CN201461131U - Self-priming jet engine for aircraft - Google Patents

Self-priming jet engine for aircraft Download PDF

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Publication number
CN201461131U
CN201461131U CN200920127817XU CN200920127817U CN201461131U CN 201461131 U CN201461131 U CN 201461131U CN 200920127817X U CN200920127817X U CN 200920127817XU CN 200920127817 U CN200920127817 U CN 200920127817U CN 201461131 U CN201461131 U CN 201461131U
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CN
China
Prior art keywords
oil
engine
heater
aircraft
jet engine
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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.)
Expired - Fee Related
Application number
CN200920127817XU
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Chinese (zh)
Inventor
杜春平
Original Assignee
杜春平
Priority date (The priority date 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 date listed.)
Filing date
Publication date
Application filed by 杜春平 filed Critical 杜春平
Priority to CN200920127817XU priority Critical patent/CN201461131U/en
Application granted granted Critical
Publication of CN201461131U publication Critical patent/CN201461131U/en
Anticipated expiration legal-status Critical
Expired - Fee Related legal-status Critical Current

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Abstract

The utility model discloses a self-priming jet engine for an aircraft, which comprises a cylindrical engine casing. The jet engine is characterized in that a horn-shaped air intake port is formed on the inner side of the front end of the engine casing; a funneled exhaust port is formed at the rear end of the engine casing; a combustion chamber is formed between the air intake port and the exhaust port; at least two sets of jet combustion devices are uniformly distributed in the combustion chamber; the jet combustion devices are fixedly connected to the inside walls of the combustion chamber; oil gas spray nozzles in the jet combustion devices are toward the exhaust port; the jet combustion devices are communicated with an oil transfer pump outside the engine casing; and a perforation airflow propulsion channel is formed by the air intake port, the combustion chamber and the exhaust port in sequence. The self-priming jet engine for the aircraft has the beneficial effects that the process is simple; the jet engine is light and handy; the damage is slight and the noise is low if tiny foreign objects enter into the jet engine; the shape of the jet engine can be converted as requried; less fuel is utilized and less energy is consumed; and the jet engine enables the aircraft to fly for farther distance under the condition of carrying fuel with the same weight.

Description

The self-priming jet engine of aircraft
Technical field the utility model relates to a kind of motor, the self-priming jet engine of particularly a kind of aircraft.
Background technique at present in aircraft employed jet engine all be the turbojet motor, if difficulty of processing height, heaviness, noise have foreign matter to enter motor greatly grievous injury is caused the accident; The turbine of high speed rotating causes engine high-temperature; Prescribe a time limit when turbine rotates to necessarily, turbine can cause resistance not quicken to the place ahead; The turbojet motor generally all is that circle can not change shape as required.And, employed jet engine all is that front end is a fuel injector for the motor rear end in the aircraft, produce Driving force by fuel injector, overcome the gravitation of the earth, and the resistance of air, promote aircraft lift-off or flight, can not initiatively utilize the fluid characteristics of air, make aircraft reduce resistance of air.
The summary of the invention the purpose of this utility model is exactly at the deficiencies in the prior art, provides that a kind of processing is simple, light and handy, noise is little, have little foreign matter to enter does little harm, and does not have the self-priming jet engine of aircraft of the machinery that runs up.
For achieving the above object, the utility model adopts following technological scheme:
The self-priming jet engine of a kind of aircraft comprises the drum type engine housing, it is characterized in that; The front end inboard of engine housing is tubaeform suction port, and the rear end of engine housing is the funnel shape relief opening, is the firing chamber between suction port and relief opening; Be evenly equipped with at least two cover spray combustion devices in the firing chamber, spray combustion device is fixedly connected on the madial wall of firing chamber, and the oil gas nozzle in the spray combustion device is towards relief opening, and spray combustion device is communicated with the oil transfer pump of engine housing outside; Suction port, firing chamber, relief opening form the propulsive gas circulation road of perforation successively.
Owing to adopted technique scheme, discharge is sprayed in the high-temperature fuel deflagration of spray combustion device backward, produce thrust forward, simultaneously, because suction port, firing chamber, relief opening form the propulsive gas circulation road of perforation successively, can take away a large amount of air at fuel during in burning and discharge from the propulsive gas circulation road, the place ahead forms vacuum, produce suction, these two power promote jet engine simultaneously and form proal making a concerted effort, and have strengthened the Driving force of aircraft with self-priming jet engine.And, because the place ahead forms vacuum, reduced the resistance of the air in aircraft the place ahead, and then the lift-off of raising aircraft or the speed of flight, and obtaining under the prerequisite of same acceleration, use fuel still less, consume the energy still less, under the situation of carrying identical weight fuel, the farther distance of can flying.Because therefore running machinery can not change shape as required, applied widely.
Preferably, described spray combustion device is made up of oil gas nozzle, the high-pressure oil pipe that is connected with oil nozzle, high-pressure air pipe, heater, spark plug, one end of high-pressure oil pipe is communicated with oil transfer pump, one end of high-pressure oil pipe is connected with oil nozzle, oil nozzle places the tail end inside of high-pressure air pipe, the tail end of high-pressure air pipe is extended to suction port by the direction of relief opening, bending backward near the suction port place, the tail end that high-pressure air pipe bends backward is connected with the oil gas nozzle, the oil gas nozzle is towards relief opening, and spark plug is located at the spout place of oil gas nozzle; Outside at high-pressure oil pipe, high-pressure air pipe is provided with heater, and heater is fixedly connected on the inwall of firing chamber, and heater is connected with power supply.
Heater is used for the fuel of heating high-pressure oil pipe, and make through oil nozzle and be ejected into pulverized fuel in the high-pressure air pipe, reach the point of ignition of fuel, from ejection of oil gas nozzle and air mixing, by spark ignitor, fuel produces detonation in the firing chamber, waste gas discharge is produced forward thrust from outlet pipe, consume a large amount of oxygen during fuel detonation simultaneously, make the place ahead formation vacuum of aircraft with self-priming jet engine, reach the minimizing resistance of air, improved the purpose of flying speed.
Further preferred, described heater is a tubular shape, and high-pressure oil pipe, high-pressure air pipe pass the middle part that heater is a tubular shape, place heater.The tubular shape heater heats is even, high insulating effect, and the structural reliability height, not fragile.
The utility model aircraft with the beneficial effect of self-priming jet engine is, processing is simple, light and handy, have little foreign matter to enter does little harm, noise is little, can change shape as required, use fuel still less, consume the energy still less, under the situation of carrying identical weight fuel, the farther distance of can flying.
Description of drawings Fig. 1 is a structural representation of the present utility model;
Fig. 2 is the A-A sectional view among Fig. 1.
Embodiment is further described the utility model below in conjunction with accompanying drawing, but therefore the utility model is not limited among the described scope of embodiments.
Referring to Fig. 1, the self-priming jet engine of a kind of aircraft comprises drum type engine housing 1, it is characterized in that; The front end inboard of engine housing 1 is tubaeform suction port 11, and the rear end of engine housing 1 is a funnel shape relief opening 12, is firing chamber 2 between suction port 11 and relief opening 12; In firing chamber 2, be evenly equipped with at least two cover spray combustion devices 3, spray combustion device 3 is fixedly connected on 2 madial walls of firing chamber, oil gas nozzle 31 in the spray combustion device 3 is towards relief opening 12, and spray combustion device 3 is communicated with the oil transfer pump 4 of engine housing 1 outside; Suction port 11, firing chamber 2, relief opening 12 form the propulsive gas circulation road that connects successively.
Referring to Fig. 1, Fig. 2, described spray combustion device 3 is by oil gas nozzle 31, be connected with the high-pressure oil pipe 32 of oil nozzle 33, high-pressure air pipe 34, heater 35, spark plug 36 is formed, one end of high-pressure oil pipe 32 is communicated with oil transfer pump 4, one end of high-pressure oil pipe 32 is connected with oil nozzle 33, oil nozzle 33 places the tail end inside of high-pressure air pipe 34, the tail end of high-pressure air pipe 34 is extended to suction port 11 by the direction of relief opening 12, bending backward near suction port 11 places, the tail end that high-pressure air pipe 34 bends backward is connected with oil gas nozzle 31, oil gas nozzle 31 is towards relief opening 12, and spark plug 36 is located at the spout place of oil gas nozzle 31; Outside at high-pressure oil pipe 32, high-pressure air pipe 34 is provided with heater 35, and heater 35 is fixedly connected on the inwall of firing chamber 2, and heater 35 is connected with power supply.The power line 351 of the power line 361 of spark plug 36, heater 35 is connected with power supply respectively among Fig. 1.
Referring to Fig. 2, described heater 35 is a tubular shape, and high-pressure oil pipe 32, high-pressure air pipe 34 pass heater 35 and be the middle part of tubular shape, place heater 35.
Described mode of execution of the present utility model though combine accompanying drawing, those of ordinary skill in the art can make various distortion or modification within the scope of the appended claims.
Working principle
Start
Utilize power supply that heater 35 is carried out preheating, restart oil transfer pump 4, fuel high pressure is input to high-pressure oil pipe 5, heater 35 after the preheating will the heating high-pressure oil pipe fuel in 32, High Temperature High Pressure fuel is again by oil nozzle 33 atomizings, high-pressure air pipe 34 continues heating with the fuel of atomizing, fuel is reached a high temperature, supply of fuel continuously makes high-temperature gas fuel from 31 ejections of oil gas nozzle, and with air mixing, spark plug 36 is with the ignited fuel of ejection, constantly burnt fuel makes heater 35 heat up again, make heater 35 keep high temperature, just can stop the power supply supply of heater 35 this moment, utilizes the heat that self receives that heat is provided.
Work
Start complete after, strengthening the oil transportation amount makes the fuel of oil gas nozzle 31 ejections form high pressure, the fuel of being lighted can support the high-temperature fuel that sprays to burn away, the fuel of ejection can be discharged waste gas after 2 detonations of firing chamber from outlet pipe 12 at a high speed, a large amount of air in the firing chamber 2 can be taken away when high-temperature fuel burns in this process, make firing chamber 2 form vacuum, in order to subsidize this vacuum point suction port 11 formation vacuum that also can reduce pressure, the resistance of air in the place ahead reduces, generation thrust is forward discharged in the high-temperature fuel detonation backward, the place ahead forms vacuum and produces suction, and these two power all are to promote the proal power of jet engine.
Flame-out
The fuel disconnection is stopped oil transportation, and in-engine excess oil can burn away to and stop, heater 35 natural cooling of engine interior.

Claims (3)

1. the self-priming jet engine of aircraft comprises drum type engine housing (1), it is characterized in that; The front end inboard of engine housing (1) is tubaeform suction port (11), and the rear end of engine housing (1) is funnel shape relief opening (12), is firing chamber (2) between suction port (11) and relief opening (12); In firing chamber (2), be evenly equipped with at least two cover spray combustion devices (3), spray combustion device (3) is fixedly connected on the madial wall of firing chamber (2), oil gas nozzle (31) in the spray combustion device (3) is towards relief opening (12), and spray combustion device (3) is communicated with the oil transfer pump (4) of engine housing (1) outside; Suction port (11), firing chamber (2), relief opening (12) form the propulsive gas circulation road that connects successively.
2. the self-priming jet engine of aircraft according to claim 1, it is characterized in that: described spray combustion device (3) is by oil gas nozzle (31), be connected with the high-pressure oil pipe (32) of oil nozzle (33), high-pressure air pipe (34), heater (35), spark plug (36) is formed, one end of high-pressure oil pipe (32) is communicated with oil transfer pump (4), one end of high-pressure oil pipe (32) is connected with oil nozzle (33), oil nozzle (33) places the tail end inside of high-pressure air pipe (34), the tail end of high-pressure air pipe (34) is extended to suction port (11) by the direction of relief opening (12), locating to bend backward near suction port (11), the tail end that high-pressure air pipe (34) bends backward is connected with oil gas nozzle (31), oil gas nozzle (31) is towards relief opening (12), and spark plug (36) is located at the spout place of oil gas nozzle (31); Outside at high-pressure oil pipe (32), high-pressure air pipe (34) is provided with heater (35), and heater (35) is fixedly connected on the inwall of firing chamber (2), and heater (35) is connected with power supply.
3. the self-priming jet engine of aircraft according to claim 2, it is characterized in that: described heater (35) is a tubular shape, high-pressure oil pipe (32), high-pressure air pipe (34) pass heater (35) and are the middle part of tubular shape, place heater (35).
CN200920127817XU 2009-06-30 2009-06-30 Self-priming jet engine for aircraft Expired - Fee Related CN201461131U (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN200920127817XU CN201461131U (en) 2009-06-30 2009-06-30 Self-priming jet engine for aircraft

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN200920127817XU CN201461131U (en) 2009-06-30 2009-06-30 Self-priming jet engine for aircraft

Publications (1)

Publication Number Publication Date
CN201461131U true CN201461131U (en) 2010-05-12

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Family Applications (1)

Application Number Title Priority Date Filing Date
CN200920127817XU Expired - Fee Related CN201461131U (en) 2009-06-30 2009-06-30 Self-priming jet engine for aircraft

Country Status (1)

Country Link
CN (1) CN201461131U (en)

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107514319A (en) * 2016-06-18 2017-12-26 蒋步群 Jet engine speedup liquid

Cited By (1)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN107514319A (en) * 2016-06-18 2017-12-26 蒋步群 Jet engine speedup liquid

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GR01 Patent grant
C14 Grant of patent or utility model
CF01 Termination of patent right due to non-payment of annual fee

Granted publication date: 20100512

Termination date: 20120630

C17 Cessation of patent right