CN109236495A

CN109236495A - A kind of internal combustion aircraft jet engine

Info

Publication number: CN109236495A
Application number: CN201811333983.5A
Authority: CN
Inventors: 邹伟明
Original assignee: Individual
Current assignee: Individual
Priority date: 2018-11-10
Filing date: 2018-11-10
Publication date: 2019-01-18

Abstract

The invention discloses a kind of internal combustion aircraft jet engines.The present invention using preposition axis stream air inducing calm the anger blade fan and adherent fuel vaporization room make continuous high speed drain engine it is intracorporal head-on air compress in advance form hyperbar air stream after jet flow enter engine internal combustion chamber space, the work fuel oil being continuously pumped into, which flows through adherent spiral coil preheating oil duct and enters sealing fuel vaporization room and form gasified fuel and being continuously ejected into internal combustion chamber and form efficient oil and gas mixing continuous self-combustion, burns pressurization, and the high fever high-pressure internal combustion air-flow continuously generated rapidly sprays backward through engine nozzle to be made engine block generate continuous back pressure while also continuously actuating postposition axis stream torque revolving vane fan forward coaxial torque accelerates to rotate and engine crankshaft and preposition axis stream air inducing blade fan of calming the anger is driven to enter and forward coaxially accelerate the continuous air inducing rotated to calm the anger and internal combustion jet working condition from torque.The present invention goes back while proposing the rotary propeller type jet engines of two kinds of extension Transform Type designs and the structural design schemes of double duct internal combustion type jet engines.

Description

A kind of internal combustion aircraft jet engine

Technical field

The present invention relates to a kind of internal combustion aircraft jet engines.

Background technique

Conventional internal combustion aircraft jet engine mainly has turbojet, turbofan, turbine rotation Paddle motor and turboaxle motor several types and be all by topping turbine bleed machine, turbocompressor and oil jetting combustion room And postposition torque turbine and start machine barrel composition engine body structure and be by high pressure spray project Aviation Fuel exist To while flight before combustion gas stream propulsion aircraft body in being sprayed after the high-voltage high-speed that continuous burning generates in high pressure high flow rate air stream Also actuating postposition torque turbine rotates and coaxially drives topping turbine bleed machine or preposition propeller or extension turbine wheel shaft continuously to turn round Square rotation bleed calms the anger or continuously transfers head-on air or continuous twisting screw blade transfers air and carries out continuous promoting driving Aircraft engine, due to before jet plane takes off acceleration and subsonic speed to the forward flight of aircraft body when flight both with The proportional also rotation with the topping turbine bleed machine of engine block of interior gaseous jet propeller power at engine puff prot Rotary speed is formed proportional to the forward direction traction force of aircraft body, when the forward flight of aircraft body reaches and surpasses The airbond that heads on will be generated at engine intake end when crossing velocity of sound, as long as jet-propulsion function after the internal combustion of aircraft jet engine Rate can make aircraft body carry out the long acceleration flight for surmounting velocity of sound, and the head-on airbond level that is formed by will pass through from front to back Jet engine inner cavity duct forms the airbond level that heads on and passes through through flow velocity so as to form the topping turbine of aircraft engine The forward direction that the scarf impeller of bleed machine and preposition propeller fan and topping turbine fan continuously transfers head-on airbond air is led Draw driving force thus correspondinglyd increase the internal combustion jet-propulsion drive efficiency of engine and jet plane surpassed Velocity of sound and times supersonic speed aviation flight.

Summary of the invention

The present invention is directed to propose a kind of internal combustion aircraft jet engine simple and practical in structure.

Technical assignment of the invention is patent of invention " a kind of double speed turbine internal combustion spray once declared with applicant Gas formula aero-engine " (application number: the 2016100616173) Design of Mechanical Structure of the internal combustion aircraft jet engine proposed It is completed after scheme is modified: closing on the shaft core position extension rear molding of air inlet by dress in long straight cylindrical engine cylinder lumen The drive motor for fixing a tool tubular driving spindle and sliding sleeve inserting are with the tubular for being located in drive motor In main shaft inner cavity with engine housing cylinder close to isometric tubular center arbor and by axle center drive motor front end The setting of the tube wall of extension spindle tube body lumen wall and tubular center arbor assemblies the complementary ratchet extension of orientation and twists joint pipe torque connection Simultaneously two groups or the one group of electric driving shaft before and after fixed in parallel is arranged in axis device on hanging the periphery wall surface for turning round shaft coupling outer tube head part Stream air inducing calm the anger paddle fan and on the body inner cavity peripheral wall after drive motor is adjacent the adherent setting of ring week it is fixed to drain into sky The radius decrescence air compression chamber of compression and compressed air communication port construct and prevent high-pressure internal combustion air to gas tool at double Formed air pressure balance reflux relationship air-flow torque revolve fastly non-return paddle fan non-return mechanism and by installing be equipped with pressure under opening to The adherent fuel gasification oil spout room of high pressure spray oilhole mouth array is arranged.Body in ring all adherent fuel gasification oil spout rooms neighbour lower end It is adherent on the wall surface of inner cavity to fix the through-flow oil pipe of a solid matter helical disk tubulose fuel-firing preheating and the sealing with fuel gasification oil spout room Interior space, which is connected, flows into sealing flow through work fuel oil in advance after internal combustion chamber region carries out pre-add thermosetting high temp oil-fired Fuel gasification oil spout room in formed gasified fuel and through pressure from open high pressure spray oilhole mouth array be continuously ejected into engine Combustion chamber in carry out efficient air-fuel mixture continuous self-combustion and burn pressurization, while solid matter helical disk tubulose preheats in through-flow oil pipe The low temperature fuel oil of flowing also has absorbing and cooling temperature protective effect to the engine housing cylinder for being located at internal combustion chamber region.After closing on Axially two groups of the fixed front and back of setting or one group of axis radius are slightly larger than or are equal to preposition axis on the center machine axial plane of jet tail mouth Stream air inducing calm the anger paddle fan and use samdwich hollow perforation construct torque blade plate postposition axis stream torque rotation oar fan to utilize in Heart motor shaft torque rotation oar fan forward continuously inhales stream around the centrifugal drying stream effect that axis high torque rotates, and head-on air enters center Arbor inner cavity air flue and flow separately through the interlayer in torque revolving vane plate body perforation air flue by continuously got rid of outflow it is right by this method Center arbor and postposition axis stream torque rotation oar fan in engine internal combustion chamber region carry out air-flow cooling protection to prevent Because internal combustion air flow across heat burns the fan setting of axis stream torque rotation oar.Due to by preposition electronic axle stream air inducing calm the anger paddle fan high flow rate draw The head-on air flowed into is by the flat round adherent sealing fuel gasification oil spout locular wall center ring of box body shape along aperture and centripetal arrangement Triangle notch notched wall along 1~3 times formed be less than engine head on air inlet internal diameter plane product compressed air it is through-flow The unit plane product air velocity pressure and unit time air influx and same of 1~3 times of air compression ratio are then formed when aperture When actuate two groups of air-flow torques and revolve non-return paddle fan fastly quickly forward torque rotates to form the non-return level of high-pressure internal combustion air to make The high-pressure internal combustion air that is formed continuously in engine internal combustion chamber can only rapidly jet flow be sent as an envoy to hair via engine tail end puff prot Motivation body or aircraft body generate continuous rear jet-propulsion driving force, simultaneously flow through the high-voltage high-speed of engine tail end puff prot inner cavity Two groups of postposition axis stream torque rotation oars fan that interior combustion gas stream continuously actuates on centrally disposed arbor is sprayed to afterwards forward to accelerate around axis Torque rotate the forward axis torque rotating force to be formed then coaxially drive preposition axis stream air inducing calm the anger paddle fan accelerate torque rotation Air inducing makes preposition axis stream air inducing calm the anger paddle fan automatically after calming the anger until reaching more than drive motor nominal axes torque revolving speed power Sliding is exited the orientation ratchet adapter tube shaft coupling torque rotation relationship with drive motor and is switched to by postposition axis stream torque rotation oar The axis torque revolving speed power of fan coaxially drives preposition air inducing paddle fan of calming the anger to enter and forward accelerate the company calmed the anger of rotation air inducing from torque As long as being sprayed to after the internal combustion air that continuous oil gas mixing spontaneous combustion pressurization is formed in continuous working condition and engine combustion room The unit plane product of propeller power (the long-pending product value with unit plane product internal combustion air jet pressure of puff prot inner cavity disk) Internal combustion air jet pressure is lower than or can make no more than the through-flow air pressure of unit plane product at the through-flow aperture of compressed air Engine, which keeps being in from torque acceleration, is pivoted the continuous duty that air inducing calms the anger and accelerates internal combustion jet.Due to being in The long-pending product value with unit plane product internal combustion air jet pressure of inner cavity disk at the engine puff prot of working condition is wanted Several times are greater than the engine block preposition axis stream air inducing forward coaxial at air inlet that heads on and calm the anger the torque revolving speed power and list of paddle fan Bit plane product air introduce velocity pressure so that preposition axis stream air inducing is calmed the anger paddle fan automatically into tending to close to forward coaxial The acceleration torque rotation air inducing of postposition torque rotation oar fan torque revolving speed power, which is calmed the anger, process and to head on engine intake Air conduction speed correspondinglys increase the unit plane product air velocity pressure for also synchronizing and improving at compressed air stream openings With unit time air influx, as long as the work fuel supply amount continuously sprayed is able to satisfy air-fuel mixture in engine internal combustion chamber Spontaneous combustion is pressurized the needs of the thermal efficiency, the interior gaseous jet propeller power of engine tail portion and the axis stream torque rotation of coaxial postposition The axis torque rotary power of paddle fan can also increase accordingly therewith, which should continue to always preposition axis stream air inducing and calm the anger Paddle fan drained within the unit time until head-on air capacity is not further added by.When the aircraft body for being assembled with of the invention reaches and surpasses Crossed the engine after the forward flight of velocity of sound in aircraft body head on formed at air inlet head-on airbond level can be with one Fixed circulation traverse velocity passes through the inner cavity duct of engine block and engine jet-propulsion after continuously performance internal combustion is driven While power also performance high speed forward torque rotation preposition axis stream air inducing calm the anger paddle fan spiral beveling plate face continuously transfer The continuous forward direction that head-on sound barrier air is formed pulls driving force, therefore, the forward flight of jet plane body in addition to hair The directly proportional interior gaseous jet of the air internal combustion thermal efficiency of motivation promotes driving force to have outside proportional relation also and by the super of aircraft body The continuous forward direction drawing driving force of the engine block formed before velocity of sound to the coasting flight speed of flight is proportional to.

If heading on air inlet wall along the tubular center arbor to protract in internal combustion aircraft jet engine of the invention Four blades for fixing one group of appropriate big axis core radius and appropriate diagonal cutting plate face angle degree or more blade pre-driver spirals is arranged in head end Blade fan then can be super when large aircraft body take off acceleration flight and subsonic flight and after breakthrough sound barrier level Jet-propulsion driving force but also energy while table after so that aircraft body had not only been showed the internal combustion of engine tail portion puff prot when velocity of sound coasting flight The spiral beveling plate face continuous action of the preposition screw blade fan of the big axis core radius of existing engine heads on the company of sound barrier air formation To drawing driving force before continuous, therefore since the internal combustion aircraft jet engine that this kind has preposition screw blade fan is in aircraft To winged before the opposite inertia formed when subsonic flight and when supersonic flight from engine internal combustion jet-propulsion driving power The continuous helical that scanning frequency degree can make the preposition axis stream screw blade of engine to head-on air and head-on sound barrier air shows is oblique The plate face position that effect is transferred in cutting plate face correspondingly extends back because without making in the state that runs at high speed or propeller The peripheral velocity in leaf outer radius site be more than velocity of sound pre-driver propeller shape at " trackslipping " idle idle running phenomenon, because This, the aircraft body for being assembled with the internal combustion jet engine of this kind of pre-driver propeller can both carry out subsonic load-carrying flight The supersonic flight of head-on airbond level can also be broken through.The present invention that this kind is retrofited can be referred to as rotary propeller type internal combustion Jet aerial engine

If using the casing cylinder of internal combustion aircraft jet engine of the invention as main duct machine barrel and in main duct machine barrel Outside corresponds to the outer layer internal combustion jet machine drum body of the fixed upper major lumen radius of circle of inserting assembly as by-pass air duct machine in parallel again Cylinder simultaneously fixes the outer culvert of one group with the cavity radius corresponding matching of by-pass air duct machine barrel in the setting assembly of main duct center machine axis head end The preposition axis stream air inducing in road, which is calmed the anger, paddle fan and fixes one group with the inner cavity of by-pass air duct machine barrel tail portion partly in the setting of the tail portion of center arbor The by-pass air duct axis stream torque rotation oar of diameter corresponding matching is fanned and ring week is adherent on the machine barrel wall surface of by-pass air duct interlayer inner cavity two sides Fixed by-pass air duct air compression chamber and the setting of sealing fuel gasification oil spout room and dress is set on machine barrel wall surface on the inside of the by-pass air duct The by-pass air duct air-flow on the through-flow aperture of compressed air on by-pass air duct sealing fuel vaporization room top surface siding is floated on two groups of patches Torque revolves the main structure of the invention that non-return paddle fan then organizes duct internal combustion jet structure in pairs fastly.Due to this kind of double duct internal combustion The postposition torque rotation oar fan of center arbor is relatively high when main duct jet plane starting operation is utilized in the jet engine of structure Continuous axle torque revolving speed power simultaneously drive the preposition axis stream air inducing of coaxial by-pass air duct calm the anger paddle fan forward accelerate torque rotation The course of work continuously calmed the anger to the interlayer intracavity space air inducing of by-pass air duct is carried out, the by-pass air duct by several times compression head-on drains Air continuum is crossed two groups of by-pass air duct air-flow torques and is revolved on non-return paddle fan and the adherent fuel vaporization room plane wooden partition of by-pass air duct fastly The air-fuel mixture combustion chamber regions of compressed air is through-flow aperture enters by-pass air duct interlayer space and with the adherent fuel gasification of by-pass air duct On the wooden partition of oil spout room bottom surface wall-through by the pressure set of installing from open high pressure spray oilhole mouth array it is continuous under to the vaporization ejected Annular gap inner cavity puff prot of the by-pass air duct high-pressure internal combustion gas through by-pass air duct tail portion that fuel efficient mixing spontaneous combustion is formed Go out after continuous high speed to jet flow and merges to form this kind of double duct with interior combustion gas stream is sprayed to after the high speed of main duct internal combustion jet plane The internal combustion jet pusher of internal combustion type jet engine is into driving power.Fixed by-pass air duct solid matter is set on main duct machine barrel outer wall The tubular fuel-firing preheating of helical disk is through-flow, and oil pipe makes also to fire in by-pass air duct while circulation fuel oil pre-add thermosetting high temp oil-fired The protective effect that machine barrel on the inside of the engine in chamber region has absorbing and cooling temperature is burnt, while in the by-pass air duct machine barrel outer wall of engine It is upper be arranged fixed proper number circumference it is equidistant vertical arranged in parallel and one lead to bottom supporting rib construction thus in engine block Shell protection level between form the interlayer circulation air flue that front and back penetrates through and make head-on air in aviation flight for aircraft body Automatic high flow rate flows through interlayer space airflow channel on the outside of the by-pass air duct machine barrel of engine and carries out to engine by-pass air duct machine barrel Air-flow cooling protection.The present invention of the double duct internal combustion jet structures of the kind can be referred to as double duct internal combustion type jet engines, It can be used as the adapted aero-engine of high speed of a ship or plane bulk transport aircraft and large-scale passenger airplane.Below according to Figure of description to this The structure of invention is described in detail.

Figure of description 1 is the vertical section structure view of main body of the present invention.

Figure of description 2 is the top surface shape view for the adherent fuel gasification oil spout room that the present invention uses.

Figure of description 3 is the tail end shape view for the air-flow cooling torque rotation oar impeller that the present invention uses.

Figure of description 4 is that the complementary ratchet that the present invention uses hangs the longitudinal section view for twisting joint pipe shaft coupling.

Figure of description 5 is the configuration view at preposition propeller impeller top edge.

Figure of description 6 is the vertical section structure view of the invention of the preposition propeller setting of tool.

Figure of description 7 is the vertical section structure view of the invention of double duct internal combustion jet structures.

It is fixed centripetal arranged in parallel by being placed equidistant in ring week on an inner cavity wall surface referring to Figure of description 1,2,3,4 Four in-line support plate feet constructions (29) and protract the fixed tool tubular driving spindle (9) of rear molding in its shaft core position Thin-wall circular cylinder (28) adherent sleeve of axis stream drive motor (8) be fixed on long straight cylinder shape engine housing cylinder (24) On the round cavity barrel of middle front position, one is led in the circle of bottom with engine housing cylinder (24) close to isometric and tool one Tubular center arbor (10) gauge of chamber channel (17) and cone shape tail end (21) slides sleeve in tubular motor reel (9) the rear end axle sleeve for being located in drive motor (8) is assembled in internal diameter cavity and using rolling bearing cooperation (12) (7) The boss for neutralizing overhanging motor reel (9) the top setting of front-end shaft sleeve is shorted on the inner cavity tube wall of tubular shaft end construction (6), electricity On motivation axis (9) boss on top be shorted round tube (6) and equal calibers short and thick round tube bodily form outer tube head part (4) (36) and in Header structures part (37) in the short tubular of boss heavy wall is connect on scheming axis (10) upper top, and setting assemblies the present invention jointly The orientation complementation ratchet extension of use twists joint pipe shaft coupling (4) (Fig. 4) and front and back is set in parallel on adapter tube shaft coupling periphery tube wall (4) Set fix two groups of fixed proper number axis stream torque blade plates of (or one group) ring week equidistant arrangement axis stream air inducing calm the anger paddle fan (3) (23).The doubling of (or ten several) the ring week equidistant centripetal protrusion arrangement that will be provided with eight in a round plate face is oblique convex Frid surface construction (33) (34) and be correspondingly formed eight at (or ten number place) triangle notch notched wall it is (26) and small along construction Radius of circle ring presses dress with equidistant wall-through setting is merged with flat shape along the flat round box body shape top surface siding of hole outlet structure (27) There is proper number pressure to form sealing fuel gasification oil spout room from lower base wall panel (14) structure for opening high pressure spray oilhole mouth array Be arranged (57) and ring week it is adherent be fixed on drive motor (8) it is adjacent after appropriate location thin-wall circular cylinder (28) inner cavity wall surface On.One tool is turned to the air pressure of recessed deep gouge circumference siding (25) shape of circle in the trapezoidal radius of funnel decrescence ring week inclined-plane siding (11) The upper plate of contracting room circumferential surface siding is along the adherent appropriate location for being fixed on thin-wall circular cylinder (28) inner cavity wall surface and by its lower plate along patch Wall, which is fixed on sealing fuel gasification oil spout room (57) the about top surface siding of one third outer radius plan-position, forms ring week patch The recessed deep gouge of circle on wall sealing fuel gasification oil spout room (57) top surface siding, which is faced directly, connects air compression chamber inclined-plane week on peripheral wall (25) The peripheral wall surface construction of wall (11).In the recessed deep gouge shape wall surface structure of circle with ring week adherent sealing fuel gasification oil spout room (57) top surface Making two groups of solid matter setting assembly above and below on center arbor (10) axial plane of (Fig. 2 (25)) lateral corresponding position can independently freely The air-flow torque for rolling rotation revolves non-return paddle fan (13) fastly.It is arranged on the inner cavity wall surface of another thin-wall circular cylinder (30) and fixes A piece tubular fuel-firing preheating of solid matter helical disk is through-flow oil pipe oil supply system (16) is simultaneously solid by thin-wall circular cylinder (30) the adherent sleeve It is scheduled on the appropriate position of machine barrel (24) inner cavity wall surface and connects the tail end of through-flow oil pipe (16) after manual oil-control valve (15) It is connected with the sealing intracavity space (57) of ring all adherent fuel gasification oil spouts room.Closing on engine tail portion puff prot wall edge (22) a tool inclined-plane air guide conduit disk is fixed by dress on inner cavity wall surface, and (18) are set and in the center arbor of lateral corresponding position (10) front and back gauge setting fixes two groups on axial plane or one group of axle center radius is equal to or calms the anger paddle slightly larger than preposition axis stream air inducing The postposition axis stream torque rotation oar for fanning (3) (23) fans (19) (20), and every torque rotation oar flabellum plate (19) (20) is hollow Perforation interlayer batten shape (Fig. 3 (19) (20) (32) (31)) is simultaneously connected with the intracavity space (17) of center arbor (10).? On ring week air compression chamber (11) neighbour on thin-walled circular cylinder body (28) inner cavity peripheral wall of position ring week adherent setting fixation second level or The oily oil spout pipeline (12) of the ring week oil transportation point that person's second level and three-level afterbunring jet-propulsion need simultaneously connects through second level or second level It is connected afterwards with high pressure fuel oil pipeline with three-level manual force application oil-control valve (15) and in the oil transportation point oil spray of ring week setting It is placed equidistant with transmural on the downside of oil-piping (12) or inner tube wall and opens high pressure spray oilhole mouth certainly by an appropriate number of pressure is filled Array.By the main structure of composition described above internal combustion jet aerial engine of the invention.

Referring to Figure of description 4, using motor (8) driving spindle (9) of tubular and by tubular motor drive The tube wall of main shaft (9) extension shaft end is arranged to connect boss nipple construction (6) on pipe axial plane and will be equal with boss nipple (6) The lower end pipe of the short and thick round tube bodily form outer tube head part (4) of caliber is slided at junction along with boss nipple (6) upper pipes edge Upper and lower sides tube wall be arranged to circumference equidistant arrangement tube wall edge face structure of the parallel top rake complementation ratchet wall along shape (7).One Tubular center arbor (10) gauge that bottom round cavity is led to close to isometric and tool one in root and engine housing cylinder (24) is sliding The dynamic internal diameter cavity for being inserted through tubular motor drive main shaft (9) is simultaneously located in driving electricity using rolling bearing cooperation assembly The rear axle of motivation (8) puts on and on the inner cavity wall surface of boss nipple (6), incites somebody to action at the top of tubular motor projecting tube axis (9) The head tube wall part of tubular center arbor (10) is arranged to connect the interior tube head knot of the short round tube shape of boss heavy wall on pipe axial plane Component (37) simultaneously is arranged to the extra strong pipe wall port edge (37) of its top surface to extend out bell shape (2), in outer tube head component (4) Round tube axial plane is connect under header structures part (37) in the middle and lower part position of short and thick tube inner cavity wall surface and the short tubular of boss heavy wall (10) corresponding position respectively corresponds several parallel isometric in-line convex surface slideway constructions (36) and (5) of setting ring week equidistant arrangement simultaneously The corresponding sliding sleeve inserting of the inner cavity tube wall construction (36) of outer tube head part (4) is fitted over into header structures part in boss heavy wall short tubular (37) ring all in-line convex surface slideway (36) upper end edge and boss arranged in parallel on and on the peripheral wall of outer tube head component (4) inner cavity One is added in the glide lamella intracavity space (38) formed between the recessed lower end edge of circle of header structures part (37) in heavy wall short tubular Only the top elastic force spiral disc spring (39) of flat lath cross sectional shape is used to make the lower end pipe of short and thick round tube bodily form outer tube head part (4) It is complementary along parallel top rake of round tube (6) upper pipes between is shorted with the boss of tubular drive motor main shaft extension shaft end Sliding junction of the ratchet-shaped tube wall end along (7) is in normal elastic force extension and twists joint pipe shaft coupling state.

Referring to Figure of description 1,2,3,4,5,6, starting the overhanging center arbor in machine drum body (24) air inlet inner cavity (1) (10) upper position that complementary ratchet extension twists joint pipe shaft coupling (Fig. 4) periphery tube wall (4) is parallel to rear group of main duct drive shaft Stream air inducing calm the anger paddle fan (3) setting fix one group of appropriate big axis core radius and appropriate diagonal cutting plate face angle degree four blades or number blade The top edge of pre-driver axis stream propeller (23), each propeller impeller in pre-driver propeller (23) is to be in Outer evagination short face side plate (35) shape that plane is folded under turning straight, the parallel height of outer evagination short face side plate (35) is about propeller Outer 1/10th diametrically of fan are to improve forward direction traction force and forward direction drawing drive when preposition propeller runs at high speed Efficiency of movement and flight noise for reducing aircraft, thus form the master of rotary propeller type internal combustion jet aerial engine of the invention Body structure.The internal combustion jet engine that this kind has preposition propeller flight driving mechanism is electronic by driving in aircraft starting operation Owner's axis (10) drives preposition axis stream air inducing paddle fan (3) coaxial rotating of calming the anger to carry out continuous air inducing to head-on air and calm the anger process simultaneously High-pressure internal combustion air, which is formed, through continuous oil jetting combustion passes through one group of inclined-plane air slot in engine tail portion puff prot (22) inner cavity The inclined-plane continuous jet flow of air guide conduit of road disk (18), which goes out puff prot (22), keeps the continuous rear jet-propulsion driving force of aircraft body generation same When also to actuate two groups of postposition axis stream torque rotation oars fan (18) (19) that patch floats on after inclined-plane air guide conduit disk (18) continuous suitable It rotates to form the high forward axis torque rotary power of several times and while drive the coaxial preposition propeller of big radius of circle to torque (23) accelerate forward to make aircraft body generate continuous traction force or continuous drawing driving force around the rotation of axis torque and make aircraft Body can both carry out heavily loaded subsonic flight or carry out underloading supersonic flight.

Referring to Figure of description 1,2,3,4,7, it is placed equidistant with using one by four supporting ring weeks and is in that parallel is stretched in axle center The both sides of the face of the in-line support plate foot construction (40) of column support the inside thin-wall circular cylinder of a fixed suitable length respectively (48) and the double-layer barrel structuring of the outside thin-wall circular cylinder (41) of suitable length composition and respectively by inside thin-wall circular Cylinder (48) adherent inserting is fixed in the circumferential wall of main duct internal combustion jet machine barrel (24) middle front part position and by outside thin-walled Cylinder (41) adherent inserting is fixed in the circumferential wall of by-pass air duct internal combustion jet machine barrel (42) middle front part position.It is supported in array After plate foot (40) is adjacent fixed second level or second level are set in the inner peripheral wall of the outside cylindrical body (41) of position ring week and three-level adds The ring week fuel feed oil spout pipeline and on the downside tube wall of ring week distribution piping or inside tube that power burns that jet-propulsion needs An appropriate number of pressure is arranged from high pressure spray oilhole mouth array is opened in equidistant wall-through on wall, and reinforcing fuel oil oil pipeline, which then connects, to be handled Dynamic reinforcing oil-control valve is connected with ring week distribution piping.Orientation complementation ratchet in main duct center machine axis (10) overhanging shaft end Extension twist joint pipe shaft coupling (Fig. 4) ((Fig. 7) (4) (7)) periphery wall surface fix in back-end location ring week one group with main duct head-on into The pre-driver axis stream air inducing of port (1) cavity radius corresponding matching is calmed the anger paddle fan (3) and in shaft coupling (4) (7) periphery wall surface Fix in front position ring week one group with by-pass air duct head on air inlet (39) cavity radius corresponding matching big axis core radius it is preposition Drive shaft stream air inducing calm the anger paddle fan (23).Be placed equidistant with eight on one circular plate type top surface siding ring week (or several or ten numbers Road) the poly- heart is protruded outside stretches at the doubling lower inclined plane shape tongue wooden partition construction (34) (33) of arrangement and the eight of the alternate formation of correspondence (or at number or at ten numbers) plane triangle notch lower plate is along the ring of notch construction (26) and small radius of circle along hole outlet structure (27) formed the top surface wallboard construction (Fig. 2) of the by-pass air duct adherent fuel gasification oil spout room (51) of flat round cassette shapes and with it is flat Shape corresponding simultaneously equiblibrium mass distribution wall-through setting in face, which is pressed, is equipped with proper number pressure from unlatching high pressure spray oilhole mouth array (Fig. 2 (14)) Lower base wall panel (52) knot constitute by-pass air duct adherent sealing fuel gasification oil spout room setting (51) and ring is all adherent is fixed on outer culvert The appropriate location of road interlayer intracavity space two avris cylinder (48) (41) circumferential wall.Gradually in the trapezoidal radius of circle of funnel by a tool Subtract the upper plate edge that recessed deep gouge circumferential surface straight wall (47) the shape air compression chamber circumferential surface siding of circle is connect under inclined-plane circle wall (49) (Fig. 2 (11)) And it will be under it on all adherent outside cylindrical body (41) inner cavity wall surfaces for being fixed on the adjacent top of sealing fuel gasification oil spout room (51) of ring Plate is along the adherent plane being fixed at sealing fuel gasification oil spout room (51) top surface siding (Fig. 4 (25)) about one third outer radius Circle is connect on wooden partition and under air compression chamber wall be respectively formed in main duct intracavity space and in by-pass air duct interlayer intracavity space The wooden partition structure in sealing fuel gasification oil spout ceiling face is connect under recessed deep gouge peripheral wall.With adherent fuel gasification oil spout room (51) top surface On the lateral corresponding position of circle recessed deep gouge construction (49) inside cylindrical body (48) periphery wall surface under solid matter setting fit on Two groups of patches float on the by-pass air duct air-flow that the independence and freedom in the bottom wall plate face of the recessed deep gouge (49) of circle and in inner circumferential plate face rolls rotation Torque revolves non-return paddle fan (50) fastly.A by-pass air duct internal combustion jet is fixed in setting on the periphery wall surface of another thin-wall circular cylinder The through-flow oil pipe oil supply system (55) of solid matter helical disk tubulose fuel-firing preheating that uses and by the end of through-flow oil pipe (55) even through one Sealing intracavity space (51) after the manual oil-control valve of by-pass air duct fuel feed pump with by-pass air duct adherent fuel gasification oil spout room (52) It is connected and is fixed on this thin-walled cylinder consideration wall the appropriate location of machine barrel (24) periphery wall surface on the inside of by-pass air duct.Parallel In main duct machine barrel (24) puff prot (22) interior bottom of chamber along the tail portion axial plane of the tubular center arbor (10) of position ring week etc. One group of main duct axis stream torque rotation oar fan (19) is fixed away from setting and on the main duct inner cavity barrel (24) that upper patch trim is set It is adherent to fix tool main duct inclined-plane air guide conduit disk setting (18) by dress, in lower floating sticker main duct machine barrel (24) tail end puff prot (22) one group and by-pass air duct machine barrel (42) tail portion inner cavity are fixed in bottom ring week setting along center arbor (10) tail portion axial plane of position Half journal axle stream torque rotation oar of the big axis core fan (20) and machine barrel (24) (42) circle inside and outside by-pass air duct of radius corresponding matching Tool by-pass air duct inclined-plane air guide conduit disk setting (53) is fixed by dress in the appropriate location of peripheral wall surfaces.In the outer of by-pass air duct machine barrel (42) It is arranged in peripheral wall surfaces and fixed proper number ring week is equidistantly vertically arranged and constructs (43) through to the straight parallel column supporting rib at bottom And straight parallel column supporting rib (43) wall surface in by-pass air duct machine barrel (42) middle front part position is structurally adherent fixes an outside wall surface On be provided with for bracket stationary engine body (42) (Fig. 7) in-line prolate cylinder-shaped pipe support construction (46) circular cylinder body Part (44) and in by-pass air duct machine barrel (42) outside wall surface one lead to bottom straight parallel column supporting rib wall surface construction (43) on include Circular cylinder body part (44) outside wall surface all standing wrap one layer of body Outwall protection shell plate face (45).Thus it organizes in pairs The jet-propelled main structure of the invention of duct internal combustion.

Claims

1. a kind of internal combustion aircraft jet engine, the main structure feature of (Fig. 1) of the invention is ring week on an inner cavity wall surface The shaft core position extension rear molding for being placed equidistant with fixed centripetal four in-line support plate foot constructions (29) arranged in parallel is fixed Thin-wall circular cylinder (28) adherent sleeve of the axis stream drive motor (8) of one tool tubular driving spindle (9) is fixed on long straight On the round cavity barrel of cylinder-shaped engine housing cylinder (24) middle front part position, by one and engine housing cylinder (24) Close to it is isometric and have one lead to the tubular center arbor (10) of bottom round cavity channel (17) and cone shape tail end (21) every It is fixed to be assembled away from sliding sleeve in the internal diameter cavity of tubular motor reel (9) and using rolling bearing cooperation (12) (7) Position boss of top setting in the rear end axle sleeve of drive motor (8) and on the overhanging motor reel (9) of front-end shaft sleeve is shorted Tubular shaft end constructs on the inner cavity tube wall of (6), and the round convex shape on top is shorted round tube (6) and waits calibers on motor reel (9) Boss heavy wall short tube bodily form inner tube is connect on short and thick round tube bodily form outer tube head part (4) (36) and center arbor (10) upper top Header structure part (37) the orientation complementation ratchet extension that setting assemblies that the present invention uses jointly is twisted joint pipe shaft coupling (Fig. 4) and is being connect Pipe shaft coupling (4) periphery wall surface is arranged in parallel after going forward fixes two groups of fixed proper number axis of (or one group) ring week equidistant arrangement Stream torque blade plate axis stream air inducing calm the anger paddle fan (3) (23), be arranged on the inner cavity wall surface of another thin-wall circular cylinder (30) Fix the through-flow oil pipe oil supply system (16) of the tubular fuel-firing preheating of the solid matter helical disk and thin-wall circular cylinder (30) is adherent solid It is scheduled on the appropriate position of machine barrel (24) inner cavity wall surface and connects the tail end of through-flow oil pipe (16) after manual oil-control valve (15) It is connected with the sealing intracavity space (57) of ring all adherent fuel gasification oil spouts room, is closing on engine tail portion puff prot wall edge (22) a tool inclined-plane air guide conduit disk is fixed by dress on inner cavity wall surface, and (18) are set and in the center arbor of lateral corresponding position (10) front and back gauge setting fixes two groups of (or one or more groups of) axle center radiuses and is equal to or draws slightly larger than preposition axis stream on axial plane The postposition axis stream torque rotation oar that wind pressure gas paddle fans (3) (23) fans (19) (20), every torque rotation oar flabellum plate (19) (20) It is hollow perforation interlayer batten shape (Fig. 3 (19) (20) (32) (31)) and the intracavity space (17) with center arbor (10) It is connected.

2. by internal combustion aircraft jet engine as defined in claim 1, reinforcing oil jetting combustion jet-propulsion setting (Fig. 1) The structure feature of (Fig. 7) is thin-wall circular cylinder (28) inner cavity peripheral wall of the position after drive motor array support plate foot (29) is adjacent Ring on upper or the position after by-pass air duct interlayer inner cavity support plate foot (40) is adjacent outer avris thin-walled cylinder body (41) inner cavity peripheral wall The oily oil spout pipeline of ring week oil transportation point that the fixed second level of week adherent setting or second level and three-level afterbunring jet-propulsion need (12) and even it is connected simultaneously after second level or second level and three-level manual force application oil-control valve (15) with high pressure fuel oil pipeline Equidistant transmural is arranged an appropriate number of pressure and opens certainly on the downside of the oily oil spout pipeline (12) of ring week oil transportation point or inner tube wall High pressure spray oilhole mouth array.

3. air compresses through-flow non-return mechanism (Fig. 2) (figure by internal combustion aircraft jet engine as defined in claim 1,2 1) structure feature of (Fig. 7) is that will be provided with eight in a round plate face (or ten several) equidistant centripetal protrusion of circumference arranges Doubling oblique tongue plate face construction (33) (34) and be correspondingly formed eight at (or ten number places) triangle notch notched wall edge construct (26) and small radius of circle ring is equidistantly worn along flat round box body shape top surface siding and the flat shape of hole outlet structure (27) with merging Wall setting forms sealing fuel oil from lower base wall panel (14) structure for opening high pressure spray oilhole mouth array by equipped with proper number pressure Vaporization oil spout room setting (57) (52) and ring week it is adherent be fixed on drive motor (8) it is adjacent after appropriate location thin-wall circular cylinder (28) on inner cavity wall surface or ring week adherent is fixed on two avris thin-walled cylinder body (41) (48) of by-pass air duct interlayer intracavity space Circumferential wall on, a tool is turned into recessed deep gouge circumferential surface siding (25) shape of circle in the trapezoidal radius of funnel decrescence ring week inclined-plane siding (11) Adherent to be fixed on the outer avris of thin-wall circular cylinder (28) or by-pass air duct thin along ring week for the upper plate of the air compression chamber circumference siding of shape The inner cavity wall surface appropriate location of wall cylinder (41) and by its lower plate along it is adherent be fixed on sealing fuel gasification oil spout room (57) or The all adherent sealing fuel gasification oil spout rooms (57) of ring are formed on the top surface siding of person (51) about one third outer radius plan-position Either the recessed deep gouge of circle on the siding of (51) top surface face directly connect on peripheral wall (25) or (49) air compression chamber inclined-plane peripheral wall (11) or (47) peripheral wall surface construction, in the recessed deep gouge shape of circle with ring week adherent sealing fuel gasification oil spout room (57) or (51) top surface Wall surface constructs (Fig. 2 (25)) machine barrel either on center arbor (10) axial plane of (49) lateral corresponding position or on the inside of by-pass air duct (24) two groups of air-flow torques that independently can freely roll rotation of solid matter setting assembly revolve non-return paddle fastly up and down on the wall surface of periphery It fans (13) or (50).

4. being oriented complementary ratchet extension by internal combustion aircraft jet engine as defined in claim 1,2,3 and being twisted joint pipe shaft coupling The structure feature of (Fig. 4) is using tubular motor (8) driving spindle (9) and will be before tubular motor drive main shaft (9) The tube wall for stretching shaft end be arranged to connect on pipe axial plane boss nipple construction (6) and will caliber equal with boss nipple (6) it is short The lower end pipe of thick round tube bodily form outer tube head part (4) is along the side pipe up and down with boss nipple (6) upper pipes along sliding junction Wall be arranged to circumference equidistant arrangement tube wall edge face structure of the parallel top rake complementation ratchet wall along shape (7), one with start Tubular center arbor (10) the gauge sliding that machine casing cylinder (24) leads to bottom round cavity close to isometric and tool one is interspersed logical It crosses the internal diameter cavity of tubular motor drive main shaft (9) and is assembled using rolling bearing cooperation and be located in drive motor (8) rear axle put on tubular motor projecting tube axis (9) at the top of boss nipple (6) inner cavity wall surface on, by round tube The head tube wall part of shape center arbor (10) is arranged to connect the interior header structures part of the short round tube shape of boss heavy wall on pipe axial plane (37) and by the extra strong pipe wall port edge (37) of its top surface it is arranged to extend out bell shape (2), in the short and thick of outer tube head component (4) Round tube axial plane (10) are connect under header structures part (37) in the middle and lower part position of tube inner cavity wall surface and the short tubular of boss heavy wall Corresponding position distinguishes ring week equidistant arrangement and several parallel isometric in-line convex surface slideways constructions (36) and (5) is arranged and by outer tube head The corresponding sliding sleeve inserting of the inner cavity tube wall construction (36) of part (4) fits over the outer of header structures part (37) in the short tubular of boss heavy wall Peripheral wall surfaces ring week structurally and on the peripheral wall of outer tube head component (4) inner cavity in-line convex surface slideway (36) upper end edge arranged in parallel with In the glide lamella intracavity space (38) formed between the recessed lower end edge of circle of header structures part (37) in the short tubular of boss heavy wall The top elastic force spiral disc spring (39) of a flat lath cross sectional shape is added for making short and thick round tube bodily form outer tube head part (4) Lower end pipe is shorted oriented parallel between round tube (6) upper pipes edge along the boss with tubular drive motor main shaft extension shaft end Sliding junction of the top rake complementation ratchet-shaped tube wall end along (7) is in normal elastic force extension and twists joint pipe shaft coupling state.

5. by internal combustion aircraft jet engine as defined in claim 1,2,3,4, rotary propeller type internal combustion jet engine (Fig. 6) Main structure feature be in the head-on round tube in air inlet (1) inner cavity close to internal combustion aircraft jet engine cylinder (24) The orientation complementation ratchet of shape center arbor (Fig. 1 (4)) anterior extension end setting assembly hangs the outer tube head part for twisting joint pipe shaft coupling (Fig. 4) (4) it is placed equidistant in the rear positions ring week of periphery wall surface and fixes one group of preposition axis stream air inducing and calm the anger blade fan (3) and in outer tube The preposition axis stream spiral for fixing one group suitably big radius of circle and appropriate diagonal cutting plate face angle degree is arranged in parallel in head tube wall (4) forward position Blade fans (23), and the convex outward that the outer end plate of each propeller impeller (23) is folded under turning straight in plane is short along side plate structure It makes (20), the short parallel height along side plate (20) of convex outward is about 1/10th of propeller edge diameter.

6. by internal combustion aircraft jet engine as defined in claim 1,2,3,4, double duct internal combustion type jet engine (figures 7) main structure feature is using one by being placed equidistant with centripetal four in-line support plate heel pieces (40) arranged in parallel ring week Both sides side end face support respectively a fixed suitable length inside thin-wall circular cylinder (48) and suitable length it is outer Inside thin-wall circular cylinder (48) adherent inserting is simultaneously fixed on by the double-layer barrel structuring of side thin-wall circular cylinder (41) composition respectively It is fixed in the circumferential wall of main duct internal combustion jet machine barrel (24) middle front part position and by outside thin-wall circular cylinder (41) adherent inserting In the circumferential wall of by-pass air duct internal combustion jet machine barrel (42) middle front part position, in determining for main duct center machine axis (10) overhanging shaft end To complementary ratchet hang twist joint pipe shaft coupling (Fig. 4 Fig. 7 (4) (7)) periphery wall surface back-end location ring week setting fix one group with it is interior The head on pre-driver axis stream air inducing of air inlet (1) cavity radius corresponding matching of duct is calmed the anger paddle fan (3) and in shaft coupling (Fig. 4 Fig. 7 (4) (7)) the front position ring week setting of periphery wall surface fixes one group and heads on air inlet (39) cavity radius pair with by-pass air duct The big axis core radius pre-driver axis stream air inducing that should cooperate calm the anger paddle fan (23), be parallel to main duct machine barrel (24) puff prot (22) one group of main duct axis stream torque rotation is fixed in wall ring week setting along the tail portion axial plane of the tubular center arbor (10) of position Turn paddle fan (19) and adherent on the upper main duct inner cavity barrel (24) set of patch trim fixes a tool main duct inclined-plane air guide by dress (18) are arranged in conduit disk, at lower floating sticker main duct machine barrel (24) tail end puff prot (22) bottom along center arbor (10) tail portion of position The setting of ring week fixes one group on axial plane and the half journal axle stream of big axis core of by-pass air duct machine barrel (42) tail portion cavity radius corresponding matching is turned round Square rotation oar fan (20) is simultaneously fixed culvert outside a tool by dress in the circumferential wall appropriate location of by-pass air duct both sides side machine barrel (24) (42) (53) are arranged in air guide conduit disk in road inclined-plane, and a by-pass air duct internal combustion is fixed in setting on the periphery wall surface of another thin-wall circular cylinder The through-flow oil pipe oil supply system (55) of solid matter helical disk tubulose fuel-firing preheating that jet uses simultaneously connects the end of through-flow oil pipe (55) Sealing intracavity space after the manual oil-control valve of a by-pass air duct fuel feed pump with by-pass air duct adherent fuel gasification oil spout room (52) (51) it is connected and is fixed on this thin-walled cylinder consideration wall the appropriate location of machine barrel (24) periphery wall surface on the inside of by-pass air duct, It is arranged on the periphery wall surface of by-pass air duct machine barrel (42) and is equidistantly vertically arranged in fixed proper number ring week and through to the straight parallel at bottom Column supporting rib construct (43) and straight parallel column supporting rib (43) wall surface of by-pass air duct machine barrel (42) middle front part position structurally It is adherent to fix the in-line prolate cylinder-shaped pipe support being provided in an outside wall surface for bracket stationary engine body (42) (Fig. 7) It constructs the circular cylinder body part (44) of (46) and one in by-pass air duct machine barrel (42) outside wall surface leads to bottom straight parallel column supporting rib It includes that circular cylinder body part (44) outside wall surface all standing wraps one layer of body Outwall protection shell that wall surface, which constructs on (43), Plate face (45).