CN106948877B - Aircraft gas screwed pipe rotary engine - Google Patents
Aircraft gas screwed pipe rotary engine Download PDFInfo
- Publication number
- CN106948877B CN106948877B CN201710281816.XA CN201710281816A CN106948877B CN 106948877 B CN106948877 B CN 106948877B CN 201710281816 A CN201710281816 A CN 201710281816A CN 106948877 B CN106948877 B CN 106948877B
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- screwed pipe
- engine
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- annular
- pipe rotor
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- 238000002485 combustion reaction Methods 0.000 claims abstract description 97
- 239000000567 combustion gas Substances 0.000 claims abstract description 28
- 239000002737 fuel gas Substances 0.000 claims description 10
- 230000008859 change Effects 0.000 claims description 6
- 239000000295 fuel oil Substances 0.000 claims description 5
- 238000002347 injection Methods 0.000 claims description 5
- 239000007924 injection Substances 0.000 claims description 5
- 230000001154 acute effect Effects 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
- 239000007789 gas Substances 0.000 abstract description 23
- 239000000446 fuel Substances 0.000 abstract description 11
- 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
- 230000006870 function Effects 0.000 description 6
- 230000003014 reinforcing effect Effects 0.000 description 5
- 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
- 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
- 238000009826 distribution Methods 0.000 description 2
- 230000003628 erosive effect Effects 0.000 description 2
- 210000004209 hair Anatomy 0.000 description 2
- 238000004519 manufacturing process Methods 0.000 description 2
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- 230000007306 turnover Effects 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
- 230000006835 compression Effects 0.000 description 1
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- 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
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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
Landscapes
- Engineering & Computer Science (AREA)
- Mechanical Engineering (AREA)
- General Engineering & Computer Science (AREA)
- Chemical & Material Sciences (AREA)
- Combustion & Propulsion (AREA)
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention discloses combustion gas screwed pipe rotary jet engines significant improvement is made to aviation gas turbine jet engine formed, with derived by it a kind of screwed pipe rotor helical-screw paddle or shaft generator, a kind of a kind of screwed pipe rotor fan engine and screwed pipe rotor fan boost engine, amount to five kinds of aircraft gas screwed pipe rotary engine.All be small with unit mass surface area using combustion gas screwed pipe rotary jet engine by core engine and be that whole screwed pipe rotor instead of blade turbine converts energy and replace thin burner inner liner with toroidal combustion chamber that the chemical energy of fuel is converted into thermal energy, make it with long lifespan, failure is few, low cost, reliability are high.A kind of screwed pipe rotor helical-screw paddle or shaft generator, a kind of a kind of screwed pipe rotor fan engine and screwed pipe rotor fan boost engine is made to have the advantages that there be power saving advantages outside core engine, makes 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 engines, relate in particular to four kinds of aviation gas turbine hairs of the prior art
Motivation makes the aircraft gas screwed pipe rotary engine of significant improvement.
Background technology
Aero gas turbine engine abbreviation aircraft gas engine is sent out including turbojet, turbo-propeller
Motivation, turboaxle motor, four kinds of turbofan are the major impetus devices of modern fixed wing aircraft and helicopter.
The turbojet being made of the gas turbine of compressor, combustion chamber and driving compressor is also known as core engine, because
It is for providing high pressure, high-temperature fuel gas, therefore also known as gas generator, and excess-three machine is derived by it.
Aero gas turbine engine short life is global problem.It makes the country prosperous and shows to aero-engine according to data：Russia sieve
The nominal head of this AL-31F engine turn over service life phase up to 1000 it is small when, however use during be not achieved at all, actually total longevity
Life only 900 it is small when, overhaul life only have 300 it is small when (this engine be used for China destroy 10 and destroy in 11 opportunities of combat)；The U.S.
F-100, F-110 military aero-engine working life and head turn over service life phase it is general be all up 4000 it is small when and 1000 it is small when.I
State uses single crystal turbine blade and integrated powder metallurgy turbine disk technology, and the Taihang voluntarily developed improves h type engine h WS10A's
Service life reached 2000 to 3000 it is small when, considerably beyond Russian products.According to instruction when about 240-300 is small every year
Practice with flying hour on duty to calculate, brand-new engine is just needed replacing within 4 years when being typically less than.Average life span can reach 20 years
As long as fighter plane for, if 4 years replace once brand-new engine, it is necessary to which about 5 engines cause huge wave
Take.As it can be seen that aircraft heart --- the engine that cost is very expensive, the service life but only has trivial thousands of hours and carries out countdown, order
People is astonished and regrets.
The main reason for causing aero gas turbine engine short life：First, burner inner liner combustion chamber is used to come chemistry
Thermal energy can be converted into；Second is that use vane type turbine that thermal energy is converted to mechanical work.
Making combustion chamber using burner inner liner, there are many apparent and hiding hidden danger.Burner inner liner combustion chamber is for ensuring that combustion gas whirlpool
The chemical energy of fuel is converted into the device of thermal energy by turbine aircraft under various state of flights.Entire engine work
Reliability, depend greatly on the reliability of combustion chamber operational.The operating condition 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 thermal 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 high temperature and pressure, axial force and
The static load and vibration that inertia force generates are outer, since temperature field is uneven, still suffer from the heat erosion of thermal stress and combustion gas.
So important burner inner liner combustion chamber, but its parts are mainly but thin-wall metal alloy components, are inevitably present with certainly for example：
Combustor exit local temperature is excessively 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 for making engine degenerate, the job insecurity of combustion chamber, can cause to stop working, stop engine
Vehicle.The deterioration of combustion chamber operational situation can also influence the efficiency of engine, such as：Since combustion process tissue is bad, combustion can be made
The thermal loss increase in room and fuel consumption increase are burnt, while carbon deposit can be also generated on flame tube wall and turbo blade, fire
Carbon deposit on flame barrel makes barrel cooling be deteriorated, and causes to overheat, deforms, even cracks；Carbon deposit on turbo blade makes blade
Aeroperformance is deteriorated, and reduces turbine efficiency, and influences the balance of engine rotor.
Vane type turbine has been used to have many-sided shortcoming thermal energy is converted to mechanical work.The cross-sectional area of turbo blade is not
May be big, ability is met with stresses with regard to very limited from blade tip to blade root under high temperature and pressure；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 component.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, since burner inner liner outlet temperature field is frequent
Uneven, turbine still suffers from the heat erosion of thermal stress and combustion gas, so as to accelerate the shortening in its service life.
Gas-turbine unit continues increase thrust after maximum rating is reached and is known as engine reinforcing.Since burner inner liner fires
It burns room and is arranged on engine block stage casing, combustion gas is again by turbine and the continuous enthalpy drop of free turbine, the fuel gas temperature deficiency discharged
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 is connect equally using thin burner inner liner combustion chamber as used
Nearly rocket flight detonation mode reinforces suddenly, and the recoil strength instantaneously generated is just not only enough to destroy entire 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-mv1It understands, causes
It is long to reinforce the rise time.
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 which is counted as aircraft carrier field, the highest technology of degree-of-difficulty factor.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 is in maximum position, it means that carrier-borne aircraft cannot definitely shut down and it is necessary to fill up
Throttle is dropped in type aircraft carrier deck at full speed, this requires arresting gear and pilot very high, thus to trigger security incident
Foreign countries happen occasionally.
Carrier-borne aircraft could must smoothly take off when taking off from aircraft carrier by ejector again.No matter steam catapult or electromagnetism
Ejector, structure is all extremely complex, not only occupies many spaces of aircraft carrier and deadweight tonnage, can't race against time in time
It takes off.
Advanced aero gas turbine engine technology is the extremely sensitive secrecy technology with embargo in various countries, from disclosure
The channel of communication, which obtains, 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 provide replace turbine rotor with the screwed pipe rotor for being equivalent to cellular type turbine to convert the screwed pipe of energy for the first time
Rotary engine is additionally provided to be compressed with external displacement air and combined with screwed pipe rotary engine as automobile engine.Specially
A kind of sharp 201610813636.7 screwed pipe rotor of application number and its engine, provide single-ended or both-end screwed pipe rotor and use it
To form 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 solution.
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 service life
A kind of long, safe and reliable, energy saving screwed pipe rotor helical-screw paddle or shaft generator；Three be to provide long lifespan, it is safe and reliable, energy saving,
Thrust big a kind of screwed pipe rotor fan engine and its boost engine.
Including turbojet, whirlpool is replaced with stairstepping screwed pipe rotor for a kind of combustion gas screwed pipe rotary jet engine
Wheel is equipped with diffuser between compressor exhaust outlet and stairstepping screwed pipe rotor, the annular letter of air quantity can be adjusted by being fixed on L-shaped on casing
The staging pack in road and screwed pipe rotor forms 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 adjust the air door of annular exhausting, can control into the first burning from the inlet to the outlet gradually to put shape
The air supply of room and the air supply for flowing through screwed pipe rotor periphery annular exhausting, with this mechanism into gas generator, work
Flow at high speed air becomes high pressure air inflow L-shaped annular exhausting through diffuser deceleration when making, through the eddy flow set by exhausting
Ring generates high-temperature high-pressure fuel gas with cyclone mode into first annular combustion chamber and fuel oil blending burning, and high-temperature high-pressure fuel gas flow through
Continuous change occurs for flow direction during each road screwed pipe, and a part of enthalpy drop is made to be converted to the mechanical work of driving compressor high-speed rotation,
Another part enthalpy drop, which is converted to flowing kinetic energy, makes the airflow speed increasing for flowing 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 forms annular
Exhausting, annular exhausting front end are equipped with the supporting of fixed size cylinder, and annular exhausting rear end is equipped with hundred gates of supporting size cylinder,
Radially hundred at an acute angle are equipped on small cylinder axial direction barrel between front support and hundred gates in clockwise and counterclockwise directions
Window whirl hole, the small drum surface set of annular exhausting is designed with hundred there are one radial and axial 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 hundred gate of L-shaped cylinder
The air quantity of exhausting reduces the air quantity of flowing in combustion chamber and increases the air quantity for flowing through screwed pipe rotor periphery annular exhausting.
A kind of screwed pipe rotor helical-screw paddle or shaft generator, including turbo-propeller or shaft generator, with a kind of combustion gas screwed pipe
Rotary jet engine makees core engine, and free turbine is replaced with a free screwed pipe rotor, core engine screwed pipe rotor exhaust outlet with from
By corresponding between screwed pipe rotor screwed pipe air inlet and equipped 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, is 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, the ladder of core engine turbine exhaust mouth and free screwed pipe rotor is correspondingly formed concave ring, then with equipped with air quantity can be adjusted
The second annular exhausting form the second toroidal combustion chamber, adjust the air door of the second annular exhausting, can control and 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, and screwed pipe rotor fan engine is made to have 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, and free turbine is replaced 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, the ladder of core engine turbine exhaust mouth and free screwed pipe rotor is correspondingly formed concave ring, then with equipped with
The second annular exhausting of air quantity can be adjusted to form the second toroidal combustion chamber, adjust the air door of the second annular exhausting, can control and 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 equipped 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.
It is had the following advantages that for a kind of combustion gas screwed pipe rotary jet engine (core engine)：
1. service life is long.Due to it is small with unit mass surface area and be whole screwed pipe rotor instead of blade turbine come
The chemical energy of fuel and is converted into thermal energy at energy by conversion with toroidal combustion chamber, just can be using thick and solid, high intensity, heat safe
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, and overcome burner inner liner combustion chamber overheat, deform, very
To cracking with burning shortcoming, overcome using vane type turbine come existing many-sided shortcoming when thermal energy is converted to mechanical work.
2. low cost.Than expensive blade turbine easy to manufacture, two can be used than high temperature resistant conjunction one whole screwed pipe rotor
The cheap hot pressed silicon nitride (HPSN) material of gold.
3. core engine entire length is short.Because with toroidal combustion chamber instead of burner inner liner combustion chamber, the axis 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 opposite to be greatly reduced.
It is had the following advantages that for a kind of screwed pipe rotor helical-screw paddle or shaft generator：
1. there is a kind of combustion gas screwed pipe rotary jet engine (core engine).
It is 2. energy saving.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.
It is 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, concentration heating is avoided.Compressor, the second combustion chamber supervisor's jet are responsible in first combustion chamber
Flight.
It is 3. energy saving.In identical compressed air require at a temperature of, turbofan is due to the combustion come out from burner inner liner
Gas working medium enthalpy has had 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 aircraft flight promoted just to seem somewhat weak, is unfavorable for energy saving.It compares, 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 is little, row
It is still very high to go out pressure and temperature, enthalpy drop is converted to flowing kinetic energy just very greatly, and jet promotes aircraft flight just to seem very strong.
4. provide 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
Kind working condition.
It is 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 utilized 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.
It can realize that short distance landing is shut down 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 the function of core engine maximum (top) speed output squeezing air and jet flight thrust makes engine close to 0
It is actual not shut down, it can go around at any time.The shortcomings that occurring when overcoming existing carrier-borne aircraft landing aircraft carrier.
4. carrier-borne aircraft can be realized when taking off from aircraft carrier realizes short field take-off using itself thrust.Because carrier-borne aircraft is from aircraft carrier
It can be used when taking off from maximum (top) speed output squeezing air and jet flight thrust is pushed away close to 0 function suddenly change for jet flight
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 shortcomings that occurring when existing carrier-borne aircraft takes off from aircraft carrier.
Description of the drawings
Specification schematic diagram provided by the invention 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. shafts, 5. diffusers, 6.L shape energy
The annular exhausting of tune 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 paddle or shaft generator schematic diagram.
In Fig. 2,1. engine crankcases, 2. compressor blades, 3. compressor rotors, 4. propeller shafts or 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 are with channeling
Slot, 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, and 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. 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
It puts, 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 wall surfaces, 4. screwed pipe entrances, 5. high-pressure compressors
Shaft, 6. low-pressure compressor 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, 3. high-pressure compressor shafts, and 4. low-pressure compressors turn
Axis.
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 small cylinder of 3. annular 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 small cylinder of 3. annular 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.
Specific embodiment
The specific embodiment of the present invention is described in further detail again below.
Including turbojet, whirlpool is replaced with stairstepping screwed pipe rotor for a kind of combustion gas screwed pipe rotary jet engine
Wheel is equipped with diffuser between compressor exhaust outlet and stairstepping screwed pipe rotor, the annular letter of air quantity can be adjusted by being fixed on L-shaped on casing
The staging pack in road and screwed pipe rotor forms 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 adjust the air door of annular exhausting, can control into the first burning from the inlet to the outlet gradually to put shape
The air supply of room and the air supply for flowing through screwed pipe rotor periphery annular exhausting, with this mechanism into gas generator, work
Flow at high speed air becomes high pressure air inflow L-shaped annular exhausting through diffuser deceleration when making, through the eddy flow set by exhausting
Ring generates high-temperature high-pressure fuel gas with cyclone mode into first annular combustion chamber and fuel oil blending burning, and high-temperature high-pressure fuel gas flow through
Continuous change occurs for flow direction during each road screwed pipe, and a part of enthalpy drop is made to be converted to the mechanical work of driving compressor high-speed rotation,
Another part enthalpy drop, which is converted to flowing kinetic energy, makes the airflow speed increasing for flowing to spout discharge, and aircraft obtains jet flight thrust.
A kind of combustion gas screwed pipe rotary jet engine is as turbojet, with different components, with regard to that can become
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
It 45 °, is located at the single-ended screwed pipe rotor of built-in screwed pipe cylinder surface layer for the screwed pipe of switching flow energy and makes stairstepping into, with
Being fixed on L-shaped on casing can adjust the annular exhausting of air quantity to form 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, acts as the wall surface that combination forms first annular combustion chamber.L-shaped anchor ring and stairstepping
There are running clearances for screwed pipe rotor.
Turbine is such as replaced using single-ended screwed pipe rotor, then is fixed on the neck group of the annular exhausting and screwed pipe rotor on casing
It closes and forms toroidal combustion chamber.
L-shaped can adjust the annular exhausting of air quantity and all available long-term resistance to 1300 DEG C of hot pressed silicon nitride (HPSN)s of screwed pipe rotor to manufacture, L-shaped energy
The annular exhausting of air quantity is adjusted to do thick and solid point as far as possible, the surface area for making unit mass is small, increases heat-resisting ability.
Screwed pipe accumulates gradually to put shape from air inlet to exhaust cross section, and combustion gas is made fully to be expanded in screwed pipe.According to
Total output is obtained with the formula of power=torque * rotating speeds/9550 in the power and rotating speed of compressor requirement screwed pipe rotary engine output
Total output moment of couple is divided into the n moment of couple by the moment of couple, is exactly idol arm further according to the distance between the symmetrical two air inlets center of circle, 1/n
The total moment of couple=power * idol arms, the compressed air pressure of compressor output, power=pressure * areas, with regard to each screwed pipe air inlet can be obtained
Open area.It is more that rotor circumference is divided into number under proof strength, 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 depth
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 screwed pipe inlet area of motivation minimum 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 increases screwed pipe inlet area, while the chemical energy of fuel is converted into the power of thermal 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 forms annular
Exhausting, annular exhausting front end are equipped with the supporting of fixed size cylinder, and annular exhausting rear end is equipped with hundred gates of supporting size cylinder,
Radially hundred at an acute angle are equipped on small cylinder axial direction barrel between front support and hundred gates in clockwise and counterclockwise directions
Window whirl hole, the small drum surface set of annular exhausting is designed with hundred there are one radial and axial 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 hundred gate of L-shaped cylinder
The air quantity of exhausting reduces the air quantity of flowing in combustion chamber and increases the air quantity for flowing through screwed pipe rotor periphery annular exhausting.
A kind of screwed pipe rotor helical-screw paddle or shaft generator, including turbo-propeller or shaft generator, with a kind of combustion gas screwed pipe
Rotary jet engine makees core engine, and free turbine is replaced with a free screwed pipe rotor, core engine screwed pipe rotor exhaust outlet with from
By corresponding between screwed pipe rotor screwed pipe air inlet and equipped 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.
Since 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
It obtains, the enthalpy drop of such combustion gas working medium is just converted as far as possible, the lack of gas of discharge reach with regard to that can be down to close to normal temperature and pressure
Energy saving purpose.
A kind of screwed pipe rotor fan engine including turbofan, is 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, the ladder of core engine turbine exhaust mouth and free screwed pipe rotor is correspondingly formed concave ring, then with equipped with air quantity can be adjusted
The second annular exhausting form the second toroidal combustion chamber, adjust the air door of the second annular exhausting, can control and 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, and screwed pipe rotor fan engine is made to have 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 can be adjusted with foregoing as the annular exhausting structure of air quantity.
During aircraft landing, damper makes the first shape combustion chamber throttle be in maximum position, at the second shape combustion chamber throttle
In idle position, at this moment, the equivalent screwed pipe rotor helical-screw paddle of screwed pipe rotor fan engine working condition or shaft generator work shape
State, whole enthalpy drops be converted to shaft work, make screwed pipe rotor fan engine have 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, and free turbine is replaced 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, the ladder of core engine turbine exhaust mouth and free screwed pipe rotor is correspondingly formed concave ring, then with equipped with
The second annular exhausting of air quantity can be adjusted to form the second toroidal combustion chamber, adjust the air door of the second annular exhausting, can control and 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 equipped 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
It burns room and the 3rd combustion chamber throttle is also provided 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 more than the requirement of minimum takeoff speed, realize using self power short field take-off.
Claims (3)
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 equipped 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 form 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 adjust the air door of annular exhausting from the inlet to the outlet gradually to put shape, can control and enter the
The air supply of one combustion chamber and the air supply for flowing through screwed pipe rotor periphery annular exhausting are occurred with this mechanism into combustion gas
Device, flow at high speed air becomes high pressure air through diffuser deceleration and flows into L-shaped annular exhausting during work, through set by exhausting
Cyclone ring generates high-temperature high-pressure fuel gas, high-temperature high-pressure fuel gas with cyclone mode into first annular combustion chamber and fuel oil blending burning
Continuous change occurs for flow direction when flowing through each road screwed pipe, and a part of enthalpy drop is made to be converted to the machinery of driving compressor high-speed rotation
Work(, another part enthalpy drop, which is converted to flowing kinetic energy, makes the airflow speed increasing for flowing 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 is combined with the neck of screwed pipe rotor forms toroidal combustion chamber.
3. a kind of annular letter that can adjust air quantity of combustion gas screwed pipe rotary jet engine according to claim 1,2
Road, 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 is formed
Annular exhausting, annular exhausting front end are equipped with the supporting of fixed size cylinder, and annular exhausting rear end is equipped with the hundred of supporting size cylinder
Gate is equipped on the small cylinder axial direction barrel between front support and hundred gates radially at an acute angle in clockwise and counterclockwise directions
Hundred window whirl holes, the small drum surface set of annular exhausting is designed with there are one radial and axial between front support and hundred gates
The L-shaped cylinder of hundred gates, the air quantity of flowing in combustion chamber can be increased and reduce and flow through screwed pipe rotor periphery by rotating hundred gate of L-shaped cylinder
The air quantity of annular exhausting reduces the air quantity of flowing in combustion chamber and increases the air quantity for flowing through screwed pipe rotor periphery annular exhausting.
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 |
| CN201810199314.7A CN108518246A (en) | 2017-04-15 | 2017-04-15 | A kind of screwed pipe rotor spindle engine |
| CN201810199367.9A CN108487947B (en) | 2017-04-15 | 2017-04-15 | Spiral tube rotor fan engine |
| CN201810199366.4A CN108518248A (en) | 2017-04-15 | 2017-04-15 | A kind of screwed pipe rotor helical-screw paddle motor |
| 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 |
|---|---|---|---|
| CN201810199315.1A Division CN108518247B (en) | 2017-04-15 | 2017-04-15 | Spiral-tube rotor fan boost 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 |
| CN201810199314.7A Division CN108518246A (en) | 2017-04-15 | 2017-04-15 | A kind of screwed pipe rotor spindle engine |
Publications (2)
| Publication Number | Publication Date |
|---|---|
| CN106948877A CN106948877A (en) | 2017-07-14 |
| CN106948877B true CN106948877B (en) | 2018-06-05 |
Family
ID=59477602
Family Applications (5)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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 |
| CN201810199315.1A Expired - Fee Related CN108518247B (en) | 2017-04-15 | 2017-04-15 | Spiral-tube rotor fan boost engine |
Family Applications Before (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201810199314.7A Withdrawn CN108518246A (en) | 2017-04-15 | 2017-04-15 | A kind of screwed pipe rotor spindle engine |
Family Applications After (3)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| 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 |
| CN201810199315.1A Expired - Fee Related CN108518247B (en) | 2017-04-15 | 2017-04-15 | Spiral-tube rotor fan boost engine |
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| Country | Link |
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| CN (5) | CN108518246A (en) |
Families Citing this family (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN208416619U (en) * | 2018-05-29 | 2019-01-22 | 游涛 | A kind of turbine and screwed pipe gas turbine |
| CN111779549A (en) * | 2020-07-08 | 2020-10-16 | 孙涛 | Aircraft engine tail nozzle |
| CN111751078A (en) * | 2020-08-10 | 2020-10-09 | 成都志胜空天动力科技有限公司 | Method for simulating performance parameters of turbine engine in test and multi-electric high-temperature turbine simulator |
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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
- 2017-04-15 CN CN201810199366.4A patent/CN108518248A/en not_active Withdrawn
- 2017-04-15 CN CN201810199315.1A patent/CN108518247B/en not_active Expired - Fee Related
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Also Published As
| Publication number | Publication date |
|---|---|
| CN108518246A (en) | 2018-09-11 |
| CN108518248A (en) | 2018-09-11 |
| CN108518247A (en) | 2018-09-11 |
| CN108518247B (en) | 2020-03-31 |
| CN106948877A (en) | 2017-07-14 |
| CN108487947A (en) | 2018-09-04 |
| CN108487947B (en) | 2020-04-21 |
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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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