CN114645799B - Axisymmetric full-speed-domain ramjet engine using electric auxiliary supercharging - Google Patents
Axisymmetric full-speed-domain ramjet engine using electric auxiliary supercharging Download PDFInfo
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- CN114645799B CN114645799B CN202210175965.9A CN202210175965A CN114645799B CN 114645799 B CN114645799 B CN 114645799B CN 202210175965 A CN202210175965 A CN 202210175965A CN 114645799 B CN114645799 B CN 114645799B
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- engine
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- air inlet
- speed
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 50
- 239000000446 fuel Substances 0.000 claims abstract description 31
- 239000007921 spray Substances 0.000 claims abstract description 19
- 239000003381 stabilizer Substances 0.000 claims abstract description 17
- 230000000087 stabilizing effect Effects 0.000 claims description 8
- 230000006835 compression Effects 0.000 description 7
- 238000007906 compression Methods 0.000 description 7
- 239000007789 gas Substances 0.000 description 5
- 238000002955 isolation Methods 0.000 description 3
- 102100040255 Tubulin-specific chaperone C Human genes 0.000 description 2
- 238000005516 engineering process Methods 0.000 description 2
- 108010093459 tubulin-specific chaperone C Proteins 0.000 description 2
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 108091053398 TRIM/RBCC family Proteins 0.000 description 1
- 102000011408 Tripartite Motif Proteins Human genes 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000002902 bimodal effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000009194 climbing Effects 0.000 description 1
- 238000010586 diagram Methods 0.000 description 1
- 230000005611 electricity Effects 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000002243 precursor Substances 0.000 description 1
- 230000002035 prolonged effect Effects 0.000 description 1
- 239000002918 waste heat Substances 0.000 description 1
Classifications
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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
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/06—Varying effective area of jet pipe or nozzle
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F02—COMBUSTION ENGINES; HOT-GAS OR COMBUSTION-PRODUCT ENGINE PLANTS
- F02K—JET-PROPULSION PLANTS
- F02K1/00—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto
- F02K1/36—Plants characterised by the form or arrangement of the jet pipe or nozzle; Jet pipes or nozzles peculiar thereto having an ejector
-
- 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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention provides an axisymmetric full-speed-domain ramjet engine using electric auxiliary supercharging, and belongs to the technical field of aerospace equipment. The problem that the high-speed requirement of an aircraft is difficult to meet by a traditional hybrid engine is solved. The engine comprises an air inlet passage center cone, an engine shell, fixed guide posts, a high-speed motor, an air compressor, fuel nozzles, a fuel stabilizer and a spray pipe, wherein the air inlet passage center cone is arranged inside the front end of the engine shell through the fixed guide posts, the high-speed motor is arranged inside the air inlet passage center cone, the air compressor is connected with the high-speed motor, the inside of the engine shell at the rear end of the air compressor is a combustion chamber, the number of the fuel nozzles is multiple, the fuel nozzles are uniformly distributed on the inner wall of the engine shell along the circumferential direction of an inlet of the combustion chamber, the number of the fuel stabilizers is multiple, the fuel stabilizers are uniformly distributed on the area, close to the center, of the combustion chamber along the circumferential direction of the inlet of the combustion chamber, and the rear end of the engine shell is connected with the spray pipe. It is mainly used for full-speed domain ramjet engines.
Description
Technical Field
The invention belongs to the technical field of aerospace equipment, and particularly relates to an axisymmetric full-speed domain ramjet engine using electric auxiliary supercharging.
Background
An aerospace vehicle with the horizontal take-off and landing capability is an important development direction of the future aerospace field, and one of key technologies of the aerospace vehicle with the horizontal take-off and landing capability is a wide-speed-domain engine capable of realizing Ma 0-6 < + > flight. The main problem faced by the current wide-range engine scheme is that the bimodal ramjet engine suitable for hypersonic flight cannot operate at a low Mach number, so that the wide-range engine is mostly combined in a combined power mode, and the combination of three power modes of a rocket engine, a turbine engine and a ramjet engine is mainly adopted. The rocket ramjet engine combined by the rocket and the ramjet engine has smaller specific impact at low Mach number and weak load capacity; the turbine ramjet engine has a complex structure, has strict technical requirements on the turbine engine, and has to adopt precooling and other modes to improve the operation Mach number of the turbine engine; the engine structure formed by the three engines is more complex, and the thrust-weight ratio is more difficult to meet the requirements of an aerospace vehicle.
With the development of high-energy density aviation battery and other technologies, hybrid power is gradually becoming a development direction of future aircraft with potential. The general hybrid electric system is roughly divided into a series hybrid electric system, a parallel hybrid electric system and a series-parallel hybrid electric system, has better specific impulse than a conventional internal combustion engine system, and has longer range, shorter charging time and smaller battery size compared with a pure electric system. The current mixing cases include DA 36E-Star 2 series type mixing aircraft of Siemens of Germany, song parallel type mixing aircraft developed based on Czech UL-2, cessna 337 modified by Ampaire of America, and parallel type mixing aircraft. However, the traditional hybrid engine is less affected by factors such as motor output power, battery size and the like, so that the requirement of the aircraft in high speed and even supersonic speed is difficult to meet.
Disclosure of Invention
In view of this, the present invention aims to propose an axisymmetric full-speed domain ramjet engine using electric auxiliary supercharging to solve the problem that the conventional hybrid engine is difficult to meet the high-speed requirement of an aircraft.
In order to achieve the above purpose, the present invention adopts the following technical scheme: the utility model provides an use motor-assisted supercharged axisymmetric full-speed domain ramjet, it includes intake duct center cone, engine housing, fixed guide post, high-speed motor, air compressor, fuel nozzle, steady combustor and spray tube, engine housing front end is the air inlet, the intake duct center cone passes through fixed guide post setting in the front end of engine housing inside, high-speed motor sets up in the inside of intake duct center cone, the air compressor links to each other with high-speed motor, through the work of high-speed motor drive air compressor, the engine housing inside of air compressor rear end is the combustion chamber, fuel nozzle quantity is a plurality of, and a plurality of fuel nozzle are along the combustion chamber entry circumferencial direction equipartition on the engine housing inner wall, steady combustor quantity is a plurality of, and a plurality of steady combustors are along the combustion chamber circumferencial direction equipartition on the region that the combustion chamber is close to the center, engine housing rear end links to each other with the spray tube.
Furthermore, the fixed guide post is of a hollow structure, a circuit is arranged in the hollow structure, and the high-speed motor is connected with an external power supply through the circuit.
Furthermore, the flame stabilizer is of a V-shaped flame stabilizing structure, a support plate flame stabilizing structure or a concave cavity flame stabilizing structure.
Still further, the fixed guide post is circumferentially disposed about the engine housing.
Furthermore, the center cone of the air inlet channel at the front end of the air compressor is of a contracted structure.
Further, the burner is arranged in the combustion chamber through a bracket.
Further, the spray pipe is of a Laval spray pipe structure.
Further, the spray pipe is a geometrically adjustable tail spray pipe.
Further, the combustion chamber is of an annular structure.
Further, the number of the fuel nozzles is 8-16, and the number of the stabilizators is 4-8.
Compared with the prior art, the invention has the beneficial effects that: the invention uses an electric auxiliary supercharging mode, the ramjet engine is used as an afterburner to provide thrust, the thrust of the engine can be ensured when Ma 0-3 is provided, compared with a TBCC and RBCC scheme, the specific impact of the engine at low Mach number can be effectively improved, and the oil consumption of the climbing acceleration section of the engine is reduced. When the speed is increased to Ma 2-3, the wide-range ramjet engine can work to Ma6 or even higher, waste heat can be used for generating electricity through an active heat protection scheme, and the heat protection performance is improved, and meanwhile, the electric power required by low Mach number is stored, so that the full-speed-range ramjet engine is an effective full-speed-range engine scheme.
The electric compressor is adopted to meet the pressure requirement of the inlet of the stamping combustion chamber, so that the stamping combustion chamber has good performance at low Mach number, and the task requirement of the horizontal take-off and landing of the aerospace vehicle is met. The air inlet is in a supersonic air inlet configuration, and the precursor extends out of the front end of the engine shell and has a variable geometry structure, so that the flight working conditions of Ma 2-6+ can be met; the electric compression system consists of a high-speed motor and a multi-stage compressor, is powered by an external battery, and uses the high-speed motor to drive the compressor to work; the combustion chamber is positioned behind the electric compression system and comprises an oil spray hole, an igniter, a flame stabilizer and the like; the variable tail nozzle may adjust the exit area based on changes in flight Mach number to provide optimum performance of the engine in the full speed regime.
The electric supercharging system used by the invention reduces the quality of the traditional combined engine, so that the thrust-weight ratio of the engine can be improved, and the size of the combined engine can be reduced. Meanwhile, by using an electric compression mode, the stamping combustion chamber can run at a low speed, and the working range of the stamping combustion chamber is widened. In addition, the battery is used for supplying energy to the supercharging part of the engine, so that the specific impulse of the engine can be effectively improved, the effective load of the aircraft can be improved, and the service life of the engine can be prolonged.
The invention can make the ramjet engine work in the mode of afterburner at low speed by means of electric supercharging. The length of the isolation section behind the air inlet channel is shorter, the total pressure loss is lower, and then the expansion mode is adopted, so that the incoming flow can be decelerated to subsonic speed, and the problem of insufficient compression capacity of the supersonic through-flow fan can be effectively avoided. Compared with a TBCC engine without a turbine component, the invention can effectively reduce the quality of the engine. The invention can reduce the carbon emission of the full-speed engine by using the hybrid power.
Drawings
The accompanying drawings, which are included to provide a further understanding of the invention and are incorporated in and constitute a part of this specification, illustrate embodiments of the invention and together with the description serve to explain the invention. In the drawings:
FIG. 1 is a schematic diagram of an axisymmetric full-speed domain ramjet engine using electric assist supercharging in accordance with the present invention;
FIG. 2 is a schematic view of the fuel nozzle and stabilizer position according to the present invention.
1-An air inlet channel center cone, 2-an engine shell, 3-a fixed guide post, 4-a high-speed motor, 5-a gas compressor, 6-a fuel nozzle, 7-a combustion stabilizer and 8-a spray pipe.
Detailed Description
The technical solutions in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It should be noted that, in the case of no conflict, embodiments of the present invention and features of the embodiments may be combined with each other, and the described embodiments are only some embodiments of the present invention, not all embodiments.
Referring to fig. 1-2, the embodiment is described as an axisymmetric full-speed-range ramjet engine using electric auxiliary supercharging, which comprises an air inlet passage center cone 1, an engine housing 2, a fixed guide post 3, a high-speed motor 4, a gas compressor 5, fuel nozzles 6, a flame stabilizer 7 and a spray pipe 8, wherein the front end of the engine housing 2 is an air inlet, the air inlet passage center cone 1 is arranged in the front end of the engine housing 2 through the fixed guide post 3, the high-speed motor 4 is arranged in the air inlet passage center cone 1, the gas compressor 5 is connected with the high-speed motor 4, the gas compressor 5 is driven to work through the high-speed motor 4, a combustion chamber is arranged in the engine housing 2 at the rear end of the gas compressor 5, a plurality of fuel nozzles 6 are uniformly distributed on the inner wall of the engine housing 2 along the circumferential direction of the inlet of the combustion chamber, a plurality of flame stabilizers 7 are uniformly distributed on the area, close to the center, of the combustion chamber along the circumferential direction of the inlet of the combustion chamber, and the rear end of the engine housing 2 is connected with the spray pipe 8.
The fixed guide post 3 is of a hollow structure, a circuit is arranged in the hollow structure, the high-speed motor 4 is connected with an external power supply through the circuit, the high-speed motor 4 is powered through the external power supply, and the fixed guide post 3 is circumferentially arranged around the engine housing 2. The combustion chamber is of an annular structure, and a stable combustion mode can be selected according to the specific configuration and size of the engine, such as a V-shaped stable combustion structure, a support plate stable combustion structure or a concave cavity stable combustion structure.
When the flight Mach number is low, an external power supply supplies power to the high-speed motor 4 through a circuit in the hollow fixed guide column 3, and the high-speed motor 4 drives the air compressor 5 to work, so that the inlet of the combustion chamber has a certain pressure rise. The center cone 1 of the air inlet channel at the front end of the air compressor 5 is of a contracted structure so as to ensure that the sectional area of the flow channel is increased, and the incoming air is decelerated to subsonic speed before the air compressor 5, so that the normal operation of the air compressor 5 is ensured. If a high-power high-speed motor 4 is used, the compressor 5 provides a higher pressure ratio, and the compressor 5 can be used as a high-speed ducted fan to provide thrust. If the fan driven by the high speed motor 4 does not provide sufficient thrust, the combustion chamber operates to provide additional thrust. The fuel nozzle 6 injects fuel into the combustion chamber around the engine at the front end of the punched passage. The stabilizer 7 is placed at the rear side of the fuel nozzle 6, and penetrates into the combustion chamber through the bracket as compared with the fuel nozzle 6. An alternative combustion chamber configuration is shown in fig. 2, in which fuel is injected from the outer wall into the combustion chamber, and fuel is injected into the combustion chamber from a fuel nozzle 6, and part of the fuel can also be injected into the combustion chamber through a stabilizer 7 to ensure sufficient combustion. The number of the fuel nozzles and the stables are arranged according to the scale of the combustion chamber of the engine, preferably, the number of the fuel nozzles 6 is 8-16, and the number of the stables 7 is 4-8. The spray pipe 8 is of a Laval spray pipe structure.
As the flight mach number increases, the motor-driven compressor 5 provides sufficient pressure rise to decrease as the forward flow velocity of the compressor 5 increases. At the moment, the air inlet central cone 1 is used as a compression surface, the front end of the engine shell 2 is used as a lip, and the supersonic air inlet is formed. At which point the fan may continue to operate to reduce drag, the engine generally operating as a wide area ramjet engine. The expansion of the front flow passage sectional area of the combustion chamber is larger, so that the Mach number in the ram combustion chamber in a wide Mach number range can be ensured to be subsonic. The nozzle 8 of the engine may preferably be a geometrically adjustable tail nozzle to ensure that the engine has sufficient thrust over a wide speed range.
When the high Mach number operates, the high-speed motor stops working outwards, and at the moment, the blades of the compressor 5 operate in a windmill state. Because the flow passage in front of the combustion chamber adopts an expansion structure, the air speed in front of the blades of the air compressor 5 can be reduced to subsonic speed, so that the energy loss caused by the idling of the blades of the air compressor 5 is lower, and the ram combustion chamber works as a scramjet combustion chamber at the moment. If the engine adopts an equal-straight isolation section configuration, a supersonic through-flow fan can be selected to be used as a compression component, and blades are arranged in the isolation section, so that supersonic operation is ensured when the air passes through the compression system in high Mach number flight, and the combustion chamber works as a scramjet combustion chamber.
The embodiments of the invention disclosed above are intended only to help illustrate the invention. The examples are not intended to be exhaustive or to limit the invention to the precise forms disclosed. Many modifications and variations are possible in light of the above teaching. The embodiments were chosen and described in order to best explain the principles of the invention and the practical application, to thereby enable others skilled in the art to best understand and utilize the invention.
Claims (9)
1. An axisymmetric full speed domain ramjet engine using electric assist supercharging, characterized by: the engine comprises an air inlet channel center cone (1), an engine shell (2), a fixed guide post (3), a high-speed motor (4), a gas compressor (5), fuel nozzles (6), a plurality of fuel stabilizer (7) and a spray pipe (8), wherein the front end of the engine shell (2) is an air inlet, the air inlet channel center cone (1) is arranged in the front end of the engine shell (2) through the fixed guide post (3), the high-speed motor (4) is arranged in the air inlet channel center cone (1), the gas compressor (5) is connected with the high-speed motor (4), the gas compressor (5) is driven by the high-speed motor (4) to work, the interior of the engine shell (2) at the rear end of the gas compressor (5) is provided with a combustion chamber, the number of the fuel nozzles (6) is a plurality of the fuel stabilizer (6) are uniformly distributed on the inner wall of the engine shell (2) along the circumferential direction of the inlet of the combustion chamber, the number of the fuel stabilizer (7) is a plurality of the fuel stabilizer (7) are uniformly distributed on the inner wall of the engine shell (2) along the circumferential direction of the inlet of the combustion chamber, the combustion chamber in the area close to the center, the shell (2) is connected with the front end of the engine shell (8) as the front end of the engine shell (1) is in the shape of the front end of the air inlet channel, the front end of the gas compressor (5) is connected with the front end of the engine shell (1) as the front end of the air inlet pump (1) is in the front end of the engine shell (1), the flow passage in front of the combustion chamber adopts an expansion structure.
2. An axisymmetric full speed domain ramjet engine using electric assist supercharging according to claim 1, characterized in that: the fixed guide post (3) is of a hollow structure, a circuit is arranged in the hollow structure, and the high-speed motor (4) is connected with an external power supply through the circuit.
3. An axisymmetric full speed domain ramjet engine using electric assist supercharging according to claim 1, characterized in that: the flame stabilizer (7) is of a V-shaped flame stabilizing structure, a support plate flame stabilizing structure or a concave cavity flame stabilizing structure.
4. An axisymmetric full speed domain ramjet engine using electric assist supercharging according to claim 1, characterized in that: the fixed guide posts (3) are circumferentially arranged around the engine housing (2).
5. An axisymmetric full speed domain ramjet engine using electric assist supercharging according to claim 1, characterized in that: the stabilizer (7) is arranged in the combustion chamber through a bracket.
6. An axisymmetric full speed domain ramjet engine using electric assist supercharging according to claim 1, characterized in that: the spray pipe (8) is of a Laval spray pipe structure.
7. An axisymmetric full speed domain ramjet engine using electric assist supercharging according to claim 1, characterized in that: the spray pipe (8) is a geometrically adjustable tail spray pipe.
8. An axisymmetric full speed domain ramjet engine using electric assist supercharging according to claim 1, characterized in that: the combustion chamber is of an annular structure.
9. An axisymmetric full speed domain ramjet engine using electric assist supercharging according to claim 1, characterized in that: the number of the fuel nozzles (6) is 8-16, and the number of the stabilizators (7) is 4-8.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210175965.9A CN114645799B (en) | 2022-02-24 | 2022-02-24 | Axisymmetric full-speed-domain ramjet engine using electric auxiliary supercharging |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210175965.9A CN114645799B (en) | 2022-02-24 | 2022-02-24 | Axisymmetric full-speed-domain ramjet engine using electric auxiliary supercharging |
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| Publication Number | Publication Date |
|---|---|
| CN114645799A CN114645799A (en) | 2022-06-21 |
| CN114645799B true CN114645799B (en) | 2024-04-26 |
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| CN202210175965.9A Active CN114645799B (en) | 2022-02-24 | 2022-02-24 | Axisymmetric full-speed-domain ramjet engine using electric auxiliary supercharging |
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| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB861101A (en) * | 1957-09-03 | 1961-02-15 | United Aircraft Corp | Combination power plant for an aircraft |
| US3719428A (en) * | 1969-03-14 | 1973-03-06 | W Dettmering | Jet engine for hypersonic intake velocities |
| US4730453A (en) * | 1985-10-23 | 1988-03-15 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Afterburner fuel injection system |
| US5685142A (en) * | 1996-04-10 | 1997-11-11 | United Technologies Corporation | Gas turbine engine afterburner |
| JPH1068357A (en) * | 1996-08-28 | 1998-03-10 | Ishikawajima Harima Heavy Ind Co Ltd | High speed aircraft |
| DE10115766A1 (en) * | 2001-03-29 | 2002-10-17 | Wiese Guenter Klotz | Thrust generator, for a glider or jet models, has a drive motor within the inner zone of the housing to be coupled to the turbine compressor, in a simple structure which can be controlled easily |
| CN101725431A (en) * | 2008-10-31 | 2010-06-09 | 南昌航空大学 | Electric fuel oil jet propeller |
| CN103807052A (en) * | 2014-03-10 | 2014-05-21 | 邱世军 | Electric drive jet engine |
| TW201738457A (en) * | 2016-04-18 | 2017-11-01 | 李晉毅 | Air turbine rocket engine and operating method thereof |
| RU2647919C1 (en) * | 2016-06-20 | 2018-03-21 | Владимир Леонидович Письменный | Ramjet engine |
| CN108800205A (en) * | 2018-04-24 | 2018-11-13 | 南京航空航天大学 | A kind of eddy flow reinforcing/stamping combustion chamber |
| EP3985241A1 (en) * | 2020-10-14 | 2022-04-20 | Taiwan Innovative Space, Inc. | Motor and fuel-powered hybrid system for a rocket thruster |
-
2022
- 2022-02-24 CN CN202210175965.9A patent/CN114645799B/en active Active
Patent Citations (12)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| GB861101A (en) * | 1957-09-03 | 1961-02-15 | United Aircraft Corp | Combination power plant for an aircraft |
| US3719428A (en) * | 1969-03-14 | 1973-03-06 | W Dettmering | Jet engine for hypersonic intake velocities |
| US4730453A (en) * | 1985-10-23 | 1988-03-15 | Societe Nationale D'etude Et De Construction De Moteurs D'aviation "S.N.E.C.M.A." | Afterburner fuel injection system |
| US5685142A (en) * | 1996-04-10 | 1997-11-11 | United Technologies Corporation | Gas turbine engine afterburner |
| JPH1068357A (en) * | 1996-08-28 | 1998-03-10 | Ishikawajima Harima Heavy Ind Co Ltd | High speed aircraft |
| DE10115766A1 (en) * | 2001-03-29 | 2002-10-17 | Wiese Guenter Klotz | Thrust generator, for a glider or jet models, has a drive motor within the inner zone of the housing to be coupled to the turbine compressor, in a simple structure which can be controlled easily |
| CN101725431A (en) * | 2008-10-31 | 2010-06-09 | 南昌航空大学 | Electric fuel oil jet propeller |
| CN103807052A (en) * | 2014-03-10 | 2014-05-21 | 邱世军 | Electric drive jet engine |
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| Publication number | Publication date |
|---|---|
| CN114645799A (en) | 2022-06-21 |
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