CN106948877A - Aircraft gas screwed pipe rotary engine - Google Patents
Aircraft gas screwed pipe rotary engine Download PDFInfo
- Publication number
- CN106948877A CN106948877A CN201710281816.XA CN201710281816A CN106948877A CN 106948877 A CN106948877 A CN 106948877A CN 201710281816 A CN201710281816 A CN 201710281816A CN 106948877 A CN106948877 A CN 106948877A
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- screwed pipe
- engine
- pipe rotor
- combustion chamber
- rotor
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 108
- 239000000567 combustion gas Substances 0.000 claims abstract description 31
- 239000007789 gas Substances 0.000 claims abstract description 26
- 239000000446 fuel Substances 0.000 claims abstract description 12
- 230000008859 change Effects 0.000 claims abstract description 9
- 239000002737 fuel gas Substances 0.000 claims description 10
- 238000002347 injection Methods 0.000 claims description 6
- 239000007924 injection Substances 0.000 claims description 6
- 230000003014 reinforcing effect Effects 0.000 claims description 6
- 239000000295 fuel oil Substances 0.000 claims description 5
- 230000001154 acute effect Effects 0.000 claims description 3
- 238000009826 distribution Methods 0.000 claims description 3
- 239000011229 interlayer Substances 0.000 claims description 3
- 230000007246 mechanism Effects 0.000 claims description 3
- 238000002156 mixing Methods 0.000 claims description 3
- 239000000203 mixture Substances 0.000 claims description 3
- 239000000126 substance Substances 0.000 abstract description 5
- 230000006872 improvement Effects 0.000 abstract description 2
- 230000000903 blocking effect Effects 0.000 abstract 1
- 238000010586 diagram Methods 0.000 description 8
- 238000005516 engineering process Methods 0.000 description 7
- 238000005474 detonation Methods 0.000 description 6
- 238000004134 energy conservation Methods 0.000 description 6
- 230000006870 function Effects 0.000 description 6
- 238000000034 method Methods 0.000 description 4
- 239000003921 oil Substances 0.000 description 4
- 239000007921 spray Substances 0.000 description 4
- OKTJSMMVPCPJKN-UHFFFAOYSA-N Carbon Chemical compound [C] OKTJSMMVPCPJKN-UHFFFAOYSA-N 0.000 description 3
- 229910052581 Si3N4 Inorganic materials 0.000 description 3
- 229910052799 carbon Inorganic materials 0.000 description 3
- 210000004209 hair Anatomy 0.000 description 3
- 230000008450 motivation Effects 0.000 description 3
- HQVNEWCFYHHQES-UHFFFAOYSA-N silicon nitride Chemical compound N12[Si]34N5[Si]62N3[Si]51N64 HQVNEWCFYHHQES-UHFFFAOYSA-N 0.000 description 3
- 230000008646 thermal stress Effects 0.000 description 3
- 230000001133 acceleration Effects 0.000 description 2
- 230000004323 axial length Effects 0.000 description 2
- 230000006835 compression Effects 0.000 description 2
- 238000007906 compression Methods 0.000 description 2
- 230000003628 erosive effect Effects 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
- 239000000463 material Substances 0.000 description 2
- 230000003416 augmentation Effects 0.000 description 1
- 230000004888 barrier function Effects 0.000 description 1
- 230000001413 cellular effect Effects 0.000 description 1
- 230000005465 channeling Effects 0.000 description 1
- 238000006243 chemical reaction Methods 0.000 description 1
- 238000004891 communication Methods 0.000 description 1
- 239000012141 concentrate Substances 0.000 description 1
- 238000001816 cooling Methods 0.000 description 1
- 238000005336 cracking Methods 0.000 description 1
- 239000013078 crystal Substances 0.000 description 1
- 230000006866 deterioration Effects 0.000 description 1
- 238000009792 diffusion process Methods 0.000 description 1
- 238000006073 displacement reaction Methods 0.000 description 1
- 230000000694 effects Effects 0.000 description 1
- 230000010006 flight Effects 0.000 description 1
- PCHJSUWPFVWCPO-UHFFFAOYSA-N gold Chemical compound [Au] PCHJSUWPFVWCPO-UHFFFAOYSA-N 0.000 description 1
- 239000010931 gold Substances 0.000 description 1
- 229910052737 gold Inorganic materials 0.000 description 1
- 238000010438 heat treatment Methods 0.000 description 1
- 230000007774 longterm Effects 0.000 description 1
- 229910001092 metal group alloy Inorganic materials 0.000 description 1
- 230000000149 penetrating effect Effects 0.000 description 1
- 239000000843 powder Substances 0.000 description 1
- 230000008569 process Effects 0.000 description 1
- 238000004904 shortening Methods 0.000 description 1
- 238000005507 spraying Methods 0.000 description 1
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- 239000002344 surface layer Substances 0.000 description 1
- 230000008719 thickening Effects 0.000 description 1
- 230000007306 turnover Effects 0.000 description 1
Classifications
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- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D1/00—Non-positive-displacement machines or engines, e.g. steam turbines
- F01D1/34—Non-positive-displacement machines or engines, e.g. steam turbines characterised by non-bladed rotor, e.g. with drilled holes
- F01D1/38—Non-positive-displacement machines or engines, e.g. steam turbines characterised by non-bladed rotor, e.g. with drilled holes of the screw type
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/08—Adaptations for driving, or combinations with, pumps
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D15/00—Adaptations of machines or engines for special use; Combinations of engines with devices driven thereby
- F01D15/12—Combinations with mechanical gearing
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F01—MACHINES OR ENGINES IN GENERAL; ENGINE PLANTS IN GENERAL; STEAM ENGINES
- F01D—NON-POSITIVE DISPLACEMENT MACHINES OR ENGINES, e.g. STEAM TURBINES
- F01D17/00—Regulating or controlling by varying flow
-
- F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
- F23—COMBUSTION APPARATUS; COMBUSTION PROCESSES
- F23R—GENERATING COMBUSTION PRODUCTS OF HIGH PRESSURE OR HIGH VELOCITY, e.g. GAS-TURBINE COMBUSTION CHAMBERS
- F23R3/00—Continuous combustion chambers using liquid or gaseous fuel
- F23R3/42—Continuous combustion chambers using liquid or gaseous fuel characterised by the arrangement or form of the flame tubes or combustion chambers
- F23R3/52—Toroidal combustion chambers
Abstract
The invention discloses the combustion gas screwed pipe rotary jet engine that significant improvement is made to aviation gas turbine jet engine, with a kind of screwed pipe rotor helical-screw oar or shaft generator, a kind of screwed pipe rotor fan engine and a kind of screwed pipe rotor fan boost engine derived by it, altogether five kinds of aircraft gas screwed pipe rotary engine.Using combustion gas screwed pipe rotary jet engine as core engine be all it is small and be that overall screwed pipe rotor instead of blade turbine to change energy and thin burner inner liner is replaced with toroidal combustion chamber the chemical energy of fuel is converted into heat energy with unit mass surface area, make it is high with long lifespan, few failure, low cost, reliability.There is a kind of screwed pipe rotor helical-screw oar or shaft generator, a kind of screwed pipe rotor fan engine and a kind of screwed pipe rotor fan boost engine and also have power saving advantages outside core engine advantage, making the carrier-borne aircraft of assembling screwed pipe rotor fan boost engine also safe and smooth can land and take off with catapult-launching gear without blocking.
Description
Technical field
The present invention relates to aero gas turbine engine, relate in particular to four kinds of aviation gas turbine hairs of prior art
Motivation makes the aircraft gas screwed pipe rotary engine of significant improvement.
Background technology
Aero gas turbine engine abbreviation aircraft gas engine, including turbojet, turbo-propeller hair
Motivation, turboaxle motor, four kinds of turbofan, are the major impetus devices of modern fixed wing aircraft and helicopter.
By compressor, combustion chamber and the turbojet also known as core engine for driving the gas turbine of compressor to be constituted, because
It is that, for providing high pressure, high-temperature fuel gas, therefore also known as gas generator, its excess-three machine is derived by it.
Aero gas turbine engine short life is global problem.Aero-engine is made the country prosperous according to data and shown：Russia sieve
The nominal head of this AL-31F engine turned over life-span phase up to 1000 hours, but did not reached at all during use, actually total longevity
Life only 900 hours, overhaul life only has 300 hours (this engine is used for China and destroys 10 and destroy in 11 opportunities of combat)；The U.S.
F-100, F-110 military aero-engine working life and head turn over life-span phase and are typically all up 4000 hours and 1000 hours.I
State is using single crystal turbine blade and the metallurgical turbine disk technology of integrated powder, and the Taihang voluntarily developed improves h type engine h WS10A's
Service life has reached 2000 to 3000 hours, considerably beyond Russian products.According to the instruction of about 240-300 hours every year
Practice with flying hour on duty to calculate, be accomplished by changing brand-new engine within 4 years when typically less than.Average life span can reach 20 years
As long as fighter plane for, if 4 years change once brand-new engine, it is necessary to about 5 engines, cause huge wave
Take.It can be seen that, very expensive aircraft heart --- the engine of cost, the life-span but only has trivial thousands of hours and carries out countdown, order
People is astonished and regretted.
Cause the main cause of aero gas turbine engine short life：One is to have used burner inner liner combustion chamber to come chemistry
Heat energy can be converted into；Two be to have used vane type turbine that heat energy is converted to mechanical work.
There are many obvious and hiding hidden danger as combustion chamber using burner inner liner.Burner inner liner combustion chamber is for ensuring that combustion gas whirlpool
The chemical energy of fuel is converted into the device of heat energy by turbine airborne vehicle under various state of flights.Whole engine work
Reliability, depend greatly on the reliability of combustion chamber operational.The condition of work of combustion chamber is very severe, is in height
Fast air-flow (100~150m/s) and lean mixture, very big excess air coefficient a=3.0~4.5 are lower to carry out complicated physics and chemistry
Process, when flying condition and working condition change, excess air coefficient excursion is very big, and a ＞ 40~50, surge during chop
A ＜ 0.2 during large throttle.Usual burner inner liner combustion chamber removes to undertake is converted into heat energy for driving compressor by the chemical energy of fuel
Outside, the important task of jet flight institute calorific requirement also wants burner inner liner combustion chamber to undertake, and fuel gas temperature is up to 2000 DEG C inside burner inner liner,
Volumetric heat intensity is up to (2.1x103~10.3x103kJ/m3.h.Pa), burner inner liner combustion chamber to bear HTHP, axial force and
The static load and vibration that inertia force is produced are outer, because temperature field is uneven, still suffer from thermal stress, and combustion gas heat erosion.
Such important burner inner liner combustion chamber, but its parts are but mainly thin-wall metal alloy components, occur unavoidably certainly for example：
Combustor exit local temperature is too high, and turbo blade can be caused to overheat or burn, make the poor reliability and short life of combustion chamber, meeting
The performance and functional reliability of engine is set to degenerate, the job insecurity of combustion chamber can cause to stop working, stop engine
Car.The deterioration of combustion chamber operational situation, can also influence the efficiency of engine, for example：Because combustion process tissue is bad, combustion can be made
The thermal loss increase and fuel consumption increase in room are burnt, while carbon deposit can be also produced on flame tube wall and turbo blade, fire
Carbon deposit on flame barrel makes barrel cooling variation, causes to overheat, deforms, even ftractures；Carbon deposit on turbo blade makes blade
Aeroperformance is deteriorated, and reduces turbine efficiency, and influence the balance of engine rotor.
Used vane type turbine has many-sided shortcoming heat energy is converted to mechanical work.The cross-sectional area of turbo blade is not
May be big, the ability that met with stresses under HTHP from blade tip to blade root is just very limited；The surface area of usual object unit mass
Smaller, object gets over difficult to burn, and the surface area of turbo blade unit mass is big, and temperature capacity is just limited, predestined whirlpool
Wheel is also a very fragile part.So engine will rapidly play high thrust and just be restricted, can not be square roughly with detonation
Formula obtains jet flight thrust.Jet flight institute calorific requirement will also flow through turbine, due to burner inner liner outlet temperature often
Uneven, turbine still suffers from thermal stress, and combustion gas heat erosion, so as to accelerate the shortening in its life-span.
Gas-turbine unit continues increase thrust after maximum rating is reached and is referred to as engine reinforcing.Due to burner inner liner combustion
Burn room and be arranged on engine block stage casing, turbine and the continuous enthalpy drop of free turbine are passed through in combustion gas again, and the fuel gas temperature discharged is not enough
Directly to light the fuel oil for spraying into the free turbine back side, at present, most widely used reinforcing method be turbine and jet pipe it
Between after-burner is installed, carry out reheat augmentation.And this combustion chamber equally uses thin burner inner liner combustion chamber, connect as used
Nearly rocket flight detonation mode is reinforced suddenly, and the recoil strength instantaneously produced is just not only enough to destroy whole burner inner liner afterbunring
Room, the free turbine blade that can also fracture of not doing a good job, so it is too quickly to refuel, by momentum theory Ft=mv2-mv1Understand, cause
Reinforce the rise time long.
Carrier-borne aircraft has used prior art gas turbine fan boost engine, and carrier-borne aircraft will be dropped on aircraft carrier, it is necessary to
It is equipped with and blocks carrier landing system, it is most important that the system is counted as aircraft carrier field, one technology of degree-of-difficulty factor highest.Warship
To close jet thrust during carrier aircraft landing aircraft carrier must just close together with compressor, but in order to not tangle the feelings of check cable
Under condition also can safe overshoot, throttle necessarily be in maximum position, it means that carrier-borne aircraft can not definitely shut down and it is necessary to fill up
Throttle is dropped in type aircraft carrier deck at full speed, and this requires very high, thus to trigger security incident to arresting gear and pilot
Foreign countries happen occasionally.
Carrier-borne aircraft must could smoothly take off by ejector again when being taken off from aircraft carrier.No matter steam catapult or electromagnetism
Ejector, its structure is all extremely complex, not only occupies many spaces of aircraft carrier and deadweight tonnage, can't race against time in time
Take off.
Advanced aero gas turbine engine technology is extremely sensitive and embargo the secrecy technology in various countries, from disclosure
The channel of communication, which is obtained, may not.China's aircraft gas engine technology is also very backward, to improve, and has self-reliance only.
To improve turbine engine efficiency, a kind of raising turbine engine efficiency of number of patent application 201410415779.3
Method and its device, change the screwed pipe of energy there is provided turbine rotor is replaced with the screwed pipe rotor for being equivalent to cellular type turbine first
Rotary engine, additionally provides and is combined with the compression of external displacement air with screwed pipe rotary engine as automobile engine.Specially
The sharp a kind of screwed pipe rotor of application number 201610813636.7 and its engine are there is provided single-ended or both-end screwed pipe rotor, and use it
To constitute the axial thrust that can be subject to main shaft bearing at least close to a kind of 0 screwed pipe rotary engine.
On this Research foundation, it is provided below and how solves above-mentioned technical problem technical scheme.
The content of the invention
Goal of the invention：One provides long lifespan, a kind of safe and reliable combustion gas screwed pipe rotary jet engine；Two provide the life-span
A kind of long, safe and reliable, energy-conservation screwed pipe rotor helical-screw oar or shaft generator；Three be to provide long lifespan, safe and reliable, energy-conservation,
Thrust big a kind of screwed pipe rotor fan engine and its boost engine.
A kind of combustion gas screwed pipe rotary jet engine, including turbojet, whirlpool is replaced with stairstepping screwed pipe rotor
Wheel, is provided with diffuser, the annular letter of air quantity can be adjusted by being fixed on L-shaped on casing between compressor exhaust outlet and stairstepping screwed pipe rotor
The staging pack in road and screwed pipe rotor constitutes first annular combustion chamber, and toroidal combustion chamber is at least provided with a fueling injection equipment and igniting
Device, the screwed pipe of screwed pipe rotor is from the inlet to the outlet gradually to put shape, and the air door of the annular exhausting of regulation can control to enter the first burning
The air supply of room and the air supply for flowing through the annular exhausting of screwed pipe rotor periphery, with this mechanism into gas generator, work
Flow at high speed air slows down through diffuser when making becomes the annular exhausting of high pressure air inflow L-shaped, through the eddy flow set by exhausting
Ring enters first annular combustion chamber with cyclone mode and produces high-temperature high-pressure fuel gas with fuel oil blending burning, and high-temperature high-pressure fuel gas are flowed through
Continuous change occurs for flow direction during each road screwed pipe, a part of enthalpy drop is converted to the mechanical work of driving compressor high-speed rotation,
Another part enthalpy drop is converted to the airflow speed increasing that flowing kinetic energy makes to flow to spout discharge, and aircraft obtains jet flight thrust.
Turbine is replaced with single-ended screwed pipe rotor, the annular exhausting being fixed on casing combines composition with the neck of screwed pipe rotor
Toroidal combustion chamber.
The annular exhausting that can the adjust air quantity interlayer formed that is nested together by small one and large one cylinder concentric constitutes annular
Exhausting, annular exhausting front end is provided with the supporting of fixed size cylinder, and annular exhausting rear end is provided with hundred gates of supporting size cylinder,
In clockwise and counterclockwise directions provided with radially hundred at an acute angle on the axial barrel of small cylinder between front support and hundred gates
Window whirl hole, the small drum surface of annular exhausting is cased with one and radial and axial is designed with hundred between front support and hundred gates
The L-shaped cylinder of window, the air quantity of flowing in combustion chamber can be increased and reduce and flow through screwed pipe rotor periphery annular by rotating the gate of L-shaped cylinder hundred
The air quantity of exhausting reduces the air quantity of flowing in combustion chamber and increases the air quantity that flows through the annular exhausting of screwed pipe rotor periphery.
A kind of screwed pipe rotor helical-screw oar or shaft generator, including turbo-propeller or shaft generator, with a kind of combustion gas screwed pipe
Rotary jet engine makees core engine, replaces free turbine with a free screwed pipe rotor, core engine screwed pipe rotor exhaust outlet with from
By correspondence between screwed pipe rotor screwed pipe air inlet and provided with hollow toroid distribution groove, the screwed pipe of free screwed pipe rotor is from entrance to going out
Another part enthalpy drop that core engine is discharged is also converted into driving compressor also gradually to put shape, by free screwed pipe rotor and turned at a high speed by mouth
Dynamic mechanical work.
A kind of screwed pipe rotor fan engine, including turbofan, are started with a kind of combustion gas screwed pipe rotary jet
Machine makees core engine, replaces free turbine with the free screwed pipe rotor of a stairstepping, the screwed pipe of free screwed pipe rotor is from the inlet to the outlet
Also gradually to put shape, core engine turbine exhaust mouthful and the ladder of free screwed pipe rotor are correspondingly formed scrobicular ring, then with provided with air quantity can be adjusted
The second annular exhausting constitute the second toroidal combustion chamber, the air door of the annular exhausting of regulation second can control to enter the second combustion chamber
Air supply and flow through the air supply of free screwed pipe rotor periphery, by respectively to first and second toroidal combustion chamber oil
The control of door and air door, can control the caloric value of first and second toroidal combustion chamber, screwed pipe rotor fan engine is had core engine
Maximum (top) speed output squeezing air and jet flight thrust are close to 0 or core engine maximum (top) speed output squeezing air and jet flight
Two kinds of working conditions of thrust maximum.
A kind of screwed pipe rotor fan boost engine, including turbofan boost engine, with a kind of combustion gas screwed pipe rotor
Jet engine makees core engine, replaces free turbine with the free screwed pipe rotor of a stairstepping, and the screwed pipe of free screwed pipe rotor is from entering
Mouthful to outlet also gradually to put shape, core engine turbine exhaust mouth and the ladder of free screwed pipe rotor are correspondingly formed scrobicular ring, then with provided with
The second annular exhausting of air quantity can be adjusted to constitute the second toroidal combustion chamber, the air door of the annular exhausting of regulation second can control to enter the
The air supply of two combustion chambers and the air supply for flowing through free screwed pipe rotor periphery, by respectively to first and second annular
The control of combustion chamber throttle and air door, can control the caloric value of first and second toroidal combustion chamber, with the free screwed pipe rotor screwed pipe back side
Make the 3rd combustion chamber between to the reinforcing cylinder that can adjust spout and provided with fuel injection equipment (FIE), by respectively to first and second annular
The control of combustion chamber throttle and air door, makes screwed pipe rotor fan engine have core engine maximum (top) speed output squeezing air and spray
Gas flight thrust is close to 0 or core engine maximum (top) speed output squeezing air and two kinds of working conditions of jet flight thrust maximum
Outside, by the way that swift and violent jet afterburner flying working condition can also be obtained to the 3rd combustion chamber Throttle Opening Control distributive value.
As a result of abovementioned technology, the present invention can receive following technique effect respectively.
Had the following advantages that for a kind of combustion gas screwed pipe rotary jet engine (core engine)：
1. long service life.Due to unit mass surface area it is small and be overall screwed pipe rotor instead of blade turbine come
The chemical energy of fuel and is converted into heat energy at energy by conversion with toroidal combustion chamber, just can be using abundant, high intensity, resistant to elevated temperatures
Material such as hot pressed silicon nitride (HPSN) etc. manufactures combustion chamber and turbine, instead of the thin burner inner liner combustion chamber for being easiest to damage and turbine just not
There are thermal stress issues, temperature capacity and intensity etc. are all largely increased, overcome burner inner liner combustion chamber overheat, deform, very
To cracking with burning shortcoming, the many-sided shortcoming for overcoming using vane type turbine to exist when heat energy is converted to mechanical work.
2. low cost.One overall screwed pipe rotor can be used than high temperature resistant conjunction than expensive blade turbine easy to manufacture, two
The cheap hot pressed silicon nitride (HPSN) material of gold.
3. core engine entire length is short.Because instead of burner inner liner combustion chamber with toroidal combustion chamber, the axle of toroidal combustion chamber
To length than burner inner liner combustion chamber much much shorters.
4. improve the reliability of aero-engine.There is no the thin burner inner liner combustion chamber for being easiest to damage and turbine, therefore
Barrier rate is just relative to be greatly reduced.
Had the following advantages that for a kind of screwed pipe rotor helical-screw oar or shaft generator：
1. there is a kind of combustion gas screwed pipe rotary jet engine (core engine).
2. energy-conservation.The enthalpy drop of combustion gas can be connect by selecting free screwed pipe rotor screwed pipe inlet area and its axial length
Near-atmospheric pressure and temperature.
Had the following advantages that for a kind of screwed pipe rotor fan engine：
1. there is a kind of combustion gas screwed pipe rotary jet engine (core engine).
2. realization is shared out the work and help one another, it is to avoid concentrate heating.Compressor, the second combustion chamber supervisor's jet are responsible in first combustion chamber
Flight.
3. energy-conservation.In identical compressed air require with a temperature of, turbofan is due to the combustion come out from burner inner liner
Gas working medium enthalpy have dropped many after power turbine, free turbine are converted to mechanical work, then in jet pipe by working medium
Enthalpy drop and increase the flowing kinetic energy of working medium and promote aircraft flight just to seem somewhat weak, be unfavorable for energy-conservation.Compare, the present invention
Power needed for high-pressure compressor has been responsible in first combustion chamber, and the second combustion chamber supervisor's jet flight almost can be empty all compressions
Gas is heated to high-temperature as far as possible, and is only converted to mechanical work driving low-pressure compressor by free turbine, and enthalpy drop amount less, is arranged
Go out pressure and temperature still very high, enthalpy drop is converted to flowing kinetic energy just very greatly, and jet promotes aircraft flight just to seem very strong.
4. there is provided two kinds of manipulation function selections.Make screwed pipe rotor fan engine that there is core engine maximum (top) speed output pressure
Contracting air and jet flight thrust close to 0 or core engine maximum (top) speed output squeezing air and the two of jet flight thrust maximum
Plant working condition.
Had the following advantages that for a kind of screwed pipe rotor fan boost engine：
1. there is a kind of screwed pipe rotor fan engine.
2. it can use close to the unexpected afterburner flying of rocket flight detonation mode.Because the free turbine back side and the spray of adjustable tail
Mouth is all rigid body, and without thin turbo blade and burner inner liner combustion chamber, discharge pressure and temperature are still very high, can be using freely
Turbine sprays high-temperature fuel gas and directly lights the largely three-barreled fuel oil of penetrating, is reinforced suddenly so as to obtain detonation mode.
Short distance landing shutdown can be realized during aircraft carrier 3. carrier-borne aircraft lands.Because carrier-borne aircraft lands screwed pipe can be used during aircraft carrier
Rotor fan engine has core engine maximum (top) speed output squeezing air and jet flight thrust makes engine close to 0 function
It is actual not shut down, it can go around at any time.Overcome the shortcoming occurred during existing carrier-borne aircraft landing aircraft carrier.
4. carrier-borne aircraft can be realized when being taken off from aircraft carrier realizes short field take-off using itself thrust.Because carrier-borne aircraft is from aircraft carrier
It can use from maximum (top) speed output squeezing air that jet flight thrust is pushed away close to 0 function suddenly change for jet flight when taking off
Power maximum function, then the nearly unexpected boosting function of rocket flight detonation mode of adjunction, shorten accelerator, can make carrier-borne aircraft 2
Second within acceleration to minimum takeoff speed require more than.Overcome the shortcoming occurred when existing carrier-borne aircraft takes off from aircraft carrier.
Brief description of the drawings
The specification schematic diagram that the present invention is provided is described in further detail below.
Fig. 1 is a kind of combustion gas screwed pipe rotary jet engine (i.e. core engine) schematic diagram.
In Fig. 1,1. engine crankcases, 2. compressor blades, 3. compressor rotors, 4. rotating shafts, 5. diffusers, 6.L shape energy
Adjust the annular exhausting of air quantity, 7. first annular combustion chambers, 8. stairstepping screwed pipe rotors, 9. screwed pipe exhaust outlets, 10. jet pipes, 11.
Igniter, 12. throttles, 13. fuel pumps.
Fig. 2 is a kind of screwed pipe rotor helical-screw oar or shaft generator schematic diagram.
In Fig. 2,1. engine crankcases, 2. compressor blades, 3. compressor rotors, 4. propeller shafts or rotating shaft, 5. diffusions
Device, 6.L shapes can adjust the annular exhausting of air quantity, and 7. first annular combustion chambers, 8. stairstepping screwed pipe rotors, 9. hollow toroids match somebody with somebody channeling
Groove, 10. free stairstepping screwed pipe rotors, 11. jet pipes, 12. igniters, 13. throttles, 14. fuel pumps.
Fig. 3 is a kind of screwed pipe rotor fan engine schematic diagram using two-spool compressor structure.
In Fig. 3,1. engine crankcases, 2. high-pressure compressors, 3. low-pressure compressors, 4. diffusers, 5.L shapes can adjust air quantity
First annular exhausting, 6. first annular combustion chambers, 7. annular exhausting, 8. stairstepping screwed pipe rotors, 9. can adjust the second ring of air quantity
Shape exhausting, 10. second toroidal combustion chambers, 11. free stairstepping screwed pipe rotors, 12. jet pipes, 13. second igniters, 14.
Second toroidal combustion chamber throttle, 15. first igniters, 16. first annular combustion chamber throttles, 17. oil pumps.
Fig. 4 is a kind of screwed pipe rotor fan boost engine schematic diagram using two-spool compressor structure.
In Fig. 4,1. engine crankcases, 2. high-pressure compressors, 3. low-pressure compressors, 4. diffusers, 5.L shapes can adjust air quantity
First annular exhausting, 6. first annular combustion chambers, 7. annular exhausting, 8. stairstepping screwed pipe rotors, 9. can adjust the second ring of air quantity
Shape exhausting, 10. second toroidal combustion chambers, 11. free stairstepping screwed pipe rotors, 12. can adjust the reinforcing cylinder of spout, 13. second
Igniter, 14. second toroidal combustion chamber throttles, 15. first igniters, 16. first annular combustion chamber throttles, 17. oil pumps,
18. reinforce throttle, 19. after-burners.
Fig. 5 is a kind of combustion gas screwed pipe rotary jet engine (i.e. core engine) schematic diagram using single-ended screwed pipe rotor.
In Fig. 5,1. engine crankcases, 2. compressor blades, 3. compressor rotors, 4. rotating shafts, 5. diffusers, 6. can adjust wind
The annular exhausting of amount, 7. first annular combustion chambers, 8. single-ended screwed pipe rotors, 9. screwed pipe exhaust outlets, 10. jet pipes, 11. igniting dresses
Put, 12. throttles, 13. fuel pumps.
Fig. 6 is the side schematic view of ladder screwed pipe rotor.
In Fig. 6,1. ladder screwed pipe rotors, 2. screwed pipe rotor ladders, 3. ladder screwed pipe rotors front, 4. ladder screwed pipe rotors
Axis hole, 5. ladder screwed pipe rotor rear faces.
Fig. 7 is the front schematic view of ladder screwed pipe rotor.
In Fig. 7,1. ladder screwed pipe rotors, 2. ladders, 3. toroidal combustion chamber walls, 4. screwed pipe entrances, 5. high-pressure compressors
Rotating shaft, 6. low-pressure compressor rotating shafts.
Fig. 8 is the schematic rear view of ladder screwed pipe rotor.
In Fig. 8,1. ladder screwed pipe rotors, 2. gradually put rear screwed pipe outlet, and 3. high-pressure compressor rotating shafts, 4. low-pressure compressors turn
Axle.
Fig. 9 is the schematic diagram for the annular exhausting that L-shaped can adjust air quantity.
In Fig. 9,1. first annular combustion chamber side covers, 2. annular exhausting large cylinders, the 3. annular small cylinders of exhausting and its hundred
Window whirl hole.
Figure 10 is the axial schematic diagram for the annular exhausting that L-shaped can adjust air quantity.
In Figure 10,1. annular exhausting large cylinders, hundred gates of 2. supporting size cylinders, the 3. annular small cylinders of exhausting and its hundred
Piece window whirl hole, 4.L shapes can adjust the annular exhausting of air quantity and the running clearance of ladder screwed pipe rotor, 5. first annular combustion chambers
Side cover.
Embodiment
The embodiment to the present invention is described in further detail again below.
A kind of combustion gas screwed pipe rotary jet engine, including turbojet, whirlpool is replaced with stairstepping screwed pipe rotor
Wheel, is provided with diffuser, the annular letter of air quantity can be adjusted by being fixed on L-shaped on casing between compressor exhaust outlet and stairstepping screwed pipe rotor
The staging pack in road and screwed pipe rotor constitutes first annular combustion chamber, and toroidal combustion chamber is at least provided with a fueling injection equipment and igniting
Device, the screwed pipe of screwed pipe rotor is from the inlet to the outlet gradually to put shape, and the air door of the annular exhausting of regulation can control to enter the first burning
The air supply of room and the air supply for flowing through the annular exhausting of screwed pipe rotor periphery, with this mechanism into gas generator, work
Flow at high speed air slows down through diffuser when making becomes the annular exhausting of high pressure air inflow L-shaped, through the eddy flow set by exhausting
Ring enters first annular combustion chamber with cyclone mode and produces high-temperature high-pressure fuel gas with fuel oil blending burning, and high-temperature high-pressure fuel gas are flowed through
Continuous change occurs for flow direction during each road screwed pipe, a part of enthalpy drop is converted to the mechanical work of driving compressor high-speed rotation,
Another part enthalpy drop is converted to the airflow speed increasing that flowing kinetic energy makes to flow to spout discharge, and aircraft obtains jet flight thrust.
A kind of combustion gas screwed pipe rotary jet engine is as turbojet, with different parts, with regard to that can turn into
Different types of engine, thus referred to as core engine or gas generator.
Screwed pipe rotor using described in number of patent application 201610813636.7 preferably screwed pipe inclined-plane and axial angle into
45 °, the screwed pipe for switching flow energy is located at the single-ended screwed pipe rotor of built-in screwed pipe cylinder surface layer to make stairstepping into, with
Being fixed on L-shaped on casing can adjust the annular exhausting of air quantity to constitute first annular combustion chamber with the staging pack of screwed pipe rotor.L-shaped energy
The L-shaped anchor ring of the annular exhausting of air quantity is adjusted, the wall that combination constitutes first annular combustion chamber is act as.L-shaped anchor ring and stairstepping
There is running clearance in screwed pipe rotor.
Turbine is such as replaced using single-ended screwed pipe rotor, then is fixed on the annular exhausting on casing and the neck group of screwed pipe rotor
Close and constitute toroidal combustion chamber.
L-shaped can adjust the annular exhausting and screwed pipe rotor of air quantity all to can use long-term resistance to 1300 DEG C of hot pressed silicon nitride (HPSN)s manufacture, L-shaped energy
Adjust the annular exhausting of air quantity to do abundant point as far as possible, make the surface area of unit mass small, increase heat-resisting ability.
Screwed pipe accumulates gradually to put shape from air inlet to exhaust cross section, combustion gas is fully expanded in screwed pipe.According to
Compressor requires the power and rotating speed of screwed pipe rotary engine output, and total output is obtained with the formula of power=moment of torsion * rotating speeds/9550
Total output moment of couple, is divided into the n moment of couple, is exactly even arm, 1/n further according to the distance between the symmetrical two air inlets center of circle by the moment of couple
Total even arms of the moment of couple=power *, the compressed air pressure of compressor output, power=pressure * areas, with regard to each screwed pipe air inlet can be obtained
Open area.Rotor circumference is divided into number under proof strength more, i.e., total output moment of couple is divided into multiple power as far as possible
Even square, more can reduce air inlet open area, just can shorten screwed pipe rotary engine length, can reduce toroidal combustion chamber concave panel deep
Degree.Calculated each screwed pipe air inlet open area is that driving compressor requires screwed pipe rotor hair when reaching certain parameter value flow and pressure
The minimum screwed pipe inlet area of motivation, will make a part of enthalpy drop be converted to the mechanical work of driving compressor high-speed rotation, another portion
Point enthalpy drop makes the airflow speed increasing for flowing to spout discharge, and aircraft obtains jet flight thrust it is necessary to jet flight thrust as requested
Size is increased to screwed pipe inlet area, while the chemical energy of fuel is converted into the power of heat energy by increase.
The annular exhausting that can the adjust air quantity interlayer formed that is nested together by small one and large one cylinder concentric constitutes annular
Exhausting, annular exhausting front end is provided with the supporting of fixed size cylinder, and annular exhausting rear end is provided with hundred gates of supporting size cylinder,
In clockwise and counterclockwise directions provided with radially hundred at an acute angle on the axial barrel of small cylinder between front support and hundred gates
Window whirl hole, the small drum surface of annular exhausting is cased with one and radial and axial is designed with hundred between front support and hundred gates
The L-shaped cylinder of window, the air quantity of flowing in combustion chamber can be increased and reduce and flow through screwed pipe rotor periphery annular by rotating the gate of L-shaped cylinder hundred
The air quantity of exhausting reduces the air quantity of flowing in combustion chamber and increases the air quantity that flows through the annular exhausting of screwed pipe rotor periphery.
A kind of screwed pipe rotor helical-screw oar or shaft generator, including turbo-propeller or shaft generator, with a kind of combustion gas screwed pipe
Rotary jet engine makees core engine, replaces free turbine with a free screwed pipe rotor, core engine screwed pipe rotor exhaust outlet with from
By correspondence between screwed pipe rotor screwed pipe air inlet and provided with hollow toroid distribution groove, the screwed pipe of free screwed pipe rotor is from entrance to going out
Another part enthalpy drop that core engine is discharged is also converted into driving compressor also gradually to put shape, by free screwed pipe rotor and turned at a high speed by mouth
Dynamic mechanical work.
The screwed pipe entrance gross area of free screwed pipe rotor is at least greater than or equal to the core engine screwed pipe rotor outlet gross area.
Because the runner length of screwed pipe rotor can be by thickening the axial length of core engine screwed pipe rotor and free screwed pipe rotor
To obtain, the enthalpy drop of such combustion gas working medium is just changed as far as possible, and the weary gas of discharge reaches with regard to that can be down to close to normal temperature and pressure
Energy-conservation purpose.
A kind of screwed pipe rotor fan engine, including turbofan, are started with a kind of combustion gas screwed pipe rotary jet
Machine makees core engine, replaces free turbine with the free screwed pipe rotor of a stairstepping, the screwed pipe of free screwed pipe rotor is from the inlet to the outlet
Also gradually to put shape, core engine turbine exhaust mouthful and the ladder of free screwed pipe rotor are correspondingly formed scrobicular ring, then with provided with air quantity can be adjusted
The second annular exhausting constitute the second toroidal combustion chamber, the air door of the annular exhausting of regulation second can control to enter the second combustion chamber
Air supply and flow through the air supply of free screwed pipe rotor periphery, by respectively to first and second toroidal combustion chamber oil
The control of door and air door, can control the caloric value of first and second toroidal combustion chamber, screwed pipe rotor fan engine is had core engine
Maximum (top) speed output squeezing air and jet flight thrust are close to 0 or core engine maximum (top) speed output squeezing air and jet flight
Two kinds of working conditions of thrust maximum.
The screwed pipe entrance gross area of free screwed pipe rotor is at least greater than or equal to the core engine screwed pipe rotor outlet gross area.
Second annular exhausting with it is foregoing can adjust the annular exhausting structure of air quantity as.
During aircraft landing, damper makes the first shape combustion chamber throttle be at maximum position, the second shape combustion chamber throttle
In idle position, at this moment, the equivalent screwed pipe rotor helical-screw oar of screwed pipe rotor fan engine working condition or shaft generator work shape
Whole enthalpy drops, are converted to shaft work by state, make screwed pipe rotor fan engine there is core engine maximum (top) speed output squeezing air and
Jet flight thrust is close to 0.
When taking off, damper makes the first shape combustion chamber throttle be in maximum position, the second shape combustion chamber throttle
Maximum position is at, at this moment, core engine maximum (top) speed output squeezing air and jet flight thrust are maximum.
A kind of screwed pipe rotor fan boost engine, including turbofan boost engine, with a kind of combustion gas screwed pipe rotor
Jet engine makees core engine, replaces free turbine with the free screwed pipe rotor of a stairstepping, and the screwed pipe of free screwed pipe rotor is from entering
Mouthful to outlet also gradually to put shape, core engine turbine exhaust mouth and the ladder of free screwed pipe rotor are correspondingly formed scrobicular ring, then with provided with
The second annular exhausting of air quantity can be adjusted to constitute the second toroidal combustion chamber, the air door of the annular exhausting of regulation second can control to enter the
The air supply of two combustion chambers and the air supply for flowing through free screwed pipe rotor periphery, by respectively to first and second annular
The control of combustion chamber throttle and air door, can control the caloric value of first and second toroidal combustion chamber, with the free screwed pipe rotor screwed pipe back side
Make the 3rd combustion chamber between to the reinforcing cylinder that can adjust spout and provided with fuel injection equipment (FIE), by respectively to first and second annular
The control of combustion chamber throttle and air door, makes screwed pipe rotor fan engine have core engine maximum (top) speed output squeezing air and spray
Gas flight thrust is close to 0 or core engine maximum (top) speed output squeezing air and two kinds of working conditions of jet flight thrust maximum
Outside, by the way that swift and violent jet afterburner flying working condition can also be obtained to the 3rd combustion chamber Throttle Opening Control distributive value.
During aircraft AB takeoff, damper makes the first shape combustion chamber throttle be in maximum position, suddenly fires the second shape
Burn room and the 3rd combustion chamber throttle is also provided with being in maximum position, jet flight thrust is by being jet flight close to 0 suddenly change
Thrust maximum, then the nearly unexpected boosting function of rocket flight detonation mode of adjunction, shorten accelerator, can make carrier-borne aircraft 2 seconds
Within acceleration to minimum takeoff speed requirement more than, realize utilize self power short field take-off.
Claims (6)
1. a kind of combustion gas screwed pipe rotary jet engine, including turbojet, it is characterized in that：With stairstepping screwed pipe rotor
Instead of turbine, diffuser is provided between compressor exhaust outlet and stairstepping screwed pipe rotor, air quantity can be adjusted by being fixed on L-shaped on casing
Annular exhausting and the staging pack of screwed pipe rotor constitute first annular combustion chamber, and toroidal combustion chamber is at least provided with a fueling injection equipment
And igniter, the screwed pipe of screwed pipe rotor is from the inlet to the outlet gradually to put shape, the air door of the annular exhausting of regulation, can control to enter the
The air supply of one combustion chamber and the air supply for flowing through the annular exhausting of screwed pipe rotor periphery, occur with this mechanism into combustion gas
Device, flow at high speed air slows down through diffuser during work becomes the annular exhausting of high pressure air inflow L-shaped, through set by exhausting
Cyclone ring enters first annular combustion chamber with cyclone mode and produces high-temperature high-pressure fuel gas, high-temperature high-pressure fuel gas with fuel oil blending burning
Continuous change occurs for flow direction when flowing through each road screwed pipe, a part of enthalpy drop is converted to the machinery of driving compressor high-speed rotation
Work(, another part enthalpy drop is converted to the airflow speed increasing that flowing kinetic energy makes to flow to spout discharge, and aircraft obtains jet flight thrust.
2. a kind of combustion gas screwed pipe rotary jet engine according to claim 1, it is characterized in that：With single-ended screwed pipe rotor generation
For turbine, the annular exhausting being fixed on casing combines composition toroidal combustion chamber with the neck of screwed pipe rotor.
3. the annular exhausting of air quantity can be adjusted described in a kind of combustion gas screwed pipe rotary jet engine according to claim 1,2,
It is characterized in that：The annular exhausting that can the adjust air quantity interlayer formed that is nested together by small one and large one cylinder concentric constitutes annular
Exhausting, annular exhausting front end is provided with the supporting of fixed size cylinder, and annular exhausting rear end is provided with hundred gates of supporting size cylinder,
In clockwise and counterclockwise directions provided with radially hundred at an acute angle on the axial barrel of small cylinder between front support and hundred gates
Window whirl hole, the small drum surface of annular exhausting is cased with one and radial and axial is designed with hundred between front support and hundred gates
The L-shaped cylinder of window, the air quantity of flowing in combustion chamber can be increased and reduce and flow through screwed pipe rotor periphery annular by rotating the gate of L-shaped cylinder hundred
The air quantity of exhausting reduces the air quantity of flowing in combustion chamber and increases the air quantity that flows through the annular exhausting of screwed pipe rotor periphery.
4. a kind of screwed pipe rotor helical-screw oar or shaft generator, including turbo-propeller or shaft generator, it is characterized in that：With one kind combustion
Gas screwed pipe rotary jet engine makees core engine, and free turbine, the exhaust of core engine screwed pipe rotor are replaced with a free screwed pipe rotor
Mouthful corresponding between free screwed pipe rotor screwed pipe air inlet and be provided with hollow toroid distribution groove, the screwed pipe of free screwed pipe rotor is from entering
Mouth, also gradually to put shape, is also converted into another part enthalpy drop that core engine is discharged by free screwed pipe rotor to drive compressor to outlet
The mechanical work of high-speed rotation.
5. a kind of screwed pipe rotor fan engine, including turbofan, it is characterized in that：Sprayed with a kind of combustion gas screwed pipe rotor
Gas engine makees core engine, replaces free turbine with the free screwed pipe rotor of a stairstepping, and the screwed pipe of free screwed pipe rotor is from entrance
To outlet also gradually to put shape, core engine turbine exhaust mouthful and the ladder of free screwed pipe rotor are correspondingly formed scrobicular ring, then with provided with energy
The second annular exhausting of air quantity is adjusted to constitute the second toroidal combustion chamber, the air door of the annular exhausting of regulation second can control to enter second
The air supply of combustion chamber and the air supply for flowing through free screwed pipe rotor periphery, by being fired respectively to first and second annular
The control of room throttle and air door is burnt, the caloric value of first and second toroidal combustion chamber can be controlled, there is screwed pipe rotor fan engine
Core engine maximum (top) speed output squeezing air and jet flight thrust is sprayed close to 0 or core engine maximum (top) speed output squeezing air
Two kinds of working conditions of gas flight thrust maximum.
6. a kind of screwed pipe rotor fan boost engine, including turbofan boost engine, it is characterized in that：With a kind of combustion gas spiral shell
Pipe rotary jet engine makees core engine, and free turbine, the spiral shell of free screwed pipe rotor are replaced with the free screwed pipe rotor of a stairstepping
Pipe is from the inlet to the outlet also gradually to put shape, and the ladder of core engine turbine exhaust mouthful and free screwed pipe rotor is correspondingly formed scrobicular ring, then
With provided with the second annular exhausting of air quantity can be adjusted to constitute the second toroidal combustion chamber, adjusting the air door of the second annular exhausting, can control
Into the second combustion chamber air supply and flow through the air supply of free screwed pipe rotor periphery, by respectively to first,
The control of second ring combustion chamber throttle and air door, can control the caloric value of first and second toroidal combustion chamber, with free screwed pipe rotor spiral shell
Make the 3rd combustion chamber between the pipe back side to the reinforcing cylinder that can adjust spout and provided with fuel injection equipment (FIE), by respectively to first,
The control of second ring combustion chamber throttle and air door, makes screwed pipe rotor fan engine have core engine maximum (top) speed output squeezing empty
Gas and jet flight thrust are close to 0 or core engine maximum (top) speed output squeezing air and two kinds of works of jet flight thrust maximum
Make outside state, by the way that swift and violent jet afterburner flying working condition can also be obtained to the 3rd combustion chamber Throttle Opening Control distributive value.
Priority Applications (5)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201810199315.1A CN108518247B (en) | 2017-04-15 | 2017-04-15 | Spiral-tube rotor fan boost engine |
| CN201810199366.4A CN108518248A (en) | 2017-04-15 | 2017-04-15 | A kind of screwed pipe rotor helical-screw paddle motor |
| CN201810199367.9A CN108487947B (en) | 2017-04-15 | 2017-04-15 | Spiral tube rotor fan engine |
| CN201810199314.7A CN108518246A (en) | 2017-04-15 | 2017-04-15 | A kind of screwed pipe rotor spindle engine |
| CN201710281816.XA CN106948877B (en) | 2017-04-15 | 2017-04-15 | Aircraft gas screwed pipe rotary engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201710281816.XA CN106948877B (en) | 2017-04-15 | 2017-04-15 | Aircraft gas screwed pipe rotary engine |
Related Child Applications (4)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810199314.7A Division CN108518246A (en) | 2017-04-15 | 2017-04-15 | A kind of screwed pipe rotor spindle engine |
| CN201810199367.9A Division CN108487947B (en) | 2017-04-15 | 2017-04-15 | Spiral tube rotor fan engine |
| CN201810199366.4A Division CN108518248A (en) | 2017-04-15 | 2017-04-15 | A kind of screwed pipe rotor helical-screw paddle motor |
| CN201810199315.1A Division CN108518247B (en) | 2017-04-15 | 2017-04-15 | Spiral-tube rotor fan boost engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106948877A true CN106948877A (en) | 2017-07-14 |
| CN106948877B CN106948877B (en) | 2018-06-05 |
Family
ID=59477602
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810199315.1A Expired - Fee Related CN108518247B (en) | 2017-04-15 | 2017-04-15 | Spiral-tube rotor fan boost engine |
| CN201810199314.7A Withdrawn CN108518246A (en) | 2017-04-15 | 2017-04-15 | A kind of screwed pipe rotor spindle engine |
| CN201710281816.XA Expired - Fee Related CN106948877B (en) | 2017-04-15 | 2017-04-15 | Aircraft gas screwed pipe rotary engine |
| CN201810199367.9A Expired - Fee Related CN108487947B (en) | 2017-04-15 | 2017-04-15 | Spiral tube rotor fan engine |
| CN201810199366.4A Withdrawn CN108518248A (en) | 2017-04-15 | 2017-04-15 | A kind of screwed pipe rotor helical-screw paddle motor |
Family Applications Before (2)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810199315.1A Expired - Fee Related CN108518247B (en) | 2017-04-15 | 2017-04-15 | Spiral-tube rotor fan boost engine |
| CN201810199314.7A Withdrawn CN108518246A (en) | 2017-04-15 | 2017-04-15 | A kind of screwed pipe rotor spindle engine |
Family Applications After (2)
| Application Number | Title | Priority Date | Filing Date |
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| CN201810199367.9A Expired - Fee Related CN108487947B (en) | 2017-04-15 | 2017-04-15 | Spiral tube rotor fan engine |
| CN201810199366.4A Withdrawn CN108518248A (en) | 2017-04-15 | 2017-04-15 | A kind of screwed pipe rotor helical-screw paddle motor |
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| CN (5) | CN108518247B (en) |
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2019228199A1 (en) * | 2018-05-29 | 2019-12-05 | You Tao | Turbine and spiral pipe gas turbine |
| CN111779549A (en) * | 2020-07-08 | 2020-10-16 | 孙涛 | Aircraft engine tail nozzle |
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- 2017-04-15 CN CN201710281816.XA patent/CN106948877B/en not_active Expired - Fee Related
- 2017-04-15 CN CN201810199367.9A patent/CN108487947B/en not_active Expired - Fee Related
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Also Published As
| Publication number | Publication date |
|---|---|
| CN108518246A (en) | 2018-09-11 |
| CN108518247A (en) | 2018-09-11 |
| CN108518247B (en) | 2020-03-31 |
| CN108518248A (en) | 2018-09-11 |
| CN108487947B (en) | 2020-04-21 |
| CN106948877B (en) | 2018-06-05 |
| CN108487947A (en) | 2018-09-04 |
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Effective date of registration: 20190314 Address after: Room 2A011, Innovation and Entrepreneurship Service Center, Construction Road, Zhaoqing High-tech Zone, Guangdong Province Patentee after: Zhaoqing High-tech Zone Partner Automobile Technology Co.,Ltd. Address before: 526200 No. 7, No. 14, No. 1 Lane, Taoli Xinyuan, Dongcheng District, Sihui City, Zhaoqing City, Guangdong Province Patentee before: Luo Xianping |
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