CN111663969B - Liquid fuel air-breathing type stamping rotary detonation engine shell structure - Google Patents
Liquid fuel air-breathing type stamping rotary detonation engine shell structure Download PDFInfo
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- CN111663969B CN111663969B CN202010513299.6A CN202010513299A CN111663969B CN 111663969 B CN111663969 B CN 111663969B CN 202010513299 A CN202010513299 A CN 202010513299A CN 111663969 B CN111663969 B CN 111663969B
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D25/00—Component parts, details, or accessories, not provided for in, or of interest apart from, other groups
- F01D25/24—Casings; Casing parts, e.g. diaphragms, casing fastenings
- F01D25/26—Double casings; Measures against temperature strain in casings
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/04—Air intakes for gas-turbine plants or jet-propulsion plants
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02C—GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS
- F02C7/00—Features, components parts, details or accessories, not provided for in, or of interest apart form groups F02C1/00 - F02C6/00; Air intakes for jet-propulsion plants
- F02C7/22—Fuel supply systems
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K7/00—Plants 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
- F02K7/10—Plants 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
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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles For Spraying Of Liquid Fuel (AREA)
Abstract
The invention relates to an air-breathing engine adopting liquid fuel, in particular to a shell structure of an air-breathing ramjet rotary detonation engine adopting liquid fuel. The invention aims to solve the technical problem that the prior art is difficult to atomize and evaporate quickly, and provides a shell structure of a liquid fuel air-breathing type stamping rotary detonation engine. The structure comprises an engine outer shell and a premixed gas shell assembly, wherein the premixed gas shell assembly comprises an air inlet cone, an isolating section central body and a combustion chamber central body; the central body of the isolating section is connected with the engine outer shell through a main support rod; the air inlet cone is connected with the central body of the isolating section through the front support rod, and a slit-shaped air inlet channel is formed between the air inlet cone and the central body of the isolating section; the central body of the combustion chamber is connected with the central body of the separation section through a rear supporting rod, and a slit-shaped injection channel is formed between the central body of the combustion chamber and the central body of the separation section; a fuel tank and a nozzle are arranged in the air inlet cone; a mixing chamber is arranged in the center body of the isolating section and is communicated with the nozzle.
Description
Technical Field
The invention relates to an air-breathing engine adopting liquid fuel, in particular to an air-breathing stamping rotary detonation engine shell structure adopting liquid fuel.
Background
The rotary detonation combustion is different from the isobaric combustion widely applied to the current engine, is essentially supersonic combustion, realizes a process of extremely fast chemical reaction with lower entropy increase, and has the advantages of high energy release rate (approximate isochoric combustion), high thermodynamic cycle efficiency and the like. In addition, because the detonation wave has the self-supercharging property, a certain combustion supercharging ratio can be realized, and a power system based on detonation combustion can save complex supercharging components and simplify the system structure of the engine. In recent years, rotary detonation engines are becoming a focus of research in the field of aerospace power.
The combustion chamber of the rotary detonation engine is generally of an annular structure, detonation waves are transmitted in the annular combustion chamber in a rotating mode along the circumferential direction, high-temperature and high-pressure fuel gas is exhausted from the tail portion of the engine along the axial direction after being expanded through a spray pipe, and continuous thrust is generated. Such an engine has the following potential advantages: 1) the thermal cycle efficiency is high; 2) the structure is simple, the weight is light, the thrust-weight ratio is large, and the specific impact is high; 3) the unit fuel consumption rate is low; 4) the working range is wide, and the thrust adjusting range is wide. Therefore, the rotary detonation engine has wide application prospect.
The rotary detonation engine mainly has two working modes, namely a rocket mode and a punching mode, and respectively corresponds to the rocket engine and the air-breathing punching engine. The current general view of the academia is that an air breathing ramjet rotary detonation engine is probably the earliest form of detonation engine used.
At present, an air-suction type stamping rotary knocking engine is still in a principle research stage in the world and does not enter an application stage, most of the research is carried out on gaseous fuel, the research on a liquid fuel air-suction type stamping rotary knocking engine is less, and the published information is not much.
In engineering applications, the engine requires the use of liquid fuel due to space and structural size constraints. In liquid fuel rotary detonation engines, because the detonation combustion rate is extremely fast, it is desirable that the droplets atomize, evaporate quickly and uniformly over a short distance, and mix with the oxidizer quickly and uniformly, a process that has a large impact on the successful initiation and stable operation of the rotary detonation wave.
Because air is much less chemically reactive (i.e., combustion-supporting) than oxygen, it is difficult to achieve rapid atomization and vaporization of liquid fuels, especially for low volatility fuels such as aviation kerosene, which has a relatively long time to atomize and vaporize, and thus, in an induction engine using liquid fuels, it is difficult to achieve rotary detonation combustion.
Disclosure of Invention
The invention aims to solve the technical problem that the prior art is difficult to atomize and evaporate quickly, and provides a shell structure of a liquid fuel air-breathing type stamping rotary detonation engine.
In order to solve the technical problems, the technical solution provided by the invention is as follows:
a liquid fuel air-breathing type stamping rotary detonation engine shell structure is characterized in that: the engine comprises an engine outer shell and a premixed gas shell component arranged in the engine outer shell;
the premix gas shell assembly comprises an air inlet cone, an isolating section central body and a combustion chamber central body;
the isolating section central body is connected with the engine outer shell through a plurality of main support rods which are circumferentially arranged along the outer side face of the isolating section central body;
the air inlet cone is connected with the central body of the isolating section through a plurality of front supporting rods arranged along the same circumference on the rear end surface of the air inlet cone, and a slit-shaped air inlet channel is formed between the air inlet cone and the central body of the isolating section;
the combustion chamber central body is connected with the separation section central body through a plurality of rear support rods arranged along the same circumference on the front end surface of the combustion chamber central body, and a slit-shaped injection channel is formed between the combustion chamber central body and the separation section central body;
the air inlet cone is internally provided with a fuel tank and a nozzle communicated with the fuel tank;
a mixing chamber which penetrates through the front end surface and the rear end surface is arranged in the central body of the isolating section and is communicated with the nozzle;
the space between the engine outer shell and the premixed gas shell assembly is divided into a front part and a rear part by taking the plane of the main support rods as a boundary, the part close to one side of an air inlet cone is an air inlet channel, the part close to one side of a central body of a combustion chamber is a rotary detonation combustion chamber, and the air inlet channel and the rotary detonation combustion chamber form an air flow channel I;
and an air flow channel II is formed by the annular seam-shaped air inlet channel, the mixing chamber and the annular seam-shaped injection channel in the premixed air shell component.
Furthermore, in order to control the mixed air flow entering the air flow channel I, the mixing chamber adopts a convergent-divergent structure, and the narrowest part of the mixing chamber is used as a throat of the air flow channel II.
Further, the nozzle is a centrifugal nozzle.
Further, in order to guarantee reliability and facilitate processing, the engine outer shell, the air inlet cone, the separation section central body and the combustion chamber central body are integrally formed through welding or integrally formed through 3D printing.
Further, in order to effectively control the fuel flow rate entering the mixing chamber, a delivery pump for controlling the fuel flow rate is connected between the fuel tank and the nozzle.
Furthermore, the diameter of the throat of the air flow channel II is 6-10 mm.
Further, in order to effectively control the air amount entering the mixing chamber, the inlet width of the annular slit-shaped air inlet channel is 2-4 mm.
Compared with the prior art, the invention has the following beneficial effects:
according to the liquid fuel air-breathing type stamping rotary detonation engine shell structure provided by the invention, a small amount of air enters the mixing chamber through the annular-seam-shaped air inlet channel, is mixed with fuel sprayed by the fuel spray nozzle to form uniform mixed gas, is sprayed into the rotary detonation combustion chamber through the annular-seam-shaped spraying channel in the radial direction, is mixed with main air flowing into the rotary detonation combustion chamber through the air inlet channel to generate rotary detonation combustion, and is discharged from the rotary detonation combustion chamber in the axial direction to generate thrust. By adopting the shell structure, partial air and fuel can be atomized and mixed in advance, the mixing process of premixed gas sprayed by the annular-slit-shaped injection channel and main stream air from the air inlet channel is similar to gas-gas mixing, the atomization and evaporation processes of liquid fuel are accelerated, the detonation difficulty is reduced, the preparation time of rotary detonation combustion is shortened, the liquid fuel is atomized and evaporated within a short time and distance and is mixed with air, rotary detonation combustion within a wide Mach number range is realized, the detonation difficulty of detonation waves in a rotary detonation combustion chamber is greatly reduced, the detonation combustion effect is enhanced, the thrust performance of an engine is improved, and the axial length of the engine is shortened.
Drawings
FIG. 1 is a two-dimensional cross-sectional view of a liquid fuel aspirated ramjet rotary detonation engine housing structure of the present invention;
description of reference numerals:
1-an engine outer casing, 2-a premix gas casing assembly;
21-an air inlet cone, 22-an isolation section central body, 23-a combustion chamber central body, 24-a main support rod, 25-a front support rod, 26-a circular seam-shaped air inlet channel, 27-a rear support rod and 28-a circular seam-shaped injection channel;
211-fuel tank, 212-nozzle;
221-a mixing chamber;
11-inlet duct, 12-rotary detonation combustor.
Detailed Description
The invention will be further described with reference to the accompanying drawings.
The invention provides a liquid fuel air-breathing type stamping rotary detonation engine shell structure which can stably work in a wide Mach number range (0.3-5), has short axial dimension and high specific impact performance, and mainly comprises an air inlet cone 21, an isolation section central body 22, a combustion chamber central body 23 and an engine outer shell 1, wherein the four parts can be welded to form a whole or integrally formed by 3D printing, as shown in figure 1.
The intake cone 21 and the separation section central body 22 are connected through a plurality of circumferentially arranged front support rods 25, the separation section central body 22 and the combustion chamber central body 23 are connected through a plurality of circumferentially arranged rear support rods 27, and the engine outer body 1 and the separation section central body 22 are connected through a plurality of circumferentially arranged main support rods 24. The air inlet cone 21 is provided with a fuel tank 211 and a nozzle 212 (the fuel tank 211 is used for containing aviation kerosene, the nozzle 212 is an oil nozzle), a slit-shaped air inlet channel 26 is arranged between the air inlet cone 21 and the separation section central body 22, a mixing chamber 221 penetrating through the front end surface and the rear end surface is arranged in the separation section central body 22, and a slit-shaped injection channel 28 is arranged between the separation section central body 22 and the combustion chamber central body 23.
The shell structure is provided with two air flow channels, wherein the air flow channel I consists of an air inlet 11 and a rotary detonation combustor 12, and the air flow accounts for 90% -95% of the total air flow; the air flow channel II consists of a circular seam-shaped air inlet channel 26, a mixing chamber 221 and a circular seam-shaped injection channel 28, the air flow accounts for 5% -10% of the total air flow, namely the air quantity introduced by the circular seam-shaped air inlet channel 26 accounts for 5% -10% of the total air quantity flowing in through the air inlet 11, and the tempering is not easy to occur because the equivalence ratio of fuel and air mixture in the mixing chamber 221 deviates from the chemical right far.
Part (namely a small amount) of air enters the mixing chamber 221 through the annular seam-shaped air inlet channel 26, is mixed with fuel sprayed by an oil nozzle to form uniform premixed air, is sprayed into the rotary detonation combustion chamber 12 through the annular seam-shaped injection channel 28 in the radial direction, is mixed with main flow air flowing into the rotary detonation combustion chamber 12 through the air inlet 11 to generate rotary detonation combustion, and combustion products are discharged from the rotary detonation combustion chamber 12 in the axial direction to generate thrust. The method has the advantages that partial air and fuel are atomized and mixed in advance (namely air in the air flow channel II acts on liquid fuel), the preparation time of rotary detonation combustion can be shortened, the detonation combustion effect is enhanced, the performance of an engine is improved, the axial length of the engine is shortened, and due to the fact that the premixed gas sprayed out of the annular-seam-shaped injection channel 28 and the main flow air from the air inlet 11 are mixed in a gas-gas mixing process in a similar mode, the premixed gas and the main flow air can be mixed uniformly and quickly in a short distance, and the length of a detonation combustion chamber can be effectively shortened.
And the liquid fuel is subjected to auxiliary atomization by utilizing air in the air flow channel II, so that the atomization difficulty is reduced, the requirements on the oil injection pressure and the injection structure are reduced, and an oil supply system can be simplified. The air flow channel II is provided with a throat (namely, the narrowest part of the mixing chamber 221), the air flow rate in the air flow channel II can be changed by adjusting the size of the throat, and the throat can inhibit the pressure in the rotary detonation combustion chamber 12 from being reversely transmitted upstream through the air flow channel II. The total incoming flow temperature of the air-breathing engine is high, air in the air flow channel II can also heat liquid fuel, the evaporation process is accelerated, and the detonation difficulty in the rotary detonation combustor 12 is reduced.
According to the liquid fuel air-breathing type stamping rotary detonation engine shell structure, the working Mach number of the engine is 0.3-5, and because detonation combustion has a self-supercharging characteristic, high thrust performance can be generated under the condition of low total pressure at the inlet of a combustion chamber, so that the liquid fuel air-breathing type stamping rotary detonation engine shell structure can operate under the condition of low Mach number when working in a stamping mode. In addition, because the detonation combustion rate is fast, the rotary detonation combustion can still be organized under the condition of high combustor inlet flow velocity, and the incoming flow Mach number can be higher than the Mach number upper limit of the traditional sub-combustion ramjet engine. The liquid fuel sprayed from the nozzle 212 is cut and atomized by a small amount of incoming high-speed air introduced through the annular slit-shaped air inlet channel 26, and under the action of pneumatic power, the liquid fuel is quickly atomized in the mixing chamber 221 and is uniformly mixed with air, which is beneficial to shortening the preparation time of detonation combustion. The total temperature of the incoming air is high, the liquid fuel is partially premixed in the mixing chamber 221 and the annular slot-shaped injection channel 28, and the liquid fuel can increase the temperature through mixing, so that the evaporation process is accelerated.
A delivery pump (which can be externally connected or internally arranged) for controlling the fuel flow is connected between the fuel tank 211 and the nozzle 212; alternatively, nitrogen gas is filled into the fuel tank 211 to control the pressure in the fuel tank 211 and control the fuel flow rate.
The technical principle of the invention is as follows:
aiming at the problem that the mixture of the liquid fuel and the air is difficult to detonate, a small amount of air is introduced from the incoming air to assist in atomizing the liquid fuel, liquid drops are broken easily under the action of pneumatic force, the incoming air is mixed with the liquid fuel and heats the liquid fuel, the evaporation process of the liquid fuel can be accelerated, the atomization and evaporation time of the liquid fuel is shortened, the liquid fuel is basically atomized and evaporated completely before entering the rotary detonation combustion chamber 12, and the detonation difficulty of detonation waves in the rotary detonation combustion chamber 12 is greatly reduced.
Examples
A liquid fuel air-breathing type punching rotary knocking engine shell structure comprises an air inlet cone 21, a separation section central body 22, a combustion chamber central body 23 and an engine outer shell 1. The intake cone 21 and the center body 22 of the separation section are connected by four front support rods 25 arranged circumferentially, the center body 22 of the separation section and the center body 23 of the combustion chamber are connected by four rear support rods 27 arranged circumferentially, and the engine outer body 1 and the center body 22 of the separation section are connected by four main support rods 24 arranged circumferentially. The air inlet cone 21 is provided with an oil tank and an oil nozzle, a slit-shaped air inlet channel 26 is arranged between the air inlet cone 21 and the central body 22 of the separation section, a mixing chamber 221 is arranged in the central body 22 of the separation section, and a slit-shaped injection channel 28 is arranged between the central body 22 of the separation section and the central body 23 of the combustion chamber.
The incoming flow air flow is 1.2-1.5 kg/s, the flight Mach number is 4, the total incoming flow air pressure is 0.8MPa, the total incoming flow air temperature is 900K, the liquid fuel adopts aviation kerosene, and the kerosene flow is 80-100 g/s.
Kerosene is conveyed to an oil nozzle through an oil supply pump, the oil nozzle is a centrifugal nozzle, the width of an inlet of a circular seam-shaped air inlet channel 26 is 2-4 mm, the air entraining amount is 80-100 g/s, the equivalence ratio of an oil-gas mixture in a mixing chamber 221 is less than 0.1, the mixing chamber 221 is of a convergent-divergent structure, the diameter of a throat (namely a throat) of the mixing chamber 221 is 6-10 mm, and the air entraining amount is adjusted by changing the size of the throat of the mixing chamber 221.
The centrifugal oil nozzle atomizes the kerosene into small droplets with the average particle size of below 100 microns and sprays the small droplets into the mixing chamber 221, high-temperature air with the total temperature of 900k enters the mixing chamber 221 through the annular seam-shaped air inlet channel 26, the air carries out auxiliary atomization on the droplets, the droplets are broken into smaller droplets, the temperature of the droplets is rapidly increased under the surrounding of the high-temperature air, and a large number of droplets are evaporated into kerosene vapor. The kerosene droplets are substantially completely evaporated before the mixture of high temperature air and kerosene droplets is injected into the rotary detonation combustor 12 through the annular slot-shaped injection channel 28, forming a homogeneous mixture in the gas phase having a total temperature of about 600K. Therefore, the rotary detonation combustion of approximately gas-phase kerosene and air occurs in the rotary detonation combustor 12, the required mixing time is short, the mixing distance is short, the axial length is shortened, and the detonation difficulty is greatly reduced.
The above description and the accompanying drawings of the present embodiment represent a preferred embodiment of the present invention, and the implementation can adjust parameters such as the amount of auxiliary atomized bleed air, the structural form of the fuel injector, and the fuel injection flow rate according to the flight conditions and working conditions of the engine, and can select a suitable liquid fuel according to the application requirements, that is, this embodiment is only used to illustrate the technical solution of the present invention, but not to limit it, and it will be obvious to those skilled in the art that modifications can be made to the specific technical solutions described in the foregoing embodiments, or equivalent substitutions can be made to some technical features thereof, and these modifications or substitutions do not make the essence of the corresponding technical solution depart from the scope of the technical solution protected by the present invention.
Claims (7)
1. The utility model provides a liquid fuel air-breathing formula punching press rotation detonation engine shell structure which characterized in that: the device comprises an engine outer shell (1) and a premixed gas shell component (2) arranged in the engine outer shell (1);
the premixed gas shell assembly (2) comprises an air inlet cone (21), an isolation section central body (22) and a combustion chamber central body (23);
the center body (22) of the isolating section is connected with the engine outer shell (1) through a plurality of main support rods (24) which are circumferentially arranged along the outer side face of the center body (22) of the isolating section;
the air inlet cone (21) is connected with the central body (22) of the isolating section through a plurality of front support rods (25) which are arranged on the rear end face of the air inlet cone (21) along the same circumference, and a slit-shaped air inlet channel (26) is formed between the air inlet cone (21) and the central body (22) of the isolating section;
the combustion chamber central body (23) is connected with the separation section central body (22) through a plurality of rear support rods (27) which are arranged along the same circumference on the front end surface of the combustion chamber central body (23), and a slit-shaped injection channel (28) is formed between the combustion chamber central body (23) and the separation section central body (22);
the air inlet cone (21) is internally provided with a fuel tank (211) and a nozzle (212) communicated with the fuel tank (211);
a mixing chamber (221) which penetrates through the front end face and the rear end face is arranged in the central body (22) of the isolating section, and the mixing chamber (221) is communicated with the nozzle (212);
the space between the engine outer shell (1) and the premixed gas shell assembly (2) is divided into a front part and a rear part by taking the plane of the main support rods (24) as a boundary, the part close to one side of the air inlet cone (21) is an air inlet channel (11), the part close to one side of a central body (23) of the combustion chamber is a rotary detonation combustion chamber (12), and the air inlet channel (11) and the rotary detonation combustion chamber (12) form an air flow channel I;
and an air channel II is formed by the annular seam-shaped air inlet channel (26), the mixing chamber (221) and the annular seam-shaped injection channel (28) in the premix gas shell component (2).
2. The liquid fuel aspirated ramjet rotary detonation engine casing structure of claim 1, wherein: the mixing chamber (221) adopts a convergent-divergent structure, and the narrowest part of the mixing chamber is used as a throat of the air flow channel II.
3. The liquid fuel aspirated ramjet rotary detonation engine casing structure of claim 1, wherein: the nozzle (212) adopts a centrifugal nozzle.
4. A liquid fuel-breathing ramjet rotary detonation engine casing structure according to any one of claims 1 to 3, characterised in that: the engine outer shell (1), the air inlet cone (21), the separation section central body (22) and the combustion chamber central body (23) are welded to form a whole, or are integrally formed through 3D printing.
5. The liquid fuel aspirated ramjet rotary detonation engine casing structure of claim 4, wherein: a delivery pump for controlling the fuel flow is connected between the fuel tank (211) and the nozzle (212).
6. The liquid fuel aspirated ramjet rotary detonation engine casing structure of claim 2, characterized in that: the diameter of the throat of the air flow channel II is 6-10 mm.
7. The liquid fuel aspirated ramjet rotary detonation engine casing structure of claim 6, wherein: the inlet width of the annular slit-shaped air inlet channel (26) is 2-4 mm.
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202010513299.6A CN111663969B (en) | 2020-06-08 | 2020-06-08 | Liquid fuel air-breathing type stamping rotary detonation engine shell structure |
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| CN202010513299.6A CN111663969B (en) | 2020-06-08 | 2020-06-08 | Liquid fuel air-breathing type stamping rotary detonation engine shell structure |
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| CN111663969B true CN111663969B (en) | 2022-04-12 |
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| CN112325332B (en) * | 2020-10-13 | 2021-07-27 | 南京航空航天大学 | Partial premixing and pre-evaporation double-channel injection device for rotary detonation engine |
Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3608582A1 (en) * | 1986-03-14 | 1987-09-17 | Gerhard Nerenberg | Device for driving an aircraft |
| CN101776027A (en) * | 2010-03-04 | 2010-07-14 | 北京大学 | Air suction type liquid fuel pulse detonation engine |
| CN104110325A (en) * | 2014-07-30 | 2014-10-22 | 清华大学 | Combined cycle engine |
| CN104929809A (en) * | 2015-06-04 | 2015-09-23 | 杜善骥 | Working method of detonation ram rocket |
| CN106170616A (en) * | 2014-03-28 | 2016-11-30 | 布兰特·W-T·李 | Electromotor, biomass powder energy conversion and/or generate system, hybrid engine, and production and preparation method thereof |
| CN109458271A (en) * | 2018-11-07 | 2019-03-12 | 厦门大学 | A kind of rotation detonation engine air intake duct and jet pipe integrated design method |
-
2020
- 2020-06-08 CN CN202010513299.6A patent/CN111663969B/en active Active
Patent Citations (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| DE3608582A1 (en) * | 1986-03-14 | 1987-09-17 | Gerhard Nerenberg | Device for driving an aircraft |
| CN101776027A (en) * | 2010-03-04 | 2010-07-14 | 北京大学 | Air suction type liquid fuel pulse detonation engine |
| CN106170616A (en) * | 2014-03-28 | 2016-11-30 | 布兰特·W-T·李 | Electromotor, biomass powder energy conversion and/or generate system, hybrid engine, and production and preparation method thereof |
| CN104110325A (en) * | 2014-07-30 | 2014-10-22 | 清华大学 | Combined cycle engine |
| CN104929809A (en) * | 2015-06-04 | 2015-09-23 | 杜善骥 | Working method of detonation ram rocket |
| CN109458271A (en) * | 2018-11-07 | 2019-03-12 | 厦门大学 | A kind of rotation detonation engine air intake duct and jet pipe integrated design method |
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