CN102536511A - High thrust aircraft engine - Google Patents
High thrust aircraft engine Download PDFInfo
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- CN102536511A CN102536511A CN2012100846158A CN201210084615A CN102536511A CN 102536511 A CN102536511 A CN 102536511A CN 2012100846158 A CN2012100846158 A CN 2012100846158A CN 201210084615 A CN201210084615 A CN 201210084615A CN 102536511 A CN102536511 A CN 102536511A
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Abstract
The invention discloses a high thrust aircraft engine, which comprises an aircraft engine body and a jet pump. An aircraft engine jet channel of the aircraft engine body serves as a jet pump high pressure power fluid nozzle of the jet pump, or the aircraft engine jet channel of the aircraft engine body is communicated with the jet pump high pressure power fluid nozzle of the jet pump. The jet pump is connected with the aircraft engine body, a jet pump fluid outlet of the jet pump serves as an air jet power boosting spray pipe, or the jet pump fluid outlet of the jet pump is communicated with the air jet power boosting spray pipe in a butt joint mode. The high thrust aircraft engine greatly improves thrust and boosting efficiency, and the power turbine working temperature of the aircraft engine body provided with a power turbine is remarkably reduced.
Description
Technical field
The present invention relates to the jet propulsion field, relate in particular to a kind of aircraft engine.
Background technique
Aircraft engine (so-called aircraft engine be meant all pass through the motor that gas or fluid jet obtain thrust) is because its jet velocity often is far longer than its flying speed and in many cases; Jet velocity is very big; And the mass flow rate of spraying is very little; This has not only had a strong impact on the efficient of this type motor, and has had a strong impact on the thrust of this type motor.In order to overcome this shortcoming, people have invented turbofan engine and turbo oar engine etc.But this type motor needs power turbine to impeller mechanism outputting powers such as fans, and this has just increased considerably the turbine load of motor, and therefore the cost of motor and technical requirements meeting increase substantially.If can find a kind of technological scheme, improve the efficient and the thrust of aircraft engine through more succinct mode, will have epoch making significance.
Summary of the invention
To achieve these goals, technological scheme of the present invention is following:
A kind of high thrust aircraft engine; Comprise aircraft engine and Jet injector; The aircraft engine injection channel of said aircraft engine is made as the Jet injector high voltage power fluid tip of said Jet injector; Or the aircraft engine injection channel of said aircraft engine is communicated with the Jet injector high voltage power fluid tip of said Jet injector; Said Jet injector is connected with said aircraft engine, and the Jet injector fluid output of said Jet injector is made as the jet power propelling nozzle, or the Jet injector fluid output of said Jet injector is made as with the jet power propelling nozzle and is docked and connected.
The product of the mass flow rate of the gas that the Jet injector fluid output continuous injection of said Jet injector goes out and the jet velocity of gas when directly carrying out continuous injection by said aircraft engine injection channel mass flow rate and the product of jet velocity of getable jet gas.
Said aircraft engine is made as rocket motor, turbojet engine, turbofan engine, turbo oar engine, turboaxle motor, pressed engine, torpedo air breathing engine, water-jet motor, steam propulsion motor, underwater propeller motor or missile propulsive plant.
Said aircraft engine is made as by firing chamber, firing chamber intake duct and firing chamber working medium injection pipe and constitutes; Said firing chamber intake duct is communicated with said firing chamber; Said firing chamber is communicated with said firing chamber working medium injection pipe, and the Jet injector low-pressure fluid inlet of said Jet injector is communicated with said firing chamber intake duct.
Said aircraft engine is made as by firing chamber, firing chamber intake duct, gas compressor and firing chamber working medium injection pipe and constitutes; The gas compressor pressurized gas outlet of said gas compressor is communicated with said firing chamber intake duct; Said firing chamber intake duct is communicated with said firing chamber; Said firing chamber is communicated with said firing chamber working medium injection pipe, between said gas compressor and the said firing chamber, establishes the pressurized gas export mouth, and said pressurized gas export mouth is communicated with the Jet injector low-pressure fluid inlet of said Jet injector.
Said aircraft engine is made as by firing chamber, firing chamber intake duct, gas compressor and firing chamber working medium injection pipe and constitutes, and said gas compressor is made as multistage compressor; The gas compressor pressurized gas outlet of said gas compressor is communicated with said firing chamber intake duct; Said firing chamber intake duct is communicated with said firing chamber; Said firing chamber is communicated with said firing chamber working medium injection pipe; On the inter-stage sender property outlet of said gas compressor, establish the pressurized gas export mouth, said pressurized gas export mouth is communicated with the Jet injector low-pressure fluid inlet of said Jet injector.
Said aircraft engine is made as turbofan engine; The by-pass air duct gas outlet of the by-pass air duct of said turbofan engine is communicated with the Jet injector low-pressure fluid of said Jet injector inlet; Or on the said by-pass air duct behind the fan of said turbofan engine, establish by-pass air duct pressurized gas export mouth, said by-pass air duct pressurized gas export mouth is communicated with the Jet injector low-pressure fluid inlet of said Jet injector.
Said high thrust aircraft engine is arranged on the rotational structure body.
The Jet injector outer tube of said Jet injector is made as detachable and/or detachable.
Said Jet injector high voltage power fluid tip position on the axis in the Jet injector outer tube of said Jet injector is made as adjustable.
The Jet injector outer tube of said Jet injector is made as straight tube.
Two the above aircraft engine injection channels are set, to dwindle the diameter of said aircraft engine injection channel on a said aircraft engine.
The distance of the aditus laryngis of said Jet injector high voltage power fluid tip and said Jet injector is greater than 10cm.
A kind of method that improves the said high thrust aircraft engine efficient and the feature of environmental protection; The temperature of the gas working medium that adjustment is about to begin to do work is below 2000K; The pressure of the gas working medium that adjustment is about to begin to do work is to more than the 15MPa, makes adiabatic relation of temperature and pressure type of meeting of the gas working medium that is about to begin to do work.
Among the present invention; So-called aircraft engine is meant the motor that all pass through gas or liquid discharging or pass through flow of fluid acquisition thrust, for example rocket motor, pressed engine, turbojet engine, turbofan engine, turbo oar engine, turboaxle motor, water-jet motor, steam propulsion motor, torpedo air breathing engine, underwater propeller motor, missile propulsive plant etc.; So-called aircraft is meant the moving body by jet propulsion, for example at the aircraft of endoatmosphere flight, the astrovehicle that need get through the earth's atmosphere, the object (like torpedo, naval vessel etc.) that in the ocean, goes.
Among the present invention, so-called flow of fluid is meant at the liquid propeller cavitation and is arranged on the flow of fluid that produces under the effect of the honeycomb duct outside the liquid propeller cavitation; So-called underwater propeller motor is meant by the liquid propeller cavitation and is arranged on the mechanism that can obtain propelling force that the outer honeycomb duct of liquid propeller cavitation constitutes, among the present invention the honeycomb duct in the said underwater propeller motor is made as said aircraft engine injection channel.
Among the present invention, the distance of the aditus laryngis of said Jet injector high voltage power fluid tip and said Jet injector is greater than 15cm, 20cm, 25cm, 30cm, 35cm, 40cm, 45cm, 50cm, 55cm, 60cm, 65cm, 70cm, 75cm, 80cm, 85cm, 90cm or greater than 100cm.
Among the present invention; Be made as in the structure of Jet injector high voltage power fluid tip of said Jet injector at the aircraft engine injection channel of said aircraft engine; Said aircraft engine injection channel should be consistent with the eject request of said Jet injector high voltage power fluid tip; And according to eject request; Adjust the distance of said aircraft engine injection channel and said Jet injector aditus laryngis; Can design said aircraft engine injection channel according to the eject request of said Jet injector high voltage power fluid tip again in case of necessity, even can said aircraft engine injection channel be made as the injection channel that is made up of a plurality of minor diameter injection pipes, to obtain bigger propelling force.
Principle of the present invention is the Jet injector high voltage power fluid tip that is made as said Jet injector through the aircraft engine injection channel with said aircraft engine; Or the aircraft engine injection channel of said aircraft engine is communicated with the Jet injector high voltage power fluid tip of said Jet injector; Said Jet injector is connected with said aircraft engine; Working medium in the said aircraft engine injection channel is sprayed by said Jet injector high voltage power fluid tip; Under the effect of the injection of said Jet injector high voltage power fluid tip and said Jet injector; Make other fluids (like the air in the atmosphere; Through the fan air pressurized, through gas compressor air pressurized or liquid) by the Jet injector low-pressure fluid of said Jet injector inlet to said Jet injector fluid output generation directional flow, increasing the mass flow rate of the working medium that ejects from said Jet injector fluid output, thereby obtain the increase of thrust.
Among the present invention, Figure 17 is the graph of a relation of the temperature T and the pressure P of gas working medium, and curve shown in the O-A-H is to be the adiabatic relation curve of gas working medium that the O of 298K and 0.1MPa is ordered through status parameter; The B point is the virtual condition point of gas working medium, and curve shown in the E-B-D is the adiabatic relation curve of ordering through B, and the A point is identical with the pressure that B is ordered; Curve shown in the F-G is the adiabatic relation curve of working medium through 2800K and 10MPa (being the state point of the gas working medium that is about in the present internal-combustion engine to begin to do work).
Among the present invention;
in
among Figure 17 is the gas working medium adiabatic index;
is the pressure of gas working medium;
is the temperature of gas working medium, and
is constant.
Among the present invention, so-called type adiabatic relation comprises following three kinds of situation: 1. the status parameter of gas working medium (being the temperature and pressure of working medium) point is on said working medium thermal insulation relation curve, and promptly the status parameter point of gas working medium is in Figure 17 shown in the O-A-H on the curve; 2. the status parameter of gas working medium (being the temperature and pressure of working medium) point is in the adiabatic relation curve of said working medium left side, the i.e. left side of the status parameter point of gas working medium curve shown in the O-A-H in Figure 17; 3. the status parameter of gas working medium (being the temperature and pressure of working medium) point is on the adiabatic relation curve of said working medium right side; It is the right side of status parameter point curve shown in the O-A-H in Figure 17 of gas working medium; But the pressure that the temperature of gas working medium is not higher than gas working medium thus by the thermal insulation relation calculate the gained temperature add 1000K with, add 950K's and, add 900K's and, add 850K's and, add 800K's and, add 750K's and, add 700K's and, add 650K's and, add 600K's and, add 550K's and, add 500K's and, add 450K's and, add 400K's and, add 350K's and, add 300K's and, add 250K's and, add 200K's and, add 190K's and, add 180K's and, add 170K's and, add 160K's and, add 150K's and, add 140K's and, add 130K's and, add 120K's and, add 110K's and, add 100K's and, add 90K's and, add 80K's and, add 70K's and, add 60K's and, add 50K's and, add 40K's and, add 30K's and or be not higher than add 20K's and; Promptly shown in figure 17; The virtual condition point of said gas working medium is the B point; The A point is the point on the pressure adiabatic relation curve identical with the B point, and the temperature difference between A point and the B point should be less than 1000K, 900K, 850K, 800K, 750K, 700K, 650K, 600K, 550K, 500K, 450K, 400K, 350K, 300K, 250K, 200K, 190K, 180K, 170K, 160K, 150K, 140K, 130K, 120K, 110K, 100K, 90K, 80K, 70K, 60K, 50K, 40K, 30K or less than 20K.
Among the present invention; So-called type of adiabatic relation can be any in above-mentioned three kinds of situation, just refers to: status parameter (being the temperature and pressure of the gas working medium) point of the gas working medium that is about to begin to do work is in the left field of passing through adiabatic process curve E-B-D that B orders shown in figure 17.
Among the present invention, the so-called gas working medium that is about to begin to do work is meant the gas working medium that is about to the expansion acting.
Among the present invention, the adiabatic engine system (being thermal power system) that concerns of status parameter (being the temperature and pressure of gas working medium) type of meeting of the gas working medium that is about to begin to do work is defined as low entropy motor.
Among the present invention, adjust the working state of said Jet injector, make the adiabatic relation of temperature and pressure type of meeting of the gas working medium in said Jet injector outlet port.
According to principle of the present invention, the mass flow rate that produces through said Jet injector outlet is big, the working medium that jet velocity is lower among the present invention; Temperature is also lower, if utilize this working medium to remove the propulsion power turbine, with the operating temperature that reduces said power turbine significantly; Thereby reduce the material and the processing cost of said power turbine; Also therefore can increase substantially the rotating speed of said power turbine simultaneously, thereby the rotating speed of the said gas compressor of raising and its interlock reaches the purpose that improves said gas compressor pressure ratio.Among the present invention,, proposed related art scheme, utilized these technological schemes, can produce low cost of manufacture, the jet engine that efficient is high according to this principle.
In order to understand better; Why can increase the thrust of aircraft engine through said Jet injector, we at first analyze turbofan engine, and why turbofan engine can increase thrust; Though be because it has reduced the speed of jet gas backward; But increased the motor mass flow rate of jet gas backward significantly, thereby realized the increase of the product of fluid jet mass flow rate and nozzle-fluid velocity, realized the increase of thrust.From essence; No matter adopt fan, or propeller cavitation, additive method still adopted; As long as under the prerequisite that can seldom consume energy; Promptly the speed of jet gas increases the motor mass flow rate of jet gas backward through reducing backward, finally increases the product of fluid jet mass flow rate and nozzle-fluid velocity, just can improve the thrust and the propulsive efficiency of air breathing engine.The present invention is through the setting of Jet injector; Be implemented under the prerequisite of few power consumption; Promptly the speed of jet gas increases the motor mass flow rate of jet gas backward through reducing backward; The final product that increases fluid jet mass flow rate and nozzle-fluid velocity reaches the purpose that increases thrust and propulsive efficiency.
Among the present invention, no matter be to promote said power turbine to obtain rotating power, still obtain thrust through said jet power propelling nozzle, the process and the common blending of the said Jet injector of process have the different of essence.Generally speaking, blending is that two kinds of working medium a little less than the strong or acting ability are mixed with the acting ability, and this mode can be lost part acting ability in some cases.And the disclosed technological scheme of the present invention; Blending through said Jet injector; Resulting working medium is to be kept in motion; Not only do not lose the acting ability, and whole acting ability is improved, utilize the stronger working medium of acting ability that the more weak working medium of acting is done work rather than simple blending because on this process nature be.
Among the present invention; In said Jet injector fluid output, be provided with in the structure of said power turbine, can combustion chamber temperature be increased substantially, reduce the loss of the acting ability in the fuel combustion process; To obtain the working medium of higher acting ability through the combustion process in the firing chamber; Utilize this working medium through of the fluid acting of said Jet injector, thereby realize not having the acting process of movement parts, produce the working medium that temperature is lower, the acting ability is big getting into by said Jet injector low-pressure fluid inlet; Promote said power turbine and form rotating power, finally improve the efficient of motor.
Among the present invention; In being provided with the structure of said gas compressor, the gas pressure of said gas compressor pressurized gas outlet is greater than 1MPa, 1.1MPa, 1.2MPa, 1.3MPa, 1.4MPa, 1.5MPa, 1.6MPa, 1.7MPa, 1.8MPa, 1.9MPa, 2MPa, 2.1MPa, 2.2MPa, 2.3MPa, 2.4MPa, 2.5MPa, 2.6MPa, 2.7MPa, 2.8MPa, 2.9MPa, 3MPa, 3.1MPa, 3.2MPa, 3.3MPa, 3.4MPa, 3.5MPa, 3.6MPa, 3.7MPa, 3.8MPa, 3.9MPa, 4MPa, 4.1MPa, 4.2MPa, 4.3MPa, 4.4MPa, 4.5MPa, 4.6MPa, 4.7MPa, 4.8MPa, 4.9MPa, 5MPa, 5.1MPa, 5.2MPa, 5.3MPa, 5.4MPa, 5.5MPa, 5.6MPa, 5.7MPa, 5.8MPa, 5.9MPa, 6MPa, 6.1MPa, 6.2MPa, 6.3MPa, 6.4MPa, 6.5MPa, 6.6MPa, 6.7MPa, 6.8MPa, 6.9MPa, 7MPa, 7.1MPa, 7.2MPa, 7.3MPa, 7.4MPa, 7.5MPa, 7.6MPa, 7.7MPa, 7.8MPa, 7.9MPa or greater than 8MPa.
Among the present invention, so-called Jet injector is meant through the non-motive fluid of motive fluid injection, the device that two fluid interactions are discharged from an outlet, and so-called Jet injector can be gas jet pump (being jet pump), also can be liquid-jet pump; So-called Jet injector can be traditional Jet injector, also can be non-traditional Jet injector.
Among the present invention; So-called traditional Jet injector is meant what the pipe by two suit settings constituted; Inwardly pipe provides the high voltage power fluid; Interior pipe high voltage power fluid sprays in outer tube, the device that other fluids (from the fluid of outer tube entering) between the inner and outer pipes are moved along the injection direction generation of interior pipe high voltage power fluid; The outer tube of so-called Jet injector can have the reducing and expansion district, and outer tube can be made as Venturi tube, and interior pipe nozzle can be made as Laval nozzle, and so-called reducing and expansion district is meant the zone that section area changes in the outer tube; Said Jet injector has three interfaces at least or claims passage, i.e. Jet injector high voltage power fluid tip, Jet injector low-pressure fluid inlet and Jet injector fluid output.
Among the present invention; So-called non-traditional Jet injector is meant and is made up of two or more mutual sheathing settings or the pipe that is set up in parallel each other; Wherein at least one pipe is communicated with the kinetic current body source, and dynamafluidal the flowing in the kinetic current body source can cause that the fluid in other pipes produces the device of directional flow; The pipe of so-called Jet injector can have the reducing and expansion district, can be made as Venturi tube, and the nozzle of pipe can be made as Laval nozzle, and so-called reducing and expansion district is the zone that section area changes in the vial; Said Jet injector has three interfaces at least or claims passage, i.e. Jet injector high voltage power fluid tip, Jet injector low-pressure fluid inlet and Jet injector fluid output; Said Jet injector can comprise a plurality of Jet injector high voltage power fluid tips; In the structure that comprises a plurality of Jet injector high voltage power fluid tips; Said Jet injector high voltage power fluid tip can be arranged in the pipeline center district of said Jet injector low-pressure fluid inlet; Also can be arranged near the tube wall of said Jet injector low-pressure fluid inlet, said Jet injector high voltage power fluid tip also can be the ring nozzle around said Jet injector low-pressure fluid inlet pipe wall.
Among the present invention, said Jet injector comprises multistage Jet injector, multiple jets pump and pulsing jet pump etc.
Among the present invention, said Jet injector high voltage power fluid tip can be arranged in the said Jet injector low-pressure fluid inlet, and said Jet injector low-pressure fluid inlet also can be arranged in the said Jet injector high voltage power fluid tip.
Among the present invention, in the structure in the Jet injector fluid output that said power turbine is arranged on said Jet injector, with the operating temperature that reduces said power turbine significantly; Therefore; On the basis of current material technology, can increase substantially the rotating speed of said power turbine, and then can increase substantially the rotating speed of said gas compressor; Improve the compression ratio of said gas compressor; The working medium that produces owing to said firing chamber did not again contact with power turbine before blending, thus can increase substantially the operating temperature of firing chamber, thus increase substantially overall engine efficiency.
Among the present invention, said cooling spray pipe and said firing chamber working medium injection pipe can in the light of actual conditions carry out assembled arrangement, to satisfy cooling and the transmission requirement to said power turbine.
Among the present invention, said inter-stage sender property outlet is meant the outlet of deriving pressurized gas from certain one-level of multistage said gas compressor; Derive pressurized gas and make this pressurized gas get into the mode of the said Jet injector low-pressure fluid inlet of said Jet injector through certain one-level from multistage said gas compressor, the requirement of said Jet injector efficient operation is satisfied in adjustment through the pressure of said Jet injector low-pressure fluid ingress.
Among the present invention, in being provided with the structure of rocket motor, can increase substantially rocket, thereby can reduce the amount of carrying fuel and oxygenant significantly in endoatmospheric thrust.
Among the present invention; So-called firing chamber is meant the space of Oxidizing and Reducing Agents generation combustion chemistry reaction; For example aeroengine combustor buring chamber, scramjet combustor etc.; So-called oxygenant comprises air, oxygen, oxygen-containing gas etc., and so-called reducing agent comprises hydrocarbon fuels and ethanol and ethanol water etc.; So-called firing chamber intake duct is to point to the passage that imports oxygenant in the said firing chamber, comprises the intake duct of motor; So-called firing chamber working medium injection pipe is meant the passage of deriving HTHP working medium from said firing chamber; So-called jet power propelling nozzle is meant in order to obtain the jet pipe of reaction force; So-called gas compressor is meant through the mechanism of impeller rotation to gas generation compression, can be single-stage, also can be multistage, can be radial-flow type, axial flow or hybrid; So-called rotational structure body is meant the structure of outputting rotary power that can rotate and external; The so-called additional additional meaning that is provided with in system that is meant.
Among the present invention; So-called " Jet injector high voltage power fluid tip is made as position adjustable " is meant the adjustable positions of said Jet injector outer tube on the common axis line of said Jet injector high voltage power fluid tip outer at both; For realizing this purpose; Can said Jet injector outer tube is moved on both common axis lines through hydraulic mechanism or screw mechanism, the purpose of this adjustment be that adjustment is from the working medium of said Jet injector high voltage power fluid tip ejection with from the mixing proportion between the gas of outer tube entering.
Among the present invention, so-called injection channel is meant the passage that all can jet fluid, and for example said aircraft engine sprays the pipeline that working medium obtains thrust.
Among the present invention; The aircraft engine injection channel of said aircraft engine is made as the Jet injector high voltage power fluid tip of said Jet injector or the aircraft engine injection channel of said aircraft engine is communicated with the Jet injector high voltage power fluid tip of said Jet injector; Should be according to known technology; Adjust the size and dimension of said aircraft engine injection channel and said Jet injector high voltage power fluid tip, to realize said Jet injector efficient operation.
Among the present invention, so-called pipe and passage are of equal value, are meant the space that all can make the fluid directional flow; So-called connection is meant and is connected or the position adjustable connection; So-called power turbine is meant that all can be with the mobile impeller mechanism that converts rotating power to of fluid; So-called secondary Jet injector is meant the Jet injector different with said Jet injector.
Among the present invention, the so-called detachable Jet injector outer tube of said Jet injector that is meant can be removed through control mechanism automatically, and for example rocket can be removed said Jet injector after getting through the earth's atmosphere, to reduce quality; So-called detachable is meant that said Jet injector outer tube constitutes with top by two, so that install, remove and/or make said Jet injector in running order or said Jet injector was lost efficacy.
Among the present invention, can said jet power propelling nozzle be made as Laval nozzle.
Among the present invention, so-called rocket motor is meant liquid propellant rocket engine and solid propellant rocket etc.
The present invention can provide bigger thrust for all aircraft engines; For example bigger thrust is provided for turbojet engine, turbofan engine, turbo oar engine, pressed engine, rocket motor, water-jet motor and steam propulsion motor; Thereby fuel saving; In some cases, can save oxygenant; The present invention can provide bigger thrust for guided missile, increases range; Moreover, can also to increase with the rocket be the thrust of the torpedo of motor in the present invention.So-called steam propulsion motor is meant through jet pipe and sprays the motor that high-temperature high-pressure steam obtains thrust.
Among the present invention, in the structure of thrust that the technological scheme among the present invention is used for increasing with the rocket torpedo that is motor, adopting liquid hydrogen is reducing agent, and liquid oxygen is an oxygenant, can eliminate the tail of torpedo.
Among the present invention, should establish necessary parts, unit or system in the place of necessity, for example on said firing chamber, establish fuel injector and ignition mechanism according to the known technology in jet propulsion field and hydraulic jet propulsion field.
Beneficial effect of the present invention is following:
1, simple in structure, the low cost of manufacture of the present invention, reliability are high.
2, the present invention has increased substantially the thrust and the propulsive efficiency of aircraft engine.
3, the present invention has reduced the power turbine operating temperature of the aircraft engine that is provided with power turbine significantly.
Description of drawings
Fig. 1 is the structural representation of the embodiment of the invention 1;
Fig. 2 to Fig. 5 is the structural representation of the embodiment of the invention 2;
Fig. 6 is the structural representation of the embodiment of the invention 3;
Fig. 7 and Fig. 8 are the structural representations of the embodiment of the invention 4;
Fig. 9 and Figure 10 are the structural representations of the embodiment of the invention 5;
Figure 11 is the structural representation of the embodiment of the invention 6;
Figure 12 and Figure 13 are the structural representations of the embodiment of the invention 7;
Figure 14 is the structural representation of the embodiment of the invention 8;
Figure 15 is the structural representation of the embodiment of the invention 9;
Figure 16 is the structural representation of the embodiment of the invention 10
Figure 17 is the graph of a relation of the temperature T and the pressure P of gas working medium.
Among the figure:
1 firing chamber; 2 firing chamber intake ducts; 3 firing chamber working medium injection pipes; 4 Jet injectors; 5 jet power propelling nozzles; 6 gas compressors; 8 fans; 10 rotational structure bodies; 11 pressurized gas export mouths; 20 by-pass air ducts; The outlet of 66 gas compressor pressurized gass; 2000 aircraft engines; 1000 aircraft engine injection channels; 401 Jet injector high voltage power fluid tips; 402 Jet injector low-pressure fluids inlet; 403 Jet injector fluid outputs; 404 Jet injector outer tubes; 200 rocket motor; 202 turbofan engines; 204 turboaxle motors; 205 pressed engines; 206 torpedo air breathing engines; 666 inter-stage sender property outlets; 2001 by-pass air duct gas outlets; 2002 by-pass air duct pressurized gas export mouths; 409 ring nozzles.
Embodiment
High thrust aircraft engine as shown in Figure 1; Comprise aircraft engine 2000 and Jet injector 4; The aircraft engine injection channel 1000 of said aircraft engine 2000 is made as the Jet injector high voltage power fluid tip 401 of said Jet injector 4; Or the aircraft engine injection channel 1000 of said aircraft engine 2000 is communicated with the Jet injector high voltage power fluid tip 401 of said Jet injector 4; Said Jet injector 4 is connected with said aircraft engine 2000, and the Jet injector fluid output 403 of said Jet injector 4 is made as jet power propelling nozzle 5.In order to improve the said high thrust aircraft engine efficient and the feature of environmental protection; The temperature of the gas working medium that adjustment is about to begin to do work is below 2000K; The pressure of the gas working medium that adjustment is about to begin to do work is to more than the 15MPa, makes adiabatic relation of temperature and pressure type of meeting of the gas working medium that is about to begin to do work.
During practical implementation, also can the Jet injector fluid output 403 of said Jet injector 4 be made as and be docked and connected with jet power propelling nozzle 5.
Adjust the geometrical shape and the size of Jet injector outer tube 404 of geometrical shape and the size and the said Jet injector 4 of said Jet injector high voltage power fluid tip 401, the product of jet velocity of mass flow rate and gas that makes the gas that goes out from Jet injector fluid output 403 continuous injections of said Jet injector 4 when directly carrying out continuous injection by said aircraft engine injection channel 1000 mass flow rate and the product of jet velocity of getable jet gas.
During practical implementation, the Jet injector outer tube 404 of said Jet injector 4 can also be made as straight tube; Two the above aircraft engine injection channels 1000 are set, to dwindle the diameter of said aircraft engine injection channel 1000 on a said aircraft engine 2000; The distance of said Jet injector high voltage power fluid tip 401 and the aditus laryngis of said Jet injector 4 is greater than 10cm, 15cm, 20cm, 25cm, 30cm, 35cm, 40cm, 45cm, 50cm, 55cm, 60cm, 65cm, 70cm, 75cm, 80cm, 85cm, 90cm or greater than 100cm.
To high thrust aircraft engine shown in Figure 5, itself and embodiment's 1 difference is: said aircraft engine 2000 is made as rocket motor 200 (as shown in Figure 2), pressed engine 205 (as shown in Figure 3), torpedo air breathing engine 206 (as shown in Figure 4), turboaxle motor 204 (as shown in Figure 5), turbojet engine, turbofan engine 202, turbo oar engine, water-jet motor, steam propulsion motor, underwater propeller motor or missile propulsive plant like Fig. 2.
High thrust aircraft engine as shown in Figure 6; Itself and embodiment's 1 difference is: said aircraft engine 2000 is made as by firing chamber 1, firing chamber intake duct 2 and firing chamber working medium injection pipe 3 and constitutes; Said firing chamber intake duct 2 is communicated with said firing chamber 1; Said firing chamber 1 is communicated with said firing chamber working medium injection pipe 3; The pressurized gas that gets into said firing chamber 1 by said firing chamber intake duct 2 said firing chamber 1 in the reaction of fuel generation combustion chemistry, working medium working medium injection pipe 3 ejections of forming of combustion chemistry reaction thus from said firing chamber, the Jet injector low-pressure fluid of said Jet injector 4 enters the mouth and 402 is communicated with said firing chamber intake duct 2.
Like Fig. 7 and high thrust aircraft engine shown in Figure 8; Itself and embodiment's 1 difference is: said aircraft engine 2000 is made as by firing chamber 1, firing chamber intake duct 2, gas compressor 6 and firing chamber working medium injection pipe 3 and constitutes; The gas compressor pressurized gas of said gas compressor 6 outlet 66 is communicated with said firing chamber intake duct 2; Said firing chamber intake duct 2 is communicated with said firing chamber 1; Said firing chamber 1 is communicated with said firing chamber working medium injection pipe 3; The pressurized gas that is produced by said gas compressor 6 gets into said firing chambers 1 and said firing chamber 1 in, reacts with fuel generation combustion chemistry through said firing chamber intake duct 2; The working medium of combustion chemistry reaction formation working medium injection pipe 3 ejections from said firing chamber are thus established pressurized gas export mouth 11 between said gas compressor 6 and the said firing chamber 1, said pressurized gas export mouth 11 is communicated with the Jet injector low-pressure fluid inlet 402 of said Jet injector 4.Wherein, the Jet injector fluid output 403 of Jet injector described in Fig. 84 is docked and connected through firing chamber and jet power propelling nozzle 5.
Selectively, when said gas compressor 6 was made as multistage compressor, said pressurized gas export mouth 11 was located on the inter-stage sender property outlet 666 of said gas compressor 6.
Like Fig. 9 and high thrust aircraft engine shown in Figure 10; Itself and embodiment's 1 difference is: said aircraft engine 2000 is made as turbofan engine 202; The by-pass air duct gas outlet 2001 of the by-pass air duct 20 of said turbofan engine 202 is communicated with (as shown in Figure 9) with the Jet injector low-pressure fluid of said Jet injector 4 inlet 402; Or on the by-pass air duct 20 behind the fan 8 of said turbofan engine 202, establish by-pass air duct pressurized gas export mouth 2002, said by-pass air duct pressurized gas export mouth 2002 is communicated with (shown in figure 10) with the Jet injector low-pressure fluid inlet 402 of said Jet injector 4.
High thrust aircraft engine shown in figure 11, said high thrust aircraft engine are arranged on and constitute the rotary jet power engine on the rotational structure body 10.
Embodiment 7
Like Figure 12 and high thrust aircraft engine shown in Figure 13, itself and embodiment's 1 difference is: the Jet injector outer tube 404 of said Jet injector 4 is made as detachable (shown in figure 12) and/or detachable (shown in figure 13).
High thrust aircraft engine shown in figure 14, itself and embodiment's 1 difference is: said Jet injector high voltage power fluid tip 401 position on the axis in the Jet injector outer tube 404 of said Jet injector 4 is made as adjustable.
Embodiment 9
High thrust aircraft engine shown in figure 15, itself and embodiment's 1 difference is: said high thrust aircraft engine is made as under water works.
High thrust aircraft engine shown in figure 16, itself and embodiment's 1 difference is: said Jet injector high voltage power fluid tip 401 is made as the ring nozzle 409 around the tube wall of said Jet injector low-pressure fluid inlet 402.
Obviously, the invention is not restricted to above embodiment, according to the known technology and the disclosed technological scheme of the present invention of related domain, can derive or association goes out many flexible programs, all these flexible programs also should be thought protection scope of the present invention.
Claims (10)
1. high thrust aircraft engine; It is characterized in that: comprise aircraft engine (2000) and Jet injector (4); The aircraft engine injection channel (1000) of said aircraft engine (2000) is made as the Jet injector high voltage power fluid tip (401) of said Jet injector (4); Or the aircraft engine injection channel (1000) of said aircraft engine (2000) is communicated with the Jet injector high voltage power fluid tip (401) of said Jet injector (4); Said Jet injector (4) is connected with said aircraft engine (2000); The Jet injector fluid output (403) of said Jet injector (4) is made as jet power propelling nozzle (5), or the Jet injector fluid output (403) of said Jet injector (4) is made as with jet power propelling nozzle (5) and is docked and connected.
2. high thrust aircraft engine according to claim 1 is characterized in that: the product of the mass flow rate of the gas that Jet injector fluid output (403) continuous injection of said Jet injector (4) goes out and the jet velocity of gas when directly carrying out continuous injection by said aircraft engine injection channel (1000) mass flow rate and the product of jet velocity of getable jet gas.
3. high thrust aircraft engine according to claim 1 or claim 2; It is characterized in that: said aircraft engine (2000) is made as by firing chamber (1), firing chamber intake duct (2) and firing chamber working medium injection pipe (3) and constitutes; Said firing chamber intake duct (2) is communicated with said firing chamber (1); Said firing chamber (1) is communicated with said firing chamber working medium injection pipe (3), and the Jet injector low-pressure fluid inlet (402) of said Jet injector (4) is communicated with said firing chamber intake duct (2).
4. high thrust aircraft engine according to claim 1 or claim 2; It is characterized in that: said aircraft engine (2000) is made as by firing chamber (1), firing chamber intake duct (2), gas compressor (6) and firing chamber working medium injection pipe (3) and constitutes; The gas compressor pressurized gas outlet (66) of said gas compressor (6) is communicated with said firing chamber intake duct (2); Said firing chamber intake duct (2) is communicated with said firing chamber (1); Said firing chamber (1) is communicated with said firing chamber working medium injection pipe (3); On between said gas compressor (6) and said firing chamber (1), establish pressurized gas export mouth (11), said pressurized gas export mouth (11) is communicated with the Jet injector low-pressure fluid inlet (402) of said Jet injector (4).
5. high thrust aircraft engine according to claim 1 or claim 2; It is characterized in that: said aircraft engine (2000) is made as by firing chamber (1), firing chamber intake duct (2), gas compressor (6) and firing chamber working medium injection pipe (3) and constitutes, and said gas compressor (6) is made as multistage compressor; The gas compressor pressurized gas outlet (66) of said gas compressor (6) is communicated with said firing chamber intake duct (2); Said firing chamber intake duct (2) is communicated with said firing chamber (1); Said firing chamber (1) is communicated with said firing chamber working medium injection pipe (3); On the inter-stage sender property outlet (666) of said gas compressor (6), establish pressurized gas export mouth (11), said pressurized gas export mouth (11) is communicated with the Jet injector low-pressure fluid inlet (402) of said Jet injector (4).
6. high thrust aircraft engine according to claim 1 or claim 2; It is characterized in that: said aircraft engine (2000) is made as turbofan engine (202); The by-pass air duct gas outlet (2001) of the by-pass air duct (20) of said turbofan engine (202) is communicated with the Jet injector low-pressure fluid of said Jet injector (4) inlet (402); Or on the said by-pass air duct (20) behind the fan (8) of said turbofan engine (202), establish by-pass air duct pressurized gas export mouth (2002), said by-pass air duct pressurized gas export mouth (2002) is communicated with the Jet injector low-pressure fluid inlet (402) of said Jet injector (4).
7. high thrust aircraft engine according to claim 1 or claim 2, it is characterized in that: said Jet injector high voltage power fluid tip (401) position on the axis in the Jet injector outer tube (404) of said Jet injector (4) is made as adjustable.
8. high thrust aircraft engine according to claim 1 or claim 2 is characterized in that: two the above aircraft engine injection channels (1000) are set on a said aircraft engine (2000).
9. high thrust aircraft engine according to claim 1 or claim 2 is characterized in that: the distance of said Jet injector high voltage power fluid tip (401) and the aditus laryngis of said Jet injector (4) is greater than 10cm.
10. one kind is improved the method for high thrust aircraft engine efficient and the feature of environmental protection according to claim 1 or claim 2; It is characterized in that: the temperature of the gas working medium that adjustment is about to begin to do work is below 2000K; The pressure of the gas working medium that adjustment is about to begin to do work is to more than the 15MPa, makes adiabatic relation of temperature and pressure type of meeting of the gas working medium that is about to begin to do work.
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| CN2012100846158A CN102536511A (en) | 2011-03-28 | 2012-03-27 | High thrust aircraft engine |
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| CN201110075185 | 2011-03-28 | ||
| CN201110075185.9 | 2011-03-28 | ||
| CN201110076729 | 2011-03-29 | ||
| CN201110076729.3 | 2011-03-29 | ||
| CN201110083429.8 | 2011-04-02 | ||
| CN201110083429 | 2011-04-02 | ||
| CN201110085045 | 2011-04-06 | ||
| CN201110085045.X | 2011-04-06 | ||
| CN2012100846158A CN102536511A (en) | 2011-03-28 | 2012-03-27 | High thrust aircraft engine |
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| CN105545523A (en) * | 2014-10-27 | 2016-05-04 | 熵零股份有限公司 | Pressure gas energy recovery method and device and heat power system adopting device |
| CN105986930A (en) * | 2015-03-02 | 2016-10-05 | 袁志平 | Exhaust mixer of turbofan engine |
| CN107620654A (en) * | 2016-07-14 | 2018-01-23 | 北京航天动力研究所 | A kind of hydrogen-oxygen expansion cycles rocket engine coaxial jet formula blender |
| CN108626024A (en) * | 2018-06-13 | 2018-10-09 | 杨清太 | A kind of jet-propelled wind turbine enhancer constructive method |
| CN108999725A (en) * | 2018-07-19 | 2018-12-14 | 北京航空航天大学 | A kind of nozzles with injector of the double bell injection casings of band |
| CN110486162A (en) * | 2017-08-29 | 2019-11-22 | 熵零技术逻辑工程院集团股份有限公司 | A kind of electric transmission injection-type engine cooling system |
| CN110486170A (en) * | 2017-08-29 | 2019-11-22 | 熵零技术逻辑工程院集团股份有限公司 | A kind of axis transmission injection-type engine cooling system |
| CN110486164A (en) * | 2017-08-29 | 2019-11-22 | 熵零技术逻辑工程院集团股份有限公司 | A kind of electric transmission engine-cooling system |
| JP2020200940A (en) * | 2019-06-10 | 2020-12-17 | 宮内 直 | Outer cylinder of propulsion machine such as flying car |
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| JP2020200940A (en) * | 2019-06-10 | 2020-12-17 | 宮内 直 | Outer cylinder of propulsion machine such as flying car |
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Application publication date: 20120704 |