multi-mode spraying pipe with adjustable throat for ramjet engine
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CN205076051U (en) * 2015-05-26 2016-03-09 吴畏 Hypersonic vehicle
CN205449923U (en) * 2016-03-10 2016-08-10 北京理工大学 A combustion system for simulating punching press engine

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