CN101725431A - Electric fuel oil jet propeller - Google Patents
Electric fuel oil jet propeller Download PDFInfo
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- CN101725431A CN101725431A CN200810107322A CN200810107322A CN101725431A CN 101725431 A CN101725431 A CN 101725431A CN 200810107322 A CN200810107322 A CN 200810107322A CN 200810107322 A CN200810107322 A CN 200810107322A CN 101725431 A CN101725431 A CN 101725431A
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- fuel oil
- firing chamber
- oil jet
- electric fuel
- duct casing
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Abstract
The invention discloses an electric fuel oil jet propeller which comprises an air inlet, a fan, a motor, an air deflector, a combustion chamber and a tailpipe with the thrust of 1-50kg. The electric fuel oil jet propeller is characterized in that fan blades are fixed on a fan hub which is fixed on an outer rotor direct-current motor rotor; the motor is fixed on an air deflector inner support ring through a bolt; an air deflector outer ring is embedded on the inner wall of a ducted casing; a heat insulation shield is arranged at the rear end of the air deflector inner support ring; the combustion chamber is arranged at the middle-rear end of the ducted casing; a pneumatic fuel oil nozzle ring is arranged at the front section of the combustion chamber and communicated with an oil pipeline; a falcate flame stabilizer is arranged at the rear end of the pneumatic fuel oil nozzle ring; an igniter is arranged at the rear end of the falcate flame stabilizer, passes through the combustion chamber and the ducted casing and is fixed on the outer wall surface of the ducted casing; and the inner wall of the ducted casing adopts a heat insulation coating. The propeller can be used as main power of small and middle size delivery tools and has simple structure, small size, light weight and large working thrust.
Description
Technical field
The present invention relates to a kind of propulsion device, more particularly be meant a kind of electric fuel oil jet propeller.
Background technique
Along with the continuous development of Aircraft Design manufacturing technology, its advancing means is had higher requirement.Be that propulsive efficiency or economic performance have all risen to higher requirement.The large and medium-sized aero-jet engine that picture is common, the technical difficulty height, complex structure, difficulty of processing is big, and the cost of production height is difficult to come into the market with cheap price.And electronic ducted fan motor is because it is simple in structure, easy processing, cost of production is low, under the drive of high energy density cells development, electronic ducted fan motor is applied on the miniature self-service aircraft as main power source morely, but present electronic ducted fan efficiency of engine is still lower, and the thrust of generation is smaller, is difficult to use on the large-size aircraft.
Summary of the invention
The purpose of this invention is to provide a kind of electric fuel oil jet propeller, can be used as the active force of the various middle-size and small-size unmanned launch vehicles that move on aviation and the earth surface, or as the large-scale auxiliary power unit that has on people, the unmanned launch vehicle.This propeller structure is simple, volume is little, in light weight, working thrust is big.
Electric fuel oil jet propeller of the present invention, comprise intake duct, fan, motor, fluid director, firing chamber, jet pipe, its fan blade 4 is fixed on the fan hub 3, fan hub 3 is fixed on external rotor direct current generator 2 rotors by the spiral heat dissipation fin supporting of its inner chamber, and described motor 2 is by being bolted on fluid director 5 inside support rings; Fluid director 5 outer shrouds are embedded on duct casing 1 interior walls; Thermal shield is installed in fluid director 5 inside support ring rear ends; Firing chamber 7 is installed in the middle rear end of duct casing 1, and firing chamber 7 leading portions are bearing in duct casing 1 interior walls intermediate portion, and 7 rear ends, firing chamber are bearing in position, duct casing 1 interior walls rear end; Firing chamber 7 leading portions are installed a pneumatic fuel nozzle ring 8, and pneumatic fuel nozzle ring 8 communicates with transport pipe 9; Transport pipe 9 passes duct casing 1 and is connected with outer oil circuit; Crescent moon flame holder 12 is arranged in a distance, pneumatic fuel nozzle ring 8 back, is bearing on burning cavity two walls of firing chamber 7; Igniter 10 is placed in a distance, crescent moon flame holder 12 rear end, passes firing chamber 7 and duct casing 1 and is fixed on duct casing 1 outer wall.
Described electric fuel oil jet propeller, its this angle of rake thrust is 1～50kg.
Described electric fuel oil jet propeller, duct casing 1 inner bore cavity of its fluid director 5 rear sections and firing chamber 7 leading portions form an expansion cavity.
Described electric fuel oil jet propeller, its firing chamber 7 are the firing chamber of the equal perforate of inside and outside wall of one similar " M " type profile shape, firing chamber 7 front-end faces and inside and outside wall rounding off, and air-flow is little along the wall flow losses.
Described electric fuel oil jet propeller, its fan hub 3 is the cavity of a front end perforate, and cavity inner wall circumferentially is covered with spiral heat dissipation fin 11, these fins serve as the function of simple centrifugal blower fan during rotation; Thermal shield 6 is the cone-shaped hood of a wall perforate, and is heat insulation to external rotor direct current generator 2.
Described electric fuel oil jet propeller, its pneumatic fuel nozzle ring 8 is a whole oil nozzle, and general shape is a similar cylindrical toroidal, and the mist of oil of ejection is central column in 7 chambeies, firing chamber.
The advantage that the present invention has:
1, with respect to large-scale, medium-sized, small-sized aviation turbojet engine usually, this propulsion device has saved hot-end components such as turbine, nozzle ring, directly by motor-driven fan work, and many oil circuits and control mechanism parts have been saved, make that it is simple in structure, volume is little, in light weight, thereby can improve this angle of rake thrust weight ratio, reduce processing and manufacturing difficulty, improve Economy.
2, compare with electronic ducted fan motor, propulsion device of the present invention can increase by 30%～～60% thrust under the supply of equal electric energy.
3, this electric fuel oil jet propeller vibrates for a short time, and noise is low, and operating range is wide.
Description of drawings:
Fig. 1 is a structural representation of the present invention
Fig. 2 is this fan hub 3 structural representations (comprising A-A and B-B generalized sections)
Fig. 3 is the structural representation of firing chamber 7
Fig. 4 is pneumatic fuel nozzle ring structure schematic cross-section
Among the figure: the 8 pneumatic fuel nozzle ring 9 transport pipe 10 igniters 11 spiral heat dissipation fins 12 crescent moon flame holders of 1 duct casing, 2 external rotor direct current generators, 3 fan hub, 4 fan blade, 5 fluid directors, 6 thermal shields, 7 firing chambers
Embodiment
The present invention is described further below in conjunction with accompanying drawing.
Please referring to shown in the accompanying drawing, in the drawings, fan blade 4 is fixed on the fan hub 3, and fan hub 3 is installed on external rotor direct current generator 2 external rotors, and is circumferentially uniform fastening with three screws.Fan hub 3 front ends open similar funnel form hole and inner chamber adopts spiral heat dissipation fin 11, fin adopts deviated splitter vane to arrange (as shown in Figure 2) at interval, spiral heat dissipation fin 11 can absorb the heat of external rotor direct current generator, can constitute an easy centrifugal blower again, air-flow sucks from fan hub 3 front end tappings when external rotor direct current generator 2 high speed rotating, when flowing through fin heat is taken away, entered into firing chamber 7 at last from thermal shield 6 outflows then and participate in burning.External rotor direct current generator 2 bearings are fixed on the inside support ring front end of fluid director 5, tighten fixing with bolt.Thermal shield is fixed on the rear end of fluid director 5 inside support rings, and fluid director 5 is tapered, the perforate cooling blast of external rotor direct current generator 2 that is used to circulate on the cover.The outer shroud of fluid director 5 is embedded on the inwall of duct casing 1, both as whole angle of rake primary load bearing parts, load in the work of supporting external rotor direct current generator high speed rotating is carried out water conservancy diversion deceleration diffusion to the air-flow after the fan blade of flowing through again and is become axially airflow flowing backward.Duct casing 1 front end is bell mouth shape and constitutes this angle of rake intake duct, makes things convenient for air-flow to flow into.Firing chamber 7 is arranged in the mid-rear portion position of duct casing 1, firing chamber 7 front ends are bearing on the inwall of duct casing 1, the rear end is bearing on the back inwall of duct casing 1, duct casing 1 inner bore cavity of fluid director 5 rear sections and firing chamber 7 outer wall leading portions form an expansion cavity, in this expansion cavity, continue the deceleration diffusion after making air flow stream cross fluid director, more help in firing chamber 7, participating in burning.A pneumatic fuel nozzle ring 8 is installed at the front end position of firing chamber 7; Crescent moon flame holder 12 is arranged in a distance, pneumatic fuel nozzle ring 8 back, be bearing on burning cavity two walls of firing chamber 7, air flow stream makes when crossing the stabilizer wall and forms low pressure area in its curved chamber, make air-flow form the airflow reflux district in curved back, chamber, fuel-air mixture can not be blown away in recirculating zone smooth combustion; Igniter 10 is placed in the airflow reflux district of crescent moon flame holder 12 rear ends; Wherein firing chamber 7 is firing chambers (as shown in Figure 3) of the equal perforate of inside and outside wall of similar " M " type profile shape, air-flow be divided into during through firing chamber 7 front ends two strands of air-flows one 7 outer walls enter the firing chamber by the hole and participate in burning from the firing chamber, another burst airflow passes firing chamber 7 inwalls enter the firing chamber by the hole and participate in burning; The gas circuit of pneumatic fuel nozzle ring 8 communicates with the oil circuit hole is vertical, when fuel oil flows into pneumatic fuel nozzle ring 8 air-flow of the elevated pressures of diversed device 5 rear ends vertically tangentially dispel form vaporific fuel-air mixture in firing chamber 7 by igniter 10 ignition combustions (as shown in Figure 4); Igniter 10 adopts electronic impulse ignition apparatus, and when reaching igniting and require, igniter 10 switch opens are emitted the electrical spark fuel-air mixture that ignites; The rear end passage of the rear end of duct casing 1 and firing chamber 7 diminishes and all is the convergence shape, constitutes this angle of rake jet nozzle, and the high temperature gas flow pressure after this convergence shape form helps burning reduces flow velocity and accelerates, and produces more effective thrust.The internal face of duct casing 1 adopts heat insulating coat, and the heat that passes over to the casing inwall when reducing combustion chambers burn helps guaranteeing the structural strength of duct casing 1 and reduces the influence of propulsion device temperature to the load and transport instrument of carrying.
Electric fuel oil jet propeller of the present invention has saved special fuel pump and the lubricating oil lubricating and cooling system that is had on the common large, medium and small type aeroengine, thereby can improve this angle of rake thrust weight ratio, has strengthened its usability.
Claims (7)
1. electric fuel oil jet propeller, comprise intake duct, fan, motor, fluid director, firing chamber, jet pipe, it is characterized in that fan blade 4 is fixed on the fan hub 3, fan hub 3 is fixed on external rotor direct current generator 2 rotors by the spiral heat dissipation fin supporting of its inner chamber, and described motor 2 is by being bolted on fluid director 5 inside support rings; Fluid director 5 outer shrouds are embedded on duct casing 1 interior walls; Thermal shield is installed in fluid director 5 inside support ring rear ends; Firing chamber 7 is installed in the middle rear end of duct casing 1, and firing chamber 7 leading portions are bearing in duct casing 1 interior walls intermediate portion, and 7 rear ends, firing chamber are bearing in position, duct casing 1 interior walls rear end; Firing chamber 7 leading portions are installed a pneumatic fuel nozzle ring 8, and pneumatic fuel nozzle ring 8 communicates with transport pipe 9; Transport pipe 9 passes duct casing 1 and is connected with outer oil circuit; Crescent moon flame holder 12 is arranged in a distance, pneumatic fuel nozzle ring 8 back, is bearing on burning cavity two walls of firing chamber 7; Igniter 10 is placed in a distance, crescent moon flame holder 12 rear end, passes firing chamber 7 and duct casing 1 and is fixed on duct casing 1 outer wall.
2. electric fuel oil jet propeller according to claim 1 is characterized in that: this angle of rake thrust is 1～50kg.
3. electric fuel oil jet propeller according to claim 1 is characterized in that: duct casing 1 inner bore cavity of fluid director 5 rear sections becomes an expansion cavity with firing chamber 7 leading portions.
4. according to claim 1,2 described electric fuel oil jet propellers, it is characterized in that: firing chamber 7 profiles are similar " M " type profile shape, and front-end face and inside and outside wall rounding off.
5. electric fuel oil jet propeller according to claim 1, it is characterized in that: fan hub 3 is the cavity of a front end perforate, and cavity inner wall circumferentially is covered with spiral heat dissipation fin 11, and fin is the length fin, and fan hub 3 is an integral body with spiral heat dissipation fin 11.
6. electric fuel oil jet propeller according to claim 1 is characterized in that: thermal shield 6 is the cone-shaped hood of wall perforate.
7. electric fuel oil jet propeller according to claim 1 is characterized in that: pneumatic fuel nozzle ring 8 is a whole oil nozzle, and general shape is similar cylindrical toroidal.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810107322A CN101725431A (en) | 2008-10-31 | 2008-10-31 | Electric fuel oil jet propeller |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810107322A CN101725431A (en) | 2008-10-31 | 2008-10-31 | Electric fuel oil jet propeller |
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| Publication Number | Publication Date |
|---|---|
| CN101725431A true CN101725431A (en) | 2010-06-09 |
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| Application Number | Title | Priority Date | Filing Date |
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| CN200810107322A Pending CN101725431A (en) | 2008-10-31 | 2008-10-31 | Electric fuel oil jet propeller |
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Cited By (15)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103807052A (en) * | 2014-03-10 | 2014-05-21 | 邱世军 | Electric drive jet engine |
| CN105888878A (en) * | 2016-04-18 | 2016-08-24 | 夏建国 | Turbineless jet engines |
| CN106121861A (en) * | 2016-06-21 | 2016-11-16 | 王启振 | Jet engine without efficient turbine |
| CN106545481A (en) * | 2015-09-22 | 2017-03-29 | 上海中科深江电动车辆有限公司 | Wearable Personal Transporter |
| CN106540433A (en) * | 2015-09-22 | 2017-03-29 | 上海中科深江电动车辆有限公司 | Personal power-driven tool |
| CN107211287A (en) * | 2014-08-29 | 2017-09-26 | 峰鸟航空科技公司 | The system and method that regional air transport network is realized using hybrid electrically aircraft |
| CN107882655A (en) * | 2017-11-17 | 2018-04-06 | 南方科技大学 | Outer edge type electric propulsion jet engine system and design method |
| CN110030113A (en) * | 2019-05-27 | 2019-07-19 | 谢昌松 | It is pressurized punching engine and aircraft |
| CN111005881A (en) * | 2019-12-10 | 2020-04-14 | 浙江双阳风机有限公司 | Fire-fighting smoke exhaust fan |
| CN111237084A (en) * | 2020-02-17 | 2020-06-05 | 王镇辉 | Electric-driven jet aircraft engine and aircraft |
| WO2021084105A1 (en) * | 2019-11-01 | 2021-05-06 | Geola Technologies Ltd. | Smart electric ducted fan |
| CN113551260A (en) * | 2021-07-19 | 2021-10-26 | 南昌航空大学 | V-shaped flame stabilizer with flow guide holes |
| CN113551259A (en) * | 2021-07-19 | 2021-10-26 | 南昌航空大学 | Wave-shaped middle-slit type V-shaped flame stabilizer with lobe partition plate |
| CN114645799A (en) * | 2022-02-24 | 2022-06-21 | 哈尔滨工业大学 | Axisymmetric full-speed-domain ramjet engine using electric auxiliary supercharging |
| CN114790955A (en) * | 2022-05-06 | 2022-07-26 | 哈尔滨工业大学 | Hybrid power engine capable of realizing oil-electricity range extension |
-
2008
- 2008-10-31 CN CN200810107322A patent/CN101725431A/en active Pending
Cited By (19)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103807052A (en) * | 2014-03-10 | 2014-05-21 | 邱世军 | Electric drive jet engine |
| CN107211287A (en) * | 2014-08-29 | 2017-09-26 | 峰鸟航空科技公司 | The system and method that regional air transport network is realized using hybrid electrically aircraft |
| US11866184B2 (en) | 2014-08-29 | 2024-01-09 | Zunum Aero, Inc. | System and methods for implementing regional air transit network using hybrid-electric aircraft |
| CN106545481A (en) * | 2015-09-22 | 2017-03-29 | 上海中科深江电动车辆有限公司 | Wearable Personal Transporter |
| CN106540433A (en) * | 2015-09-22 | 2017-03-29 | 上海中科深江电动车辆有限公司 | Personal power-driven tool |
| CN105888878A (en) * | 2016-04-18 | 2016-08-24 | 夏建国 | Turbineless jet engines |
| CN106121861A (en) * | 2016-06-21 | 2016-11-16 | 王启振 | Jet engine without efficient turbine |
| CN107882655B (en) * | 2017-11-17 | 2023-06-20 | 南方科技大学 | Outer edge type electric propulsion jet engine system and design method |
| CN107882655A (en) * | 2017-11-17 | 2018-04-06 | 南方科技大学 | Outer edge type electric propulsion jet engine system and design method |
| CN110030113A (en) * | 2019-05-27 | 2019-07-19 | 谢昌松 | It is pressurized punching engine and aircraft |
| CN110030113B (en) * | 2019-05-27 | 2024-04-16 | 宁波志胜空天动力科技有限公司 | Supercharged ramjet engine and aircraft |
| WO2021084105A1 (en) * | 2019-11-01 | 2021-05-06 | Geola Technologies Ltd. | Smart electric ducted fan |
| CN111005881A (en) * | 2019-12-10 | 2020-04-14 | 浙江双阳风机有限公司 | Fire-fighting smoke exhaust fan |
| CN111237084A (en) * | 2020-02-17 | 2020-06-05 | 王镇辉 | Electric-driven jet aircraft engine and aircraft |
| CN113551259A (en) * | 2021-07-19 | 2021-10-26 | 南昌航空大学 | Wave-shaped middle-slit type V-shaped flame stabilizer with lobe partition plate |
| CN113551260A (en) * | 2021-07-19 | 2021-10-26 | 南昌航空大学 | V-shaped flame stabilizer with flow guide holes |
| CN114645799A (en) * | 2022-02-24 | 2022-06-21 | 哈尔滨工业大学 | Axisymmetric full-speed-domain ramjet engine using electric auxiliary supercharging |
| CN114645799B (en) * | 2022-02-24 | 2024-04-26 | 哈尔滨工业大学 | Axisymmetric full-speed-domain ramjet engine using electric auxiliary supercharging |
| CN114790955A (en) * | 2022-05-06 | 2022-07-26 | 哈尔滨工业大学 | Hybrid power engine capable of realizing oil-electricity range extension |
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Application publication date: 20100609 |