CN203906118U - Gas cooling system for turbine-based combined-cycle engine - Google Patents
Gas cooling system for turbine-based combined-cycle engine Download PDFInfo
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- CN203906118U CN203906118U CN201420151044.XU CN201420151044U CN203906118U CN 203906118 U CN203906118 U CN 203906118U CN 201420151044 U CN201420151044 U CN 201420151044U CN 203906118 U CN203906118 U CN 203906118U
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Abstract
The utility model discloses a gas cooling system for a turbine-based combined-cycle engine. The combined-cycle engine is combined with a turbojet engine and a dual-mode ramjet engine, thus solving the problems that flow passages shared by the engines are less, the deadweight is heavy, supersonic combustion is difficult to realized and the like; in the aspect of the engine, a fan rotor is arranged between a low-pressure compressor and a high-pressure compressor and is used in combination with design such as deceleration drive and fuel gas pre-cooling, and the overall performance of the engine is greatly improved; the gas cooling system for the turbine-based combined-cycle engine integrates the advantages of the turbojet engine and the dual-mode ramjet engine in the respective applicable flight range, thus having the advantages of high conventional taking-off and landing capability, reuse, high reliability, good low-speed performance, low technical risk and the like, and having a very good engineering application prospect.
Description
Technical field
The utility model relates to a kind of motor of aircraft.
Background technique
In recent years, round the various possibilities of following fighter development, people have carried out exploring widely.One of main direction has: flying speed faster, higher flying height and unmanned control.Require it can take into account the flight performance under various height, various attitude.More focus on very-long-range striking capabilities, outstanding hypervelocity flight, and further strengthen subsonic velocity mobility and the ultrasound velocity mobility of modern combat aircraft at low-to-medium altitude.Wherein, motor is middle work on high both, also can in space, work, and therefore, motor is very important.
Model utility content
Technical problem to be solved in the utility model is to provide a kind of turbine base combined cycle engine gas system of optimizing flight performance.
For solving the problems of the technologies described above, the technical solution of the utility model is: turbine base combined cycle engine gas system, under low speed mode or high speed mode, work or conversion mutually, and comprise turbojet engine and dual-mode scramjet;
Described dual-mode scramjet comprises the by-pass air duct that is provided with by-pass air duct suction port, and the front end of described by-pass air duct is outer culvert intake duct; The internal surface of described outer culvert intake duct is provided with propellant spray mouth;
Described turbojet engine is arranged in described by-pass air duct, comprise the intension intake duct that is provided with main duct suction port, in described intension intake duct, low pressure compressor is installed, described main duct suction port is positioned at described outer culvert intake duct, described main duct suction port is distinguish and the taper case that can close completely, and it is tip cone forward that described taper case is closed rear profile; After described intension intake duct, be provided with fan propeller, described fan propeller comprises fan blade, fan petiole and rotor body, and described fan blade is positioned at described by-pass air duct; The described by-pass air duct being positioned at after described fan propeller is provided with main main duct, in described main main duct, high-pressure compressor is installed, in described main main duct after described high-pressure compressor, be provided with precompression chamber, after described precompression chamber, be provided with intension firing chamber, described intension is provided with propellant spray mouth in firing chamber; Described intension is provided with one-level high-pressure turbine behind firing chamber, and described high-pressure turbine is fixedly connected with by high pressure rotor axle with described high-pressure compressor; After described high-pressure turbine, be provided with two-stage low-pressure turbine, described low-pressure turbine turns to contrary with high-pressure turbine; Described low-pressure turbine is fixedly connected with by low pressure rotor axle with low pressure compressor, and described fan propeller is connected with described low pressure rotor axle by fan speed change device; Described high pressure rotor axle is hollow shaft and is sleeved on outside described low pressure rotor axle, and described fan propeller is arranged on described low pressure rotor axle;
Described main main duct after described low-pressure turbine is provided with main main duct relief opening, the exhaust adjustment sheet that described main main duct relief opening is provided with size-adjustable and can closes completely; Described main main duct relief opening is positioned at described by-pass air duct; Between described vector spout and described main main duct relief opening, be provided with the by-pass air duct prolonged section as tail pipe burner;
In described precompression chamber, be provided with heat exchanger, the double fuel feed line being connected with described propellant spray mouth that does of described heat exchanger.
As preferred technological scheme, the spatial placement of the described by-pass air duct outside described main main duct is outer culvert firing chamber; Whole described by-pass air duct inwall is provided with heat exchanger, the double fuel feed line being connected with described propellant spray mouth that does of described heat exchanger.
Owing to having adopted technique scheme, the utility model air stream after precompression chamber by heat exchanger precooling, temperature decline continue supercharging, thereby the work of sharing part gas compressor.This can design still less the progression of high-pressure compressor, thereby strengthens engine efficiency, increases thrust weight ratio.
Brief description of the drawings
Fig. 1 is that the utility model embodiment uses the structure principle chart at combined engine;
Fig. 2 is the structure principle chart of the core engine of the utility model embodiment combined engine;
Fig. 3 is the structure principle chart of the utility model embodiment fan propeller;
Fig. 4 is the fundamental diagram of the utility model embodiment fan blade;
Fig. 5 is the fundamental diagram one of the utility model embodiment low pressure compressor;
Fig. 6 is the fundamental diagram two of the utility model embodiment low pressure compressor;
Fig. 7 is the fundamental diagram of the utility model embodiment combined engine under turbofan mode;
Fig. 8 is the fundamental diagram of the utility model embodiment combined engine under the jet mould state of whirlpool;
Fig. 9 is the fundamental diagram of the utility model embodiment combined engine supersonic combustion punching press mode;
Figure 10 is the fundamental diagram of the utility model embodiment combined engine subsonic combustion punching press mode;
In figure: 1-dual-mode scramjet; 2-turbojet engine; 3-by-pass air duct suction port; Lip under 31-; 32-by-pass air duct prolonged section; 33-is contained intake duct outward; 4-vector spout; 124-is contained firing chamber outward; 12-by-pass air duct; 13-propellant spray mouth; 141-main duct suction port; 14-intension intake duct; 15-low pressure compressor; 16-taper case; 17-fan propeller; 171-fan blade; 172-fan petiole; 173-rotor body; The main main duct of 18-; The main main duct relief opening of 181-; 182-exhaust adjustment sheet; 19-high-pressure compressor; 20-precompression chamber; 21-intension firing chamber; 22-high-pressure turbine; 221-high pressure rotor axle; 23-low-pressure turbine; 231-low pressure rotor axle; 25-heat exchanger; 26-fuel feed line; 27-central gear; 28-planetary pinion; 29-gear ring; 30-clutch; 31-guide plate.
Embodiment
Understand for technical characteristics of the present utility model, object and effect being had more clearly, now contrast brief description of the drawings embodiment of the present utility model.
Below in conjunction with using motor of the present utility model to be further described the utility model.This aircraft engine is divided into turbofan mode, whirlpool jet mould state, subsonic combustion punching press mode and supersonic combustion punching press mode (both can be collectively referred to as " dual-mode scramjet " afterwards).
As shown in Figure 1, based on the present embodiment, to low-speed high-thrust and the requirement simultaneously of hypersonic power, the combined engine of the present embodiment is designed to tandem turbine base combined cycle engine.Combined engine, when subsonic velocity provides compared with high thrust, also can provide flying power, and can transit to from principal and subordinate's subsonic velocity hypersonic in the time of hypersonic flight.The combined engine of the present embodiment is in friction speed interval, respectively with four kinds of different mode work, respectively: turbofan mode, v ∈ [0Ma, 0.8Ma]; Whirlpool jet mould state, v ∈ [0.8Ma, 3Ma]; Subsonic combustion punching press mode, v ∈ [3Ma, 5Ma]; Supersonic combustion punching press mode, v ∈ [5Ma, 15Ma].
As shown in Figure 2, the core engine of combined engine can be regarded a unconventional turbojet engine 2 as, and high-pressure compressor 19 is level Four axial flow, Blisk.Air inlet place of core engine after fan propeller 17 is called the suction port of main main duct 18, is provided with here to regulate to open big or small guide plate 31.This guide plate 31 is called flow-rate ratio adjustment sheet, it open size and can regulate the inside and outside flow-rate ratio of containing, thus make motor change flow-rate ratio in turbofan mode according to the different speed of aircraft and demand, improve the conformability of turbofan mode.
After high-pressure compressor 19, be precompression chamber 20, precompression chamber 20 is exactly the space of a hollow, within be provided with heat exchanger 25, the double fuel feed line 26 being connected with described propellant spray mouth 13 that does of described heat exchanger 25.Air is rear by heat exchanger 25 precoolings at the precompression chamber 20 of flowing through, and temperature declines and continues supercharging, thus the work of sharing part gas compressor.This can design still less the progression of high-pressure compressor 19, thereby strengthens engine efficiency, increases thrust weight ratio.
After precompression chamber 20, connect intension firing chamber 21, the fuel mix after-combustion that air is vaporized in this and preheating.Behind intension firing chamber 21, be one-level high-pressure turbine 22, high-pressure turbine 22 is called high pressure rotor with the rotor that high-pressure compressor 19 is fixedly connected to form by high pressure rotor axle 221.After high-pressure turbine 22, be two-stage low-pressure turbine 23, turn to contrary with high-pressure turbine 22.Low-pressure turbine 23 links with low pressure compressor 15 and fan propeller 17, and low-pressure turbine 23 does not comprise fan propeller 17 with low pressure compressor 15() rotor that is fixedly connected with rear formation by low pressure rotor axle 231 is called low pressure rotor.This high and low pressure rotor, to the working method turning, acts on two most of counteractings of epitrochanterian gyrostatic moment can make aircraft maneuvering flight time, reduce the moment load to aircraft, strengthens the handling of aircraft; This structure makes to be loaded on two intermediate bearing inside and outside ring switched in opposite between rotor in addition, has reduced the rotating speed of retainer with the relative inside and outside ring of rotor assembly, favourable to the work of bearing; And high and low pressure rotor is to turning the combustion gas guide vane that also can save between high-pressure turbine 22, low-pressure turbine 23.Be to consider that low-pressure turbine 23 also will drive fan propeller 17 except will driving low pressure compressor 15 and low-pressure turbine 23 is designed to secondary, its duty ratio is larger.Can increase complex structure degree and weight though be designed to secondary, reduce the load of single stage turbine, improve turbine efficiency, thereby export more high power for low pressure compressor 15 and fan propeller 17.It after turbine, is main main duct relief opening 181, described main main duct relief opening 181 places are provided with exhaust adjustment sheet 182, its size-adjustable and can closing completely, its effect is except regulating core engine exhaust, can also form and seamlessly transit at subsonic combustion punching press mode and supersonic combustion punching press mode and by-pass air duct 12, burning and gas-exhausting will expand for the first time at this.
The combined engine of the present embodiment has adopted the scheme of provided with fan rotor 17 between low pressure compressor 15 and high-pressure compressor 19, in increasing turbofan mode and whirlpool jet mould state thrust efficiency, can better adapt to subsonic combustion punching press mode and supersonic combustion punching press mode.
As shown in Figure 3 and Figure 4, the fan blade 171 of the present embodiment is variable-distance, and variable-distance fan blade 171 designs except regulating the pressure ratio of fan in turbofan mode, can also better adapt to other mode to by-pass air duct 12 permeabilities and resistance demand.Fan propeller 17 comprises fan blade 171, fan petiole 172 and rotor body 173 3 parts, and a part is the fan petiole 172 that is positioned at main duct, and it is comparatively very thin, only plays a supportive role; The part that is in by-pass air duct 12 is only fan blade 171, and therefore fan is only given by-pass air duct 12 supercharging airs.
Fan propeller 17 links by fan speed change device and low pressure rotor axle 231, and this interlock can disconnect by clutch 30.In the time of turbofan mode, fan propeller 17 is driven by low pressure rotor axle 231, and fan blade 171 is to by-pass air duct 12 supercharging airs; And in the time of whirlpool jet mould state, subsonic combustion punching press mode and this three mode of supersonic combustion punching press mode, fan propeller 17 will disconnect interlock with low pressure rotor axle 231, stopping fan rotation, fan blade 171 displacements are adjusted to along slurry position, fan blade 171 is parallel with incoming flow, and fan blade 171 resistances are reduced as far as possible.The variable-distance of fan blade 171 has embodied engine design to the taking into account of different modalities, and has met the demand of the wide flight envelope of the present embodiment.
In the present embodiment, described fan speed change device comprises the central gear 27 being rotatably installed on described low pressure rotor axle 231, be rotatably installed in the planetary pinion 28 on described central gear 27, the outer gear ring 29 that is provided with of described planetary pinion 28, described gear ring 29 is fixedly connected with rotor body 173, described rotor body 173 peripheries are installed with described fan petiole 172, and described rotor body 173 is rotatably installed on described low pressure rotor axle 231; Between described central gear 27 and described low pressure rotor axle 231, clutch 30 is installed.
As shown in Figure 5 and Figure 6, in order to reduce resistance and to increase air mass flow, the low pressure compressor 15 in motor forefront is designed to three grades of axial-flow compressors, Blisk.Low pressure compressor 15 has independently intake duct, is called intension intake duct 14.Intension intake duct 14 is in outer culvert intake duct 33, and its cross section is for circular and can close completely, and closing rear profile is a cone before sensing, can play compression in subsonic combustion punching press mode and external duct 12 air inlets of supersonic combustion punching press mode.
As shown in Figure 1, the intake duct of by-pass air duct 12 is called outer culvert intake duct 33, and its front half part is being born all air inlets of main main duct 18 and by-pass air duct 12, and intension intake duct 14 is being wrapped in rear portion.In the present embodiment, the lower lip 31 of by-pass air duct suction port 3 is the certain angle of deflection up and down, is used for regulating air inlet.Outer culvert intake duct 33 is inclined upwardly slightly, and this is the result that global design is made overall plans, and can make the resistance of aircraft increase to some extent, but also makes intake duct have certain bridging effect to engine blade, is conducive to stealthy.
By-pass air duct 12 rear portions are provided with the by-pass air duct prolonged section 32 of the core engine of being longer than main main duct 18, make core engine exhaust be mixed and be discharged by by-pass air duct prolonged section 32 with by-pass air duct 12 exhausts.This by-pass air duct prolonged section 32 mixing modes make combined engine in the time of turbofan mode and whirlpool jet mould state, and main main duct 18, by-pass air duct 12 air-flows can again do energy interchange before ejection, thereby improve engine efficiency; By-pass air duct prolonged section 32 has function the convenient vector spout 4 of installing of tail pipe burner.
By-pass air duct 12 is outdoor except the afterbunring at rear portion, in the middle, arises from fan propeller 17 until this section of main main duct relief opening, for independently firing chamber of by-pass air duct 12, is called outer culvert firing chamber 124.This firing chamber is as the main combustion chamber of dual-mode scramjet 1.
The combined engine use liquid hydrogen of the present embodiment or liquid hydrocarbon, liquid oxygen are as fuel, simultaneously as heat exchanging agent.In intension firing chamber 21, establish propellant spray mouth 13 with outer culvert intake duct 33 walls.
At the present embodiment, in whole by-pass air duct 12 inwalls, precompression chamber 20 and propellant spray mouth 13 places are provided with heat exchanger 25.Wherein the heat exchanger 25 of by-pass air duct 12 inwalls is divided into independently two parts of front and back, and boundary is near fan propeller 17.
Arranging of heat exchanger 25 can shift to an earlier date precooling air inlet, increases the compression efficiency of air inlet; Also can play thermal protection effect to propellant spray mouth 13.And use fuel can reduce structure weight and the complexity of heat-exchange system as heat exchanging agent, simplify piping layout; Also make fuel shift to an earlier date preheating vaporization, more favourable to burning.
Mapping mode between working method when combined engine different modalities and mode:
1. turbofan mode
As shown in Figure 7, now outer contain intake duct 33 and intension intake duct 14 all open and open larger, main main duct Exhaust Open.Now fan is in turbofan mode, and fan propeller 17 is driven by low pressure rotor by low pressure rotor-fan gearing down system, and fan blade 171 is to by-pass air duct 12 supercharging airs.In precompression chamber 20, open with the heat exchanger 25 at propellant spray mouth 13 places, fuel first flows through the heat exchanger 25 in precompression chamber 20, then flows through the heat exchanger 25 at propellant spray mouth 13 places, finally injects firing chamber and mixes with air.
At main duct, air flows into intension intake duct 14 through outer culvert intake duct 33 front half parts, then flows into low pressure compressor 15.Low pressure compressor 15 is driven by low-pressure turbine 23, to supercharging air.Due to the design of fan in the middle of combined engine employing, therefore low pressure compressor 15 can not be subject to the unfavorable interference of fan.The fan petiole 172 that major part can be flow through fan blade 171 by the air of low pressure compressor 15 superchargings enters core engine; And have small part to be spilled over to by-pass air duct 12 from fan propeller 17, and can increase the pressure of by-pass air duct 12 exhausts and the fuel efficiency of motor, its effect is similar to " the middle duct " that the U.S. is the change circulation turbofan engine of the 6th generation opportunity of combat development.
High-pressure compressor 19 is driven rotation by high-pressure turbine 22, to enter core engine by the high-pressure air supercharging again of low pressure compressor 15 superchargings.Air is discharged into precompression chamber 20 afterwards.In precompression chamber 20, be pressurized and the high pressure draught of temperature rise flows through heat exchanger 25, do heat exchange with low temp fuel.Fuel heats up, air-flow cooling.The cooling of air-flow can improve compression efficiency again, prepares as burning.
Precompression chamber 20 is also used for pressurized air, and it has shared the task of a part of gas compressor pressurized air, thereby the progression of high-pressure compressor 19 can design still less.Therefore the high-pressure compressor 19 of combined engine only has level Four rotor blade, has reduced structure complexity and the weight of motor, has shortened size, has reduced the startup inertia of high pressure rotor.And less gas compressor progression also just means the load that turbine is less, to the energy consumption of combustion gas also just still less, combustion gas can retain more multipotency and, in order to drive low pressure rotor and last ejection to form thrust, indirectly improve rotating speed and the motor power of low pressure rotor.And precompression chamber 20 these hollow spaces between firing chamber and gas compressor, can play the effect of certain inhibition engine surge.
Fuel is after the interior burning in intension firing chamber 21, and combustion gas is flow through successively and driven high-pressure turbine 22 and low-pressure turbine 23 to rotate.Combustion gas afterwards enters by-pass air duct 12 rear portions through main main duct relief opening, will mix finally and be discharged by vector spout 4 with by-pass air duct 12 exhausts there.
At by-pass air duct 12, air enters by-pass air duct 12 through outer culvert intake duct 33.Air mixes through the air by low pressure compressor 15 superchargings fan forced and that overflow from intension with part afterwards, then from core engine, flows through and coolant core machine.Finally mix with core engine exhaust, sprayed by vector spout 4.Compared with the turbofan engine of modern combat aircraft, the bypass ratio of combined engine is larger, has higher efficiency or larger thrust; This is to be also the reserved enough spaces of dual-mode scramjet 1 simultaneously.
As shown in Figure 7, heat exchanger 25 and the external pipeline of propellant spray mouth 13(that fuel flows in precompression chamber 20 successively do not provide), finally at the interior injecting compressed air in intension firing chamber 21.
2. whirlpool jet mould state
As shown in Figure 8, now by-pass air duct suction port 3 opens littlely, and the taper case 16 of main duct suction port 141 opens larger.The clutch 30 of described fan speed change device disconnects, and described low pressure rotor axle 231 dallies, and described central gear 27 is motionless, thereby makes fan propeller 17 and low pressure rotor disconnect interlock.Now 23 of low-pressure turbines are used for driving low pressure compressor 15, and low pressure compressor 15 rise of rotational speed have met whirlpool jet mould state to the high efficiency demand of gas compressor.Now fan propeller 17 stalls, fan blade 171 displacements, blade is parallel to incoming flow, reduces fan resistance as far as possible.The operation mode of other parts is similar during to turbofan mode.
Air enters low pressure compressor 15 through main duct suction port 141 and intension intake duct 14, flow into core engine by most of air after low pressure compressor 15 superchargings through the fan petiole 172 of fan blade 171, and a small part air can be spilled over to by-pass air duct 12, when coolant core machine, increase by-pass air duct 12 stream pressures, improve engine efficiency.Flow into the air of core engine and flow through successively high-pressure compressor 19, precompression chamber 20, intension firing chamber 21 and high-pressure turbine 22 again, the working method of core engine is identical during with turbofan.
Because fan propeller 17 and low pressure rotor disconnect interlock, the load of low-pressure turbine 23 is reduced, rotating speed promotes, thereby improves the pressure ratio of low pressure compressor 15, has adapted to turbojet engine 2 to the high efficiency requirement of gas compressor.
3. supersonic combustion punching press mode
Because the most of design point in dual-mode scramjet 1 is in order to meet supersonic combustion punching press mode, so this specification is narrated before supersonic combustion punching press mode is placed on to subsonic combustion punching press mode.
In the time of supersonic combustion punching press mode, the taper case 16 of main duct suction port 141 is closed completely, forms the cone before a sensing.The suction port of outer culvert intake duct 33 opens larger, and main main duct relief opening is closed completely, forms the cone after a sensing.Fan blade 171 is still parallel to incoming flow, reduces the resistance of fan blade 171 as far as possible.In this mode, the heat exchanger 25 at whole by-pass air duct 12 inwalls and propellant spray mouth 13 places is opened.
Air enters outer culvert intake duct 33 by outside, and contains outside under the effect of the series of shock string in intake duct 33 and continue deceleration supercharging.Above, mention, intake duct is inclined upwardly a little, and this will certainly increase resistance.But the first shock wave that suction port front end produces slightly upward deflects air flow direction thereafter, and acclivitous intake duct has in fact just in time adapted to the flow direction of air-flow.
Inlet stream is crossed outer culvert intake duct 33 afterwards and fuel mix flows through fan propeller 17 again, after fan propeller 17, is outer culvert firing chamber 124.Outer culvert firing chamber 124 arises from fan propeller 17 and terminates in main intension to relief opening, and its length is very large as seen, and the present embodiment ensures burning fully under ultrasound velocity to grow the mode of firing chamber.But its problem of bringing is to need cooling area also very large, this problem solves by the fuel that plays cooling action flowing through in inwall herein.
Because combined engine adopts middle fan design, intension, in fan place "off", communicates the provided with internal duct and external duct 12 at fan place.Therefore can depart from wall at fan place at the boundary layer of intension outer wall and be involved in by-pass air duct 12 air-flows.And the high velocity air of by-pass air duct 12 can aspirate the air in intension by ejector action.The air pressure of intension can be because ejector action, far below by-pass air duct 12, even becomes class hollow state.This can form at fan place transverse-pressure gradient, the trend that the by-pass air duct 12 oriented centres of air-flow are drawn close.Simultaneously fan also plays the effect of certain vortex generator, and this two kinds of effects produce very complicated pneumatic coupling mutually, makes to form after fan the higher and baroque eddy current of intensity.The boundary layer of intension outer wall is bound to be involved in eddy current, and the eddy current of by-pass air duct 12 inwalls is also probably involved in.Research shows, in the time of the abundant premix of fuel, in the boundary layer of High Temperature High Pressure, can burn in advance.The boundary layer that burning has occurred is involved in after eddy current, can cause rapidly the burning of other pre-mixing gas combustion, thereby light outer culvert firing chamber 124.The particular design configuration of middle fan, makes combined engine be spread and be maintained flame by the mode that forms eddy current and pre-burning boundary layer is involved in, and has solved supersonic combustion igniting, flame spread and has maintained the problem of flame difficulty.
4. subsonic combustion punching press mode
As shown in figure 10, the working method of the working method of motor in the time of subsonic combustion punching press mode during with supersonic combustion punching press mode is identical, what just contain outside firing chamber 124 interior generations is subsonic combustion, and supersonic flow is contained outside in intake duct 33 and just slowed down diffusion to subsonic velocity.
Now the outer suction port of containing intake duct 33 opens littlely, and vector spout 4 is adjusted to shrinkage expansion spout, and the working state of other tunable component is identical during with supersonic combustion punching press mode.
Incoming flow is contained outside the interior deceleration of intake duct 33 and is pressurized to subsonic velocity also and fuel mix, then accelerates to ultrasound velocity ejection by shrinkage expansion spout after 124 burnings of outer culvert firing chamber.
The combined engine of the present embodiment combines the designs such as controllable pitch fan, middle fan, low pressure rotor-fan gearing down system, combustion gas precooling, in realizing hypersonic flight power, has also obtained high thrust, big thrust loading at low speed.By optimizing the design of the each runner of each parts, the problems such as turbine base combined cycle engine runner shares less, deadweight is many are solved.Improve the thrust efficiency of turbofan and whirlpool jet mould state by middle fan design, and solved supersonic combustion punching press mode engine ignition, maintain the problem of flame difficulty.Combined engine has met the power demand of the wide speed envelope curve of the present embodiment aircraft, makes it under all speed, all have powerful heart.
The utility model incorporates the designs such as combustion gas precooling, gearing down, middle fan the turbofan mode of combined engine, by further optimization detailed design, improve efficiency and the thrust weight ratio of motor, thereby ensured the high power demand of the utility model as a fighter.The special intension configuration of fan design in the middle of utilizing, has solved the difficult problem of lighting a fire when dual-mode scramjet 1 surpasses combustion.Further the function of the each parts of optimum organization motor, each duct, when making it meet hypersonic power demand, has greater efficiency.
As mentioned above, described particularly embodiment of the present utility model in the above, but the utility model is not limited to this.It should be appreciated by those skilled in the art, can carry out various amendments, combination, sub-portfolio or replacement according to designing requirement or other factors, and they are in the scope of claims and equivalent thereof.
Claims (2)
1. turbine base combined cycle engine gas system is worked or conversion mutually under low speed mode or high speed mode, it is characterized in that: comprise turbojet engine and dual-mode scramjet;
Described dual-mode scramjet comprises the by-pass air duct that is provided with by-pass air duct suction port, and the front end of described by-pass air duct is outer culvert intake duct; The internal surface of described outer culvert intake duct is provided with propellant spray mouth;
Described turbojet engine is arranged in described by-pass air duct, comprise the intension intake duct that is provided with main duct suction port, in described intension intake duct, low pressure compressor is installed, described main duct suction port is positioned at described outer culvert intake duct, described main duct suction port is distinguish and the taper case that can close completely, and it is tip cone forward that described taper case is closed rear profile; After described intension intake duct, be provided with fan propeller, described fan propeller comprises fan blade, fan petiole and rotor body, and described fan blade is positioned at described by-pass air duct; The described by-pass air duct being positioned at after described fan propeller is provided with main main duct, in described main main duct, high-pressure compressor is installed, in described main main duct after described high-pressure compressor, be provided with precompression chamber, after described precompression chamber, be provided with intension firing chamber, described intension is provided with propellant spray mouth in firing chamber; Described intension is provided with one-level high-pressure turbine behind firing chamber, and described high-pressure turbine is fixedly connected with by high pressure rotor axle with described high-pressure compressor; After described high-pressure turbine, be provided with two-stage low-pressure turbine, described low-pressure turbine turns to contrary with high-pressure turbine; Described low-pressure turbine is fixedly connected with by low pressure rotor axle with low pressure compressor, and described fan propeller is connected with described low pressure rotor axle by fan speed change device; Described high pressure rotor axle is hollow shaft and is sleeved on outside described low pressure rotor axle, and described fan propeller is arranged on described low pressure rotor axle;
Described main main duct after described low-pressure turbine is provided with main main duct relief opening, the exhaust adjustment sheet that described main main duct relief opening is provided with size-adjustable and can closes completely; Described main main duct relief opening is positioned at described by-pass air duct; Between vector spout and described main main duct relief opening, be provided with the by-pass air duct prolonged section as tail pipe burner;
The spatial placement of the described by-pass air duct outside described main main duct is outer culvert firing chamber; In described precompression chamber, be provided with heat exchanger, the double fuel feed line being connected with described propellant spray mouth that does of described heat exchanger.
2. turbine base combined cycle engine gas system as claimed in claim 1, is characterized in that: whole described by-pass air duct inwall is provided with heat exchanger, the double fuel feed line being connected with described propellant spray mouth that does of described heat exchanger.
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| CN105156229A (en) * | 2015-09-29 | 2015-12-16 | 清华大学 | Mass injection-assistant turbine-based combined cycle engine |
| CN105156227A (en) * | 2015-09-29 | 2015-12-16 | 清华大学 | Pre-cooling air-breathing type variable cycle engine |
| CN106438104A (en) * | 2016-09-18 | 2017-02-22 | 中国科学院工程热物理研究所 | Fuel-rich pre-burning turbofan engine |
| CN107748493A (en) * | 2017-09-11 | 2018-03-02 | 南京航空航天大学 | TBCC dcs communication network mixed topology structural optimization methods |
| CN113915003A (en) * | 2021-09-15 | 2022-01-11 | 南京航空航天大学 | Based on NH3Extremely-wide-speed-domain multi-mode combined power cycle system and method |
| CN114518229A (en) * | 2020-11-20 | 2022-05-20 | 北京航天试验技术研究所 | Double-duct diffuser for supersonic free jet test of air-breathing engine |
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2014
- 2014-03-31 CN CN201420151044.XU patent/CN203906118U/en not_active Expired - Fee Related
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104760703A (en) * | 2015-03-09 | 2015-07-08 | 中国航空工业集团公司沈阳飞机设计研究所 | Cooling mechanism for ramjet engine |
| CN105156229A (en) * | 2015-09-29 | 2015-12-16 | 清华大学 | Mass injection-assistant turbine-based combined cycle engine |
| CN105156227A (en) * | 2015-09-29 | 2015-12-16 | 清华大学 | Pre-cooling air-breathing type variable cycle engine |
| CN106438104A (en) * | 2016-09-18 | 2017-02-22 | 中国科学院工程热物理研究所 | Fuel-rich pre-burning turbofan engine |
| CN107748493A (en) * | 2017-09-11 | 2018-03-02 | 南京航空航天大学 | TBCC dcs communication network mixed topology structural optimization methods |
| CN114518229A (en) * | 2020-11-20 | 2022-05-20 | 北京航天试验技术研究所 | Double-duct diffuser for supersonic free jet test of air-breathing engine |
| CN113915003A (en) * | 2021-09-15 | 2022-01-11 | 南京航空航天大学 | Based on NH3Extremely-wide-speed-domain multi-mode combined power cycle system and method |
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