CN101025129A - Rotary punching engine - Google Patents

Rotary punching engine Download PDF

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Publication number
CN101025129A
CN101025129A CN 200710027243 CN200710027243A CN101025129A CN 101025129 A CN101025129 A CN 101025129A CN 200710027243 CN200710027243 CN 200710027243 CN 200710027243 A CN200710027243 A CN 200710027243A CN 101025129 A CN101025129 A CN 101025129A
Authority
CN
China
Prior art keywords
main shaft
engine
rotary punching
punching engine
main
Prior art date
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.)
Pending
Application number
CN 200710027243
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Chinese (zh)
Inventor
王永灵
Original Assignee
王永灵
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 王永灵 filed Critical 王永灵
Priority to CN 200710027243 priority Critical patent/CN101025129A/en
Publication of CN101025129A publication Critical patent/CN101025129A/en
Pending legal-status Critical Current

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Abstract

The invention relates to a rotating punching engine, comprising a main body, where the main body is connected with main shaft through link rod, the main shaft is connected with output shaft of the engine, a gas inlet channel in the cavity of the main body is equipped with primary spout, and combustion chamber is internally equipped with secondary spout and equipped with spark plug. And the invention has advantages of high starting speed, full fuel combustion, low oil consumption, high drive ratio, high drive efficiency, large voyage, and safety and reliability. And the invention can be installed on helicopters, missiles and army or civil airplanes; and the invention has a very large upgrading space and by slight improvement, can be used on space shuttles, used as a punching engine in the atmosphere and used as rocket burner in astrospace.

Description

Rotary punching engine
[technical field]
The present invention relates to a kind of motor, especially relate to a kind of rotary punching engine that is applied to aviation field.
[background technique]
At present, the inner chamber of pressed engine mainly is to be made of intake duct, firing chamber and jet pipe three parts, required fuel all is directly to spray into the firing chamber through the plug ignition after-combustion, when working under the speed of pressed engine at higher Mach number, firing chamber inlet air flow velocity degree is very high, it is very difficult that fuel and Air mixing become, will improve mixing efficiency if improve combustion efficiency, this just needs the lengthening firing chamber, thereby increases frictional loss and increase the fuel that place, firing chamber wall cools off usefulness.In addition, existing pressed engine all needs with guided missile or aircraft it to be accelerated to the superelevation velocity of sound before startup, and pressed engine could start, thereby has greatly restricted the development and the application of pressed engine.
[summary of the invention]
In order to overcome the above-mentioned shortcoming of prior art, the invention provides a kind of rotary design, combustion efficiency height, simple and reasonable rotary punching engine of adopting.
The technical solution adopted for the present invention to solve the technical problems is: a kind of rotary punching engine, comprise body, this body links by link rod and main shaft, described main shaft and starter motor output shaft link, intake duct in chamber body is provided with first nozzle, is provided with the secondary spout and spark plug is installed in the firing chamber.
Outer wall at described body is provided with thermal-protective coating.
In described main shaft and link rod, be provided with fuel channel.
At described air inlet road junction the activity safety net is housed.
Described main shaft links by flywheel and starter motor output shaft.
The shaft axis in described intrinsic intake duct, firing chamber and tail spray road becomes 75~85 degree angles with main shaft.
The invention has the beneficial effects as follows: adopt Rotation Design, utilize starter motor to make the relative velocity of firing chamber and air reach more than the 3 overtone speed, thereby reach operating conditions, general pressed engine can be worked greater than 0.5 overtone speed, when the pressed engine turning radius is 3.5 meters, spindle speed per minute tens0000 changes, and just can reach 3 overtone speed, and prior art is easy to reach; The employing secondary fuel sprays, and is injected in the intake duct for the first time, and it is lower that this sprays concentration, can prevent that like this mixed gas from burning in intake duct; Be injected in the firing chamber and spray the second time, improves combustion efficiency thereby this design can make gas fully mix; Link rod can be designed to wind stick as required, directly produces driving force, and is simple and reasonable efficient; Can connect a plurality of pressed engines simultaneously on the main shaft, and not need to increase other accessory, can significantly improve thrust weight ratio like this; At suction port the activity safety net is installed, when aircraft in the low latitude or complex environment when flight, the closed safe net can prevent that bird and other foreign matter from entering motor and stop working, and causes the fatal crass, thereby the blade that can swing in addition on the safety net is used for regulating the power of throughput control motor; First nozzle is located in the intake duct position away from engine inner wall and prevents that fuel from touching the intake duct wall of high temperature and burn; The shaft axis in intake duct, firing chamber and tail spray road becomes 75~85 degree angles with main shaft, can prevent that like this waste gas after burning from entering intake duct.
[description of drawings]
Fig. 1 is a structure cut-away view of the present invention;
Fig. 2 is the positive diagrammatic sketch of structure of the present invention;
Fig. 3 is a perspective view of the present invention;
Fig. 4 is the structural representation of activity safety net of the present invention.
Among the figure: 1-intake duct, 2-firing chamber, 3-jet pipe, 4-thermal-protective coating, 5-first nozzle, 6-secondary spout, 7-spark plug, 8-link rod, 9-main shaft, 10-fuel channel, 11-flywheel, 12-starter motor, 13-activity safety net, 14-blade, 15-air cooling road.
[embodiment]
The present invention is further described below in conjunction with drawings and Examples.
Referring to Fig. 1, a kind of rotary punching engine, comprise body, outer wall at described body is provided with thermal-protective coating 4, this body links by link rod 8 and main shaft 9, this main shaft 9 is ptos, main shaft 9 links by flywheel and starter motor 12, and intake duct 1, the shaft axis in firing chamber 2 and tail spray road 3 becomes 10 degree angles with the surface of revolution of link rod 8, utilize starter motor 12 to make the firing chamber 2 and the relative velocity of air reach more than the 3 overtone speed, thereby reach operating conditions, air can be brought up to before entering motor 37 times at the pressure of firing chamber 2, the mixed gas of high pressure is lighted the back rapid expanding, thereby and from jet pipe 3 at a high speed ejection promote motors and advance; Intake duct 1 in chamber body is provided with first nozzle 5, is injected in the intake duct 1 for the first time, and it is lower that this sprays concentration, can prevent that like this mixed gas from burning in intake duct 1; In engine wall, be provided with air cooling road 15, prevent that engine temperature is too high; In firing chamber 2, be provided with secondary spout 6 and spark plug 7 is installed, improve combustion efficiency thereby gas is fully mixed; In described main shaft 9 and link rod 8, be provided with fuel channel 10, fuel enters first nozzle 5 and secondary spout 6 respectively by fuel channel 10,1 mouthful activity safety net 13 is housed at described intake duct, when flying in the more environment of aircraft foreign material in low latitude or air, close activity safety net 13 and can prevent that bird and other foreign matter from entering motor and stop working, cause the fatal crass, thereby the blade 14 that can swing in addition on the activity safety net 13 is used for regulating the power of throughput control motor.The present invention has starting fast, and fuel combustion is abundant, and oil consumption is low, the promotion ratio is high, propulsive efficiency height, far away, the safe and reliable advantage of voyage.The present invention can be installed on helicopter, guided missile and military or the civil aircraft; The present invention also has very big upgrading space, make improvements slightly also to being used for space shuttle, in the endoatmosphere as pressed engine, in the cosmic space as the rocket burner.

Claims (6)

1, a kind of rotary punching engine, comprise body, it is characterized in that: this body links by link rod and main shaft, and described main shaft and starter motor output shaft link, intake duct in chamber body is provided with first nozzle, is provided with the secondary spout and spark plug is installed in the firing chamber.
2, rotary punching engine as claimed in claim 1 is characterized in that: the outer wall at described body is provided with thermal-protective coating.
3, rotary punching engine as claimed in claim 1 is characterized in that: be provided with fuel channel in described main shaft and link rod.
4, as claim 1 or 3 described rotary punching engines, it is characterized in that: described main shaft links by flywheel and starter motor output shaft.
5, rotary punching engine as claimed in claim 1 or 2 is characterized in that: the shaft axis in described intrinsic intake duct, firing chamber and tail spray road becomes 75~85 degree angles with main shaft.
6, rotary punching engine as claimed in claim 5 is characterized in that: at described air inlet road junction the activity safety net is housed.
CN 200710027243 2007-03-23 2007-03-23 Rotary punching engine Pending CN101025129A (en)

Priority Applications (1)

Application Number Priority Date Filing Date Title
CN 200710027243 CN101025129A (en) 2007-03-23 2007-03-23 Rotary punching engine

Applications Claiming Priority (1)

Application Number Priority Date Filing Date Title
CN 200710027243 CN101025129A (en) 2007-03-23 2007-03-23 Rotary punching engine

Publications (1)

Publication Number Publication Date
CN101025129A true CN101025129A (en) 2007-08-29

Family

ID=38743689

Family Applications (1)

Application Number Title Priority Date Filing Date
CN 200710027243 Pending CN101025129A (en) 2007-03-23 2007-03-23 Rotary punching engine

Country Status (1)

Country Link
CN (1) CN101025129A (en)

Cited By (3)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102192045A (en) * 2010-03-05 2011-09-21 余志刚 Stamping type rotor fan engine
CN105156226A (en) * 2015-09-17 2015-12-16 东北大学 Pulsation-combustion-chamber-bearing ram engine
CN110273784A (en) * 2018-03-13 2019-09-24 姚永新 Screw eruption type engine

Cited By (4)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN102192045A (en) * 2010-03-05 2011-09-21 余志刚 Stamping type rotor fan engine
CN105156226A (en) * 2015-09-17 2015-12-16 东北大学 Pulsation-combustion-chamber-bearing ram engine
CN105156226B (en) * 2015-09-17 2017-03-01 东北大学 A kind of punching engine with intermittent combustion room
CN110273784A (en) * 2018-03-13 2019-09-24 姚永新 Screw eruption type engine

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C02 Deemed withdrawal of patent application after publication (patent law 2001)
WD01 Invention patent application deemed withdrawn after publication

Open date: 20070829