CN108757221A - A kind of liquid Asia burning ramjet - Google Patents
A kind of liquid Asia burning ramjet Download PDFInfo
- Publication number
- CN108757221A CN108757221A CN201810535728.2A CN201810535728A CN108757221A CN 108757221 A CN108757221 A CN 108757221A CN 201810535728 A CN201810535728 A CN 201810535728A CN 108757221 A CN108757221 A CN 108757221A
- Authority
- CN
- China
- Prior art keywords
- cone
- air intake
- intake duct
- combustion chamber
- liquid
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
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Classifications
-
- 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
- F02K7/14—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 with external combustion, e.g. scram-jet engines
-
- 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
-
- 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
- F02C7/042—Air intakes for gas-turbine plants or jet-propulsion plants having variable geometry
-
- 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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- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Physics & Mathematics (AREA)
- Geometry (AREA)
- Fuel-Injection Apparatus (AREA)
Abstract
The invention discloses a kind of liquid Asia burning ramjets, center cone 1 including two-stage cone structure, two-stage cone structure includes the conehead part with the first cone angle and the cone body part being connect with conehead part with the second cone angle, first cone angle is less than the second cone angle, and the shell of air intake duct 2 stretches into 3 certain distance S of combustion chamber, and injection loop 4 is located at the outside for the shell that air intake duct 2 stretches into combustion chamber 3.Incoming first passes around the compression of two-stage center cone, pressure is big at inlet mouth, speed is low, continue supercharging of slowing down in air intake duct converging duct, one of faint normal shock wave is generated near inlet throat, it is subsonic flow after wave, in the combustion chamber, the fuel that injection loop ejects is under the isolation of air intake duct, it is not affected by the influence of incoming, it burns with incoming blending at downstream, stable flame can be formed, generate larger thrust, the present invention has total pressure recovery coefficient high, it is simple in structure, combustion flame stablize, thrust it is big the advantages that.
Description
Technical field
The invention belongs to technical field of engines, more particularly to a kind of liquid Asia burning ramjet.
Background technology
Ram-air jet engine, abbreviation punching engine are that one kind is suitble in supersonic and hypersonic aircraft
On the airbreathing motor that uses, mainly by Supersonic Inlet, combustion chamber, convergence expansion jet pipe and fuel feed system etc.
It constitutes.
When punching engine works, high-speed flow realizes supercharging of slowing down in air intake duct by shock wave compression, completes mine-laying
Working medium pressurization in thermodynamic cycle, compressed air enter combustion chamber and burn to form high-temperature high-pressure fuel gas with fuel blending,
Combustion gas through tail dispute tube swelling accelerate, thermal energy be kinetic energy while, utilize reaction force principle generate thrust.It is sprayed with turbine
Gas engine is compared, and punching engine realizes supercharging under high-speed flight state, using the pneumatic principle of shock wave compression, to not
The components such as compressor, turbine are needed again, also eliminate limitation of the rotation hot-end component to incoming total temperature and ignition temperature, therefore it
It can work under higher Mach number, more heats can also be added and generate the thrust per frontal area of bigger.It is sent out with rocket
Motivation is compared, and since punching engine is not required to carry oxidant, specific impulse can be improved 4~6 times, be more suitable for remote flight.It is special
It is not Liquid fuel ramjet engine, because oxidant is entirely from air, specific impulse is sent out compared with the solid punching press for carrying oxygen deprivation solid fuel
Motivation higher.
Due to punching engine have simple in structure, thrust-weight ratio it is big, than leaping high, and adapt in atmosphere and near space
In spatial domain the characteristics of supersonic flight, research has obtained lasting concern.By the unremitting effort in a century, punching press is started
Machine technology has been realized in extensive engineer application.Currently, punching engine is increasingly becoming after liquid-propellant rocket engine, solid fire
Most important Space Dynamic's technology after arrow engine, is in the application extension phase of rapid development.But existing punching press hair
The center cone of motivation largely only has level-one centrum, namely is fixed cone angle respectively after boring preceding and cone, leads to air inlet in this way
Road total pressure recovery coefficient is not high enough, while the general fuel in combustion chamber of existing punching engine in the combustion chamber spray by portion, adopts
Stablize flame with internal flame stabilizer, cause so complicated, it is not high enough that fuel and air blend insufficient thrust.
Invention content
The main object of the present invention is in view of the above problems, to provide a kind of liquid Asia burning ramjet, this hair
It is bright that there is the advantages that simple in structure, inlet total pres sure recovery coefficient is high, and flow velocity is low in combustion chamber, and thrust is big.
Realize that the technical solution of the object of the invention is：A kind of liquid Asia burning ramjet, including center cone, air inlet
Road, combustion chamber and injection loop, the center cone include precentrum and posterior pyramids, which is characterized in that the precentrum stretches out air inlet
The part in road includes two-stage cone structure, and the two-stage cone structure includes conehead part with the first cone angle and with second
The cone body part of cone angle being connect with conehead part, first cone angle be less than the second cone angle, and the air intake duct with it is described
Combustion chamber is connected, and the shell of the air intake duct stretches into combustion chamber certain distance S, and the injection loop is located at air intake duct and stretches into burning
The outside of indoor shell.
Preferably, described to connect at the maximum cross-section bored centered on the connection transition position of the precentrum and posterior pyramids
Place is crossed to be located in the air intake duct.
Preferably, ranging from 10.8 °~11.2 ° of first cone angle, ranging from 13.5 °~14 ° of second cone angle.
Preferably, the axial length of the conehead part is 6.1~6.4cm, and the axial length of the cone body part is
10.1~10.2cm.
Preferably, the circumferential direction of the injection loop is uniformly provided with multiple nozzle openings.
Preferably, the distance S is 3~5cm.
The invention has the advantages that：
(1) bipyramid air intake duct is used, and meets best wave system theory between two-stage cone, maximum total pressure recovery system can be obtained
Number；
(2) air intake structure is made of center cone and air intake duct, and fuel is ejected by injection loop, simple in structure to be illustrated, cost
It is low；
(3) thrust is big, and air intake duct expansion pipe stretches into 3~5cm of combustion chamber, which mixes with incoming fills
Point, the thrust of flame stabilization, generation of burning is big.
Other than objects, features and advantages described above, the present invention also has other objects, features and advantages.
Below with reference to figure, the present invention is described in further detail.
Description of the drawings
Fig. 1 is dimensional structure diagram of the present invention.
Fig. 2 is sectional view of the present invention.
Fig. 3 is injection loop structural schematic diagram of the present invention.
Specific implementation mode
In order to be better understood by the technology contents of the present invention, spy lifts specific embodiment and institute's attached drawing is coordinated to be described as follows.
In conjunction with Fig. 1-2, a kind of liquid Asia burning ramjet, including center cone 1, air intake duct 2, combustion chamber 3 and injection loop
4, the center cone 1 includes precentrum and posterior pyramids, and the part that the precentrum stretches out air intake duct 2 includes two-stage cone structure,
The two-stage body structure includes the conehead part with the first cone angle and the cone body being connect with conehead part with the second cone angle
Part, first cone angle is less than the second cone angle, and the air intake duct 2 is connected with the combustion chamber 3, the air intake duct 2
Shell stretch into 3 certain distance S of combustion chamber, the injection loop 4 is located at the outside for the shell that air intake duct 2 stretches into combustion chamber 3.
Incoming is pressurized by the deceleration of two-stage center cone, enters air intake duct with low speed, one is generated near inlet throat
The faint normal shock wave in road, then enters combustion chamber with subsonic speed, and air intake duct expansion pipe will stretch into 3~5cm of combustion chamber.Combustion chamber
Arrangement has multiple apertures in spray ring, is fired for spraying there are one round spray ring (i.e. injection loop 4) between 3 shells and air intake duct 2
Material, air intake duct stretch into part and have effectively completely cut off influence of the incoming to fuel injection, and in the combustion chamber, incoming is fired with fuel blending
It burns, larger thrust can be improved.
Center cone is divided into two-stage, and the angle of wherein first order conehead part and second level cone body part meets best wave system and manages
By, it is 3.6~4.4 to choose free stream Mach number, by experimental verification it can be found that first order cone angle chooses 10.8 °~11.2 °, the
Two level cone angle chooses 13.5 °~14 ° and the total pressure recovery coefficient more optimized can be achieved (specific experiment certificate parameter is referring to table 1).
By advanced optimizing, it is found that first order cone length chooses 6.1~6.4cm, second level cone length preferably chooses 10.1~10.2cm
The total pressure recovery coefficient more optimized can be obtained (specific experiment certificate parameter is referring to table 2).Incoming increases by the deceleration of two-stage cone
Pressure, becomes the supersonic speed of a little higher than velocity of sound in inlet.Inside air intake duct, before venturi, continue to subtract by Contraction Ducts
Speed supercharging, a faint normal shock wave is generated near venturi, speed is down to the velocity of sound or subsonic speed, in expansion pipe later
In road, continue to slow down, be minimized in air intake port section.δ in table 1,21Indicate the first cone angle of center cone, δ2Expression center
The second cone angle is bored, σ indicates total pressure recovery coefficient, L1Indicate that the first order bores axial length, L2Indicate that axial length, Ma are bored in the second level
Indicate free stream Mach number.
Total pressure recovery coefficient comparison (taking Ma=4) in the case of 1 different cone angle of table
Total pressure recovery coefficient compares in the case of 2 different Mach number of table, axially different length
The chamber structure, it is preferred that emphasis is air intake duct and combustion chamber coupling part, the expansion pipe of air intake duct stretch into combustion
Chamber interior certain distance S is burnt, the general fuel in available engine combustion chamber in the combustion chamber spray by portion, using internal flame stabilizer
Stablize flame, fuel and incoming can be isolated in the present invention so that incoming is more fully mixed with fuel, and flame is more stable.In order to obtain
The scheme more optimized is obtained, it is larger to can be found that when that distance S is chosen for 3-5cm can obtain by the experiment parameter of table 3
Thrust, take Ma=4, δ in table 31=10.8 °, δ2=13.8 °, nozzle throat area takes 0.0025m2。
3 air intake duct of table stretches into the thrust comparison of combustion chamber different length
The foregoing is only a preferred embodiment of the present invention, is not intended to restrict the invention, for the skill of this field
For art personnel, the invention may be variously modified and varied.All within the spirits and principles of the present invention, any made by repair
Change, equivalent replacement, improvement etc., should all be included in the protection scope of the present invention.
Claims (7)
1. a kind of liquid Asia burning ramjet, including center cone (1), air intake duct (2), combustion chamber (3) and injection loop (4), institute
It includes precentrum and posterior pyramids to state center cone (1), which is characterized in that the part that the precentrum stretches out air intake duct (2) includes two
Grade cone structure, the two-stage cone structure include conehead part with the first cone angle and with the second cone angle and cone head part
The cone body part of connection, first cone angle is divided to be less than the second cone angle, and the air intake duct (2) and the combustion chamber (3) phase
Connection, the shell of the air intake duct (2) stretch into combustion chamber (3) certain distance S, and the injection loop (4) is located at air intake duct (2) and stretches into
The outside of shell in combustion chamber (3).
2. liquid Asia according to claim 1 burning ramjet, which is characterized in that the company of the precentrum and posterior pyramids
It connects centered on transition position at the maximum cross-section of cone (1), it is interior that the connection transition position is located at the air intake duct (2).
3. liquid Asia according to claim 1 burning ramjet, which is characterized in that first cone angle is ranging from
10.8 °~11.2 °, ranging from 13.5 °~14 ° of second cone angle.
4. liquid Asia according to claim 3 burning ramjet, which is characterized in that the axial length of the conehead part
Axial length for 6.1~6.4cm, the cone body part is 10.1~10.2cm.
5. liquid Asia according to claim 1 burning ramjet, which is characterized in that the circumferential direction of the injection loop (4) is
It is even to offer multiple nozzle openings.
6. liquid Asia according to claim 5 burning ramjet, which is characterized in that the oil spout hole number is 8.
7. according to claim 1-6 any one of them liquid Asia burning ramjet, which is characterized in that the distance S be 3~
5cm。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810535728.2A CN108757221A (en) | 2018-05-30 | 2018-05-30 | A kind of liquid Asia burning ramjet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810535728.2A CN108757221A (en) | 2018-05-30 | 2018-05-30 | A kind of liquid Asia burning ramjet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN108757221A true CN108757221A (en) | 2018-11-06 |
Family
ID=64003913
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810535728.2A Pending CN108757221A (en) | 2018-05-30 | 2018-05-30 | A kind of liquid Asia burning ramjet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN108757221A (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111023150A (en) * | 2019-12-11 | 2020-04-17 | 中国空气动力研究与发展中心 | Extension plate for combustion chamber |
| CN112081685A (en) * | 2020-08-12 | 2020-12-15 | 南京理工大学 | Liquid ramjet based on disc-shaped rotary detonation combustion chamber |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5148673A (en) * | 1989-10-24 | 1992-09-22 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Integrated turboramjet engine |
| CN104110325A (en) * | 2014-07-30 | 2014-10-22 | 清华大学 | Combined cycle engine |
| CN104481700A (en) * | 2014-09-25 | 2015-04-01 | 南京航空航天大学 | Combined dynamic axisymmetric variable geometry inlet, engine and air inlet control method |
| CN105257429A (en) * | 2015-11-30 | 2016-01-20 | 清华大学 | Combined type rocket engine |
| JP2016133025A (en) * | 2015-01-18 | 2016-07-25 | 白川 利久 | Booster-less ramjet engine |
| CN205746973U (en) * | 2016-05-09 | 2016-11-30 | 南京航空航天大学 | A kind of scramjet engine combustor |
| CN107504517A (en) * | 2017-08-15 | 2017-12-22 | 南京航空航天大学 | A kind of step center cone with circumferentially staggered terrace with edge |
-
2018
- 2018-05-30 CN CN201810535728.2A patent/CN108757221A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US5148673A (en) * | 1989-10-24 | 1992-09-22 | Mtu Motoren- Und Turbinen-Union Munchen Gmbh | Integrated turboramjet engine |
| CN104110325A (en) * | 2014-07-30 | 2014-10-22 | 清华大学 | Combined cycle engine |
| CN104481700A (en) * | 2014-09-25 | 2015-04-01 | 南京航空航天大学 | Combined dynamic axisymmetric variable geometry inlet, engine and air inlet control method |
| JP2016133025A (en) * | 2015-01-18 | 2016-07-25 | 白川 利久 | Booster-less ramjet engine |
| CN105257429A (en) * | 2015-11-30 | 2016-01-20 | 清华大学 | Combined type rocket engine |
| CN205746973U (en) * | 2016-05-09 | 2016-11-30 | 南京航空航天大学 | A kind of scramjet engine combustor |
| CN107504517A (en) * | 2017-08-15 | 2017-12-22 | 南京航空航天大学 | A kind of step center cone with circumferentially staggered terrace with edge |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN111023150A (en) * | 2019-12-11 | 2020-04-17 | 中国空气动力研究与发展中心 | Extension plate for combustion chamber |
| CN111023150B (en) * | 2019-12-11 | 2021-07-27 | 中国空气动力研究与发展中心 | Extension plate for combustion chamber |
| CN112081685A (en) * | 2020-08-12 | 2020-12-15 | 南京理工大学 | Liquid ramjet based on disc-shaped rotary detonation combustion chamber |
| CN112081685B (en) * | 2020-08-12 | 2022-02-01 | 南京理工大学 | Liquid ramjet based on disc-shaped rotary detonation combustion chamber |
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Application publication date: 20181106 |