CN104454235A - Hybrid power jet engine - Google Patents
Hybrid power jet engine Download PDFInfo
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- CN104454235A CN104454235A CN201410749259.6A CN201410749259A CN104454235A CN 104454235 A CN104454235 A CN 104454235A CN 201410749259 A CN201410749259 A CN 201410749259A CN 104454235 A CN104454235 A CN 104454235A
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Abstract
The invention discloses a hybrid power jet engine. The hybrid power jet engine comprises an engine body, a battery, a motor speed regulator, an oil pump, an oil tank and a controller, wherein the engine body comprises an engine case, a pressure expander, a motor, a combustion chamber, an exhaust nozzle, an oil injection tube and an evaporation tube; the pressure expander, the motor, the combustion chamber, the exhaust nozzle, the oil injection tube and the evaporation tube are fixed in the engine case; openings are formed in two ends of the engine case; and the motor, the combustion chamber, the exhaust nozzle, the oil injection tube and the evaporation tube are fixed in the engine case. The jet engine is powered by hybrid power, works reliably, and is high in thrust-weight ratio, simple in structure and low in cost.
Description
Technical field
The invention belongs to field of power machinery, relate to a kind of motor, be specifically related to a kind of mixed power air breathing engine.
Background technique
Air breathing engine a kind ofly produces high temperature thus Accelerating Removal high-velocity fluid by fuel combustion and do work and produce the heat engine of thrust.Major part air breathing engine is all the internal-combustion engine relying on Newton's third law work.Jet engine has relatively excellent performance under high-speed condition, and major part is all be applied on aircraft, and its appearance and application allow the mankind enter the epoch of supersonic flight.Existing air breathing engine comprises athodyd, pulse jet engine, turbojet engine, turboramjet engine and turborocket etc.Wherein, no matter be that turbojet engine is most widely used in civilian or military domain.But turbojet engine is due to complex structure, and operating conditions and material requirements harshness, cause its technical difficulty and cost very high, the market of turbojet engine almost monopolized by several big companies few in number in the world.
In recent years, unmanned air vehicle technique all becomes the emphasis of various countries' research and development, and the engine technology corresponding with it also becomes focus naturally.But because different unmanned planes has difference, traditional manned aircraft jet engine can not well adapt to all types of unmanned plane.Particularly have miniaturization for some, lightweight, high speed, the unmanned plane that low cost requires, be badly in need of a kind of structure simple, reliable operation, thrust weight ratio is high, cheap motor.In recent years, along with the development of high-energy lithium cell and high-power brushless motor, the electric propeller power system as combination widely uses on Small and micro-satellite.But be subject to aerodynamic restriction, existing electric propeller power system efficiency under high-speed flight condition can reduce greatly, cannot meet the demand of high-speed unmanned aerial vehicle.
Summary of the invention
The object of the invention is to the shortcoming overcoming above-mentioned prior art, provide a kind of mixed power air breathing engine, this motor adopts mixed power, and engine operation is reliable, and thrust weight ratio is high, and structure is simple, and cost is low.
For achieving the above object, mixed power air breathing engine of the present invention comprises engine body, battery, machine governor, oil pump, fuel tank and controller;
Described engine body comprises casing and is fixed on the Diffuser in casing, motor, firing chamber, jet pipe, spray bar and evaporating pipe, the both ends open of casing, motor, firing chamber, jet pipe, spray bar and evaporating pipe are all fixed in casing, the output shaft of motor is connected with the live axle of gas compressor, the entrance of gas compressor is positioned at the aperture position of casing one end, the outlet of gas compressor is connected with the entrance of Diffuser, the outlet of Diffuser is connected with the air inlet of firing chamber, the entrance of jet pipe one end is connected with the outlet of firing chamber through the opening of the casing the other end, firing chamber internal fixtion is in preheating nozzle tip and the temperature transducer for detecting burning room temperature, the outlet of fuel tank is connected with the entrance of oil pump, oil delivery side of pump is divided into two-way, wherein a road is connected with the oiler of preheating nozzle tip, solenoid valve of separately leading up to is connected with the entrance of spray bar, the outlet of spray bar is connected with the entrance of evaporating pipe, the outlet of evaporating pipe is connected with the oil gas entrance of firing chamber,
Described battery is connected with the power interface of motor by machine governor, the power interface of oil pump is connected with battery, the output terminal of temperature transducer is connected with the input end of controller, and the output terminal of controller is connected with the control end of the control end of machine governor, solenoid valve and the control end of oil pump.
Also comprise the sensor for obtaining engine body running state, the output terminal of sensor is connected with the input end of controller.
Described evaporating pipe is positioned at firing chamber.
The present invention has following beneficial effect:
Mixed power air breathing engine of the present invention operationally, battery is worked by machine governor drive motor, motor drives gas compressor to suck air, air enters in firing chamber after Diffuser supercharging, oil in fuel tank enters into spray bar after oil pump, evaporating pipe is entered into after oil ejection in spray bar, oil gasifies due to high temperature action in evaporating pipe, oil after gasification enters into firing chamber, and with the air mixed combustion in firing chamber, thus produce the waste gas of high pressure-temperature, waste gas is sprayed by jet pipe, thus generation thrust, the present invention replaces the turbine drives gas compressor of transmission by motoring gas compressor, eliminate the turbine of transmission turbojet engine, guide vane, coupling shaft and bearing equally accurate and the very high parts of material requirements, thus simplify the structure of motor, reduce the weight of motor, improve the reliability of motor.In addition, due to behind firing chamber without any rotary component, motor of the present invention more easily and athodyd combine, thus obtain more excellent performance, particularly along with the development of high energy battery and high-speed brushless motor, motor of the present invention will highlight greater advantages, no matter is at unmanned plane or manned aircraft even other field, all can has very large development prospect.
Accompanying drawing explanation
Fig. 1 is schematic diagram of the present invention;
Fig. 2 is the structural representation of engine body 1 in the present invention;
Fig. 3 is the structural representation of the present invention when applying.
Wherein, 1 be engine body, 2 be controller, 3 be battery, 4 be machine governor, 5 be oil pump, 6 be fuel tank, 7 be gas compressor, 8 be Diffuser, 9 be motor, 10 be firing chamber, 11 be spray bar, 12 be evaporating pipe, 13 be jet pipe, 14 be preheating nozzle tip, 15 for casing.
Embodiment
Below in conjunction with accompanying drawing, the present invention is described in further detail:
With reference to figure 1, Fig. 2 and Fig. 3, mixed power air breathing engine of the present invention comprises engine body 1, battery 3, machine governor 4, oil pump 5, fuel tank 6 and controller 2, described engine body 1 comprises casing 15 and is fixed on the Diffuser 8 in casing 15, motor 9, firing chamber 10, jet pipe 13, spray bar 11 and evaporating pipe 12, the both ends open of casing 15, motor 9, firing chamber 10, jet pipe 13, spray bar 11 and evaporating pipe 12 are all fixed in casing 15, the output shaft of motor 9 is connected with the live axle of gas compressor 7, the entrance of gas compressor 7 is positioned at the aperture position of casing 15 one end, the outlet of gas compressor 7 is connected with the entrance of Diffuser 8, the outlet of Diffuser 8 is connected with the air inlet of firing chamber 10, the entrance of jet pipe 13 one end is connected with the outlet of firing chamber 10 through the opening of casing 15 the other end, firing chamber 10 internal fixtion is in preheating nozzle tip 14 and the temperature transducer for detecting temperature in firing chamber 10, the outlet of fuel tank 6 is connected with the entrance of oil pump 5, the outlet of oil pump 5 is divided into two-way, wherein a road is connected with the oiler of preheating nozzle tip 14, solenoid valve of separately leading up to is connected with the entrance of spray bar 11, the outlet of spray bar 11 is connected with the entrance of evaporating pipe 12, the outlet of evaporating pipe 12 is connected with the oil gas entrance of firing chamber 10, battery 3 is connected by the power interface of machine governor 4 with motor 9, the power interface of oil pump 5 is connected with battery 3, the output terminal of temperature transducer is connected with the input end of controller 2, and the output terminal of controller 2 is connected with the control end of the control end of machine governor 4, the control end of solenoid valve and oil pump 5.
It should be noted that, the present invention also comprises the sensor for obtaining engine body 1 motion state, and the output terminal of sensor is connected with the input end of controller 2.Described evaporating pipe 12 is positioned at firing chamber 10.
Specific works process of the present invention is:
User makes oil pump 5 work by controller 2, oil in fuel tank 6 is delivered in burning head 14 by oil pump 5, burning head 14 combustion heating evaporating pipe 12, temperature transducer detects the temperature information in evaporating pipe 12 in real time, and described temperature information is forwarded in controller 2, whether the temperature that controller 2 judges in evaporating pipe 12 according to described temperature information is more than or equal to pre-set threshold value, when the temperature in evaporating pipe 12 is more than or equal to pre-set threshold value, then produce the first electrical signal and the second electrical signal, opened by described first electrical signal Controlling solenoid valve again, and described second electrical signal is forwarded to machine governor 4, machine governor 4 makes motor 9 work according to described second electrical signal, motor 9 drives gas compressor 7 to suck air, air enters in firing chamber 10 after Diffuser 8 supercharging, oil in fuel tank 6 enters into spray bar 11 by oil pump 5, oil in spray bar 11 enters into evaporating pipe 12, oil is subject to high temperature action and gasifies in evaporating pipe 12, oil after gasification and air mixed combustion, thus produce the waste gas of High Temperature High Pressure, waste gas is sprayed by jet pipe 13, thus generation thrust.
Claims (3)
1. a mixed power air breathing engine, it is characterized in that, comprise engine body (1), battery (3), machine governor (4), oil pump (5), fuel tank (6) and controller (2);
Described engine body (1) comprises casing (15), jet pipe (13), and the Diffuser (8) be fixed in casing (15), motor (9), firing chamber (10), spray bar (11) and evaporating pipe (12), the both ends open of casing (15), the output shaft of motor (9) is connected with the live axle of gas compressor (7), the entrance of gas compressor (7) is positioned at the aperture position of casing (15) one end, the outlet of gas compressor (7) is connected with the entrance of Diffuser (8), the outlet of Diffuser (8) is connected with the air inlet of firing chamber (10), the entrance of jet pipe (13) one end is connected with the outlet of firing chamber (10) through the opening of casing (15) the other end, firing chamber (10) internal fixtion is in preheating nozzle tip (14) and the temperature transducer for detecting temperature in firing chamber (10), the outlet of fuel tank (6) is connected with the entrance of oil pump (5), the outlet of oil pump (5) is divided into two-way, wherein a road is connected with the oiler of preheating nozzle tip (14), solenoid valve of separately leading up to is connected with the entrance of spray bar (11), the outlet of spray bar (11) is connected with the entrance of evaporating pipe (12), the outlet of evaporating pipe (12) is connected with the oil gas entrance of firing chamber (10),
Described battery (3) is connected by the power interface of machine governor (4) with motor (9), the power interface of oil pump (5) is connected with battery (3), the output terminal of temperature transducer is connected with the input end of controller (2), and the output terminal of controller (2) is connected with the control end of the control end of machine governor (4), the control end of solenoid valve and oil pump (5).
2. mixed power air breathing engine according to claim 1, is characterized in that, also comprises the sensor for obtaining engine body (1) motion state, and the output terminal of sensor is connected with the input end of controller (2).
3. mixed power air breathing engine according to claim 1, is characterized in that, described evaporating pipe (12) is positioned at firing chamber (10).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410749259.6A CN104454235A (en) | 2014-12-05 | 2014-12-05 | Hybrid power jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410749259.6A CN104454235A (en) | 2014-12-05 | 2014-12-05 | Hybrid power jet engine |
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| Publication Number | Publication Date |
|---|---|
| CN104454235A true CN104454235A (en) | 2015-03-25 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201410749259.6A Pending CN104454235A (en) | 2014-12-05 | 2014-12-05 | Hybrid power jet engine |
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Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105698218A (en) * | 2016-01-11 | 2016-06-22 | 清华大学 | Combustion chamber gas introducing mechanism of turbine piston hybrid power system |
Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CZ20021405A3 (en) * | 2002-04-23 | 2003-12-17 | Marek Nedbal | Thermocouples or photoelectric cells with an electric motor for jet-turbine engines |
| RU2303152C1 (en) * | 2006-01-10 | 2007-07-20 | Открытое акционерное общество "Климов" | Jet engine installation of flight vehicle |
| US20090127400A1 (en) * | 2004-07-30 | 2009-05-21 | Eugene Lavretsky | Adaptive control in the presence of input constraints |
| CN203412671U (en) * | 2013-06-25 | 2014-01-29 | 杨家雄 | Electric compressed air jet engine |
| CN204532576U (en) * | 2014-12-05 | 2015-08-05 | 张旭超 | A kind of mixed power air breathing engine |
-
2014
- 2014-12-05 CN CN201410749259.6A patent/CN104454235A/en active Pending
Patent Citations (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CZ20021405A3 (en) * | 2002-04-23 | 2003-12-17 | Marek Nedbal | Thermocouples or photoelectric cells with an electric motor for jet-turbine engines |
| US20090127400A1 (en) * | 2004-07-30 | 2009-05-21 | Eugene Lavretsky | Adaptive control in the presence of input constraints |
| RU2303152C1 (en) * | 2006-01-10 | 2007-07-20 | Открытое акционерное общество "Климов" | Jet engine installation of flight vehicle |
| CN203412671U (en) * | 2013-06-25 | 2014-01-29 | 杨家雄 | Electric compressed air jet engine |
| CN204532576U (en) * | 2014-12-05 | 2015-08-05 | 张旭超 | A kind of mixed power air breathing engine |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105698218A (en) * | 2016-01-11 | 2016-06-22 | 清华大学 | Combustion chamber gas introducing mechanism of turbine piston hybrid power system |
| CN105698218B (en) * | 2016-01-11 | 2018-07-24 | 清华大学 | The combustion chamber bleed mechanism of Turbine piston hybrid power system |
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Application publication date: 20150325 |