CN114790955A - Hybrid power engine capable of realizing oil-electricity range extension - Google Patents
Hybrid power engine capable of realizing oil-electricity range extension Download PDFInfo
- Publication number
- CN114790955A CN114790955A CN202210487093.XA CN202210487093A CN114790955A CN 114790955 A CN114790955 A CN 114790955A CN 202210487093 A CN202210487093 A CN 202210487093A CN 114790955 A CN114790955 A CN 114790955A
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- China
- Prior art keywords
- oil
- range extension
- engine capable
- realizing
- electricity range
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- 239000007921 spray Substances 0.000 claims description 20
- 238000002485 combustion reaction Methods 0.000 claims description 19
- 238000002955 isolation Methods 0.000 claims description 12
- 239000002184 metal Substances 0.000 claims description 10
- 238000002347 injection Methods 0.000 claims description 4
- 239000007924 injection Substances 0.000 claims description 4
- 239000003921 oil Substances 0.000 claims 7
- 238000005507 spraying Methods 0.000 claims 2
- 238000000889 atomisation Methods 0.000 claims 1
- 230000005611 electricity Effects 0.000 claims 1
- 239000000295 fuel oil Substances 0.000 claims 1
- 238000004134 energy conservation Methods 0.000 abstract description 3
- 239000003344 environmental pollutant Substances 0.000 abstract description 3
- 231100000719 pollutant Toxicity 0.000 abstract description 3
- 230000007547 defect Effects 0.000 abstract description 2
- 238000004519 manufacturing process Methods 0.000 abstract description 2
- 239000000446 fuel Substances 0.000 description 6
- 230000000694 effects Effects 0.000 description 3
- 238000005516 engineering process Methods 0.000 description 3
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 1
- 230000001133 acceleration Effects 0.000 description 1
- 239000000654 additive Substances 0.000 description 1
- 230000000996 additive effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 229910052799 carbon Inorganic materials 0.000 description 1
- 230000008602 contraction Effects 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 230000007613 environmental effect Effects 0.000 description 1
- 239000002737 fuel gas Substances 0.000 description 1
- 239000007789 gas Substances 0.000 description 1
- 239000000463 material Substances 0.000 description 1
Images
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
Landscapes
- Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Nozzles (AREA)
Abstract
The invention discloses a hybrid power engine capable of realizing oil-electricity range extension, which relates to a hybrid power engine and aims to overcome the defects of the two engines and realize the purposes of oil-electricity range extension, energy conservation and emission reduction. The invention has simple structure, convenient assembly and disassembly, reduces pollutant discharge, increases the thrust of the engine and reduces the production cost. The invention relates to the technical field of aircraft engines.
Description
Technical Field
The invention relates to a hybrid power engine, in particular to a hybrid power engine which is applicable to small and medium-sized aircrafts with low Mach numbers and can realize oil-electricity range extension, and relates to the technical field of aircraft engines.
Background
In the current background, the airplane develops towards low carbon and environmental protection. The pure electric aircraft uses a ducted fan, a propeller and the like as a thrust device, but the thrust is often insufficient due to the factors of low energy density of a battery and the like. The turbojet engine can provide larger thrust, but a turbine in the turbojet engine is limited by materials and cooling technology, so that the turbojet engine is lower in heat efficiency, larger in oil consumption and more in discharge, and does not meet the requirements of energy conservation and emission reduction. In order to reduce pollutant emission, increase engine thrust and reduce production cost, a hybrid engine capable of realizing oil-electricity range extension needs to be developed based on two engine technologies.
Disclosure of Invention
The invention aims to overcome the defects of the two engines and achieve the purposes of oil-electricity range extension, energy conservation and emission reduction, and further provides a hybrid engine capable of achieving the oil-electricity range extension.
The technical scheme adopted by the invention for solving the problems is as follows:
the invention comprises an air inlet channel, a ducted fan assembly, an isolation section, a combustion chamber and a tail spray pipe, wherein the ducted fan assembly comprises a metal ducted barrel, fan blades, a main shaft and a motor, the air inlet channel, the metal ducted barrel, the isolation section, the combustion chamber and the tail spray pipe are sequentially connected from left to right, the fan blades are installed in the metal ducted barrel, and the motor is connected with the fan blades through the main shaft.
Furthermore, the outer contour of the isolation section is gradually expanded from right to left.
Furthermore, the combustion chamber is the cylinder, and the front end of combustion chamber is equipped with a plurality of oil spout pipes, and a plurality of oil spout pipes set up along the circumferencial direction equipartition.
Further, each oil spray pipe is provided with a plurality of atomized oil spray holes.
Further, the oil injection pipe is supplied with oil by an external fuel system.
Furthermore, the outer contour of the tail nozzle gradually tapers from left to right.
The invention has the beneficial effects that:
1. the invention has simple structure and convenient assembly and disassembly, does not have complex parts such as a turbine, a rotating shaft and the like, and reduces the weight;
2. the ducted fan provides thrust and compresses incoming flow; the arrangement of the isolation section can reduce the interference of the combustion chamber on the front end;
3. the combustion chamber is atomized by the additive of the oil spray pipe, so that the combustion is sufficient, larger energy is released, high-temperature and high-pressure fuel gas is generated and is sprayed out through the tail spray pipe, and the functions of increasing force and range are achieved;
4. the fan is driven by the motor to replace a mode of jointly working of the compressor and the turbine, the starting is convenient, the rotating speed of the motor and whether the combustion chamber works or not can be adjusted according to needs, the pollutant emission is reduced, and the energy-saving and environment-friendly effects are achieved.
Drawings
FIG. 1 is a schematic view of the overall structure of the present invention
In the figure: 1-air inlet channel, 2-metal culvert barrel, 3-fan, 4-main shaft, 5-motor, 6-isolation section, 7-combustion chamber, 8-oil spray pipe and 9-tail spray pipe.
Detailed Description
The first embodiment is as follows: the embodiment is described with reference to fig. 1, and the hybrid engine capable of realizing the oil-electricity range extension in the embodiment comprises an air inlet 1, a ducted fan assembly, an isolation section 6, a combustion chamber 7 and a tail spray pipe 9, wherein the ducted fan assembly comprises a metal ducted bucket 2, fan blades 3, a main shaft 4 and a motor 5, the air inlet 1, the isolation section 6 of the metal ducted bucket 2, the combustion chamber 7 and the tail spray pipe 9 are sequentially connected from left to right, the fan 3 is installed in the metal ducted bucket 2, the motor 5 is connected with the fan blades 3 through the main shaft 4, the fan blades are driven to rotate by the motor, and the motor is powered by an external power supply through a line.
The second embodiment is as follows: the present embodiment is described with reference to fig. 1, and the outer contour of the isolation section 6 in the present embodiment gradually expands from right to left.
The design of the isolation section 6 predicts the fan outlet pressure P according to reference data given by the merchant e ＝F/A e . To achieve taperingThe maximum acceleration effect of the spray pipe is assumed that the outlet of the spray pipe is in a critical state, and the flow velocity of the air flow is Mach 1. The nozzle contraction section is designed under the condition, the gradually-reduced nozzle is designed based on the Victoria-Sinkiang curve, and the nozzle gradually-reduced section meeting a certain condition is obtained through a 3D drawing and printing technology.
Other components are connected in the same manner as in the second embodiment.
The third concrete implementation mode: referring to fig. 1, the combustion chamber 7 of the present embodiment is a cylindrical body, and a plurality of oil spray pipes 8 are provided at the front end of the combustion chamber 7, and the oil spray pipes 8 are arranged uniformly in the circumferential direction.
Other components are connected in the same manner as in the first or second embodiment.
The fourth concrete implementation mode: the present embodiment is described with reference to fig. 1, and each of the fuel spray pipes 8 of the present embodiment is provided with a plurality of atomized fuel spray holes.
Other components and connection relationships are the same as those in the first, second or third embodiment.
The fifth concrete implementation mode: the present embodiment is described with reference to fig. 1, and the fuel injection pipe 8 of the present embodiment is supplied with fuel from an external fuel system.
Other components and connections are the same as those of the first, second, third or fourth embodiments.
The sixth specific implementation mode is as follows: the present embodiment is described with reference to fig. 1, and the outer contour of the jet pipe 9 of the present embodiment is gradually tapered from left to right. The tail nozzle 9 is a convergent nozzle, so that the outlet condition of the tail nozzle is close to the critical state.
Other components and connection relationships are the same as those in the first, second, third, fourth or fifth embodiment.
The working principle is as follows:
the air flow enters the engine through an air inlet 1 and is compressed; the ducted fan blades 3 are driven by the motor 5 to rotate, apply work to the incoming flow and expand the pressure, so that thrust is generated, and air is further compressed; the rotating speed of the motor 5 can be adjusted according to the working requirement, so that the current flying speed is adapted. When the thrust is sufficient, the combustion chamber 7 does not work, and only the fan generates the thrust; when the required thrust is insufficient, the oil injection pipe 8 injects oil, the combustion chamber 7 ignites and combusts to release energy, high-temperature and high-pressure gas is generated and is discharged through the tail nozzle 9, and the effect of increasing the thrust and the stroke is achieved.
Although the present invention has been described with reference to the preferred embodiments, it will be understood by those skilled in the art that various changes may be made and equivalents may be substituted for elements thereof without departing from the scope of the present invention.
Claims (6)
1. The utility model provides a can realize hybrid engine of oil electricity increase journey which characterized in that: the hybrid power engine capable of realizing the oil-electricity range extension comprises an air inlet duct (1), a ducted fan assembly, an isolation section (6), a combustion chamber (7) and a tail spray pipe (9), wherein the ducted fan assembly comprises a metal ducted bucket (2), fan blades (3), a main shaft (4) and a motor (5), the air inlet duct (1), the metal ducted bucket (2), the isolation section (6), the combustion chamber (7) and the tail spray pipe (9) are sequentially connected from left to right, the fan blades (3) are installed in the metal ducted bucket (2), and the motor (5) is connected with the fan blades (3) through the main shaft (4).
2. The hybrid engine capable of realizing the oil-electricity range extension according to claim 1, characterized in that: the outer contour of the isolation section (6) is gradually expanded from right to left.
3. The hybrid engine capable of realizing the oil-electricity range extension according to claim 1, characterized in that: the combustion chamber (7) is a cylinder, a plurality of oil spraying pipes (8) are arranged at the front end of the combustion chamber (7), and the oil spraying pipes (8) are uniformly distributed along the circumferential direction.
4. The hybrid engine capable of realizing the oil-electricity range extension according to claim 3, characterized in that: each oil spray pipe (8) is provided with a plurality of atomization oil spray holes.
5. The hybrid engine capable of realizing the oil-electricity range extension according to claim 4, is characterized in that: the oil injection pipe (8) is supplied with oil by an external fuel oil system.
6. The hybrid engine capable of realizing the oil-electricity range extension according to claim 1, characterized in that: the outer contour of the tail nozzle (9) is gradually reduced from left to right.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210487093.XA CN114790955A (en) | 2022-05-06 | 2022-05-06 | Hybrid power engine capable of realizing oil-electricity range extension |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN202210487093.XA CN114790955A (en) | 2022-05-06 | 2022-05-06 | Hybrid power engine capable of realizing oil-electricity range extension |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN114790955A true CN114790955A (en) | 2022-07-26 |
Family
ID=82461280
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN202210487093.XA Pending CN114790955A (en) | 2022-05-06 | 2022-05-06 | Hybrid power engine capable of realizing oil-electricity range extension |
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| Country | Link |
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| CN (1) | CN114790955A (en) |
Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101649781A (en) * | 2008-08-11 | 2010-02-17 | 刘佳骏 | Jet engine |
| CN101725431A (en) * | 2008-10-31 | 2010-06-09 | 南昌航空大学 | Electric fuel oil jet propeller |
| CN101975121A (en) * | 2010-10-19 | 2011-02-16 | 靳北彪 | Culvert sleeved turbojet engine |
| CN102146858A (en) * | 2010-08-12 | 2011-08-10 | 靳北彪 | Stamping engine for pneumatic turbine |
| CN104251168A (en) * | 2013-06-25 | 2014-12-31 | 杨家雄 | Electric air injection jet engine |
| CN204511702U (en) * | 2015-01-23 | 2015-07-29 | 何涛 | A kind of ducted fan motor afterburning with burning |
| CN107842442A (en) * | 2017-11-10 | 2018-03-27 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of aero-engine |
-
2022
- 2022-05-06 CN CN202210487093.XA patent/CN114790955A/en active Pending
Patent Citations (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN101649781A (en) * | 2008-08-11 | 2010-02-17 | 刘佳骏 | Jet engine |
| CN101725431A (en) * | 2008-10-31 | 2010-06-09 | 南昌航空大学 | Electric fuel oil jet propeller |
| CN102146858A (en) * | 2010-08-12 | 2011-08-10 | 靳北彪 | Stamping engine for pneumatic turbine |
| CN101975121A (en) * | 2010-10-19 | 2011-02-16 | 靳北彪 | Culvert sleeved turbojet engine |
| CN104251168A (en) * | 2013-06-25 | 2014-12-31 | 杨家雄 | Electric air injection jet engine |
| CN204511702U (en) * | 2015-01-23 | 2015-07-29 | 何涛 | A kind of ducted fan motor afterburning with burning |
| CN107842442A (en) * | 2017-11-10 | 2018-03-27 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of aero-engine |
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