CN105221295A - A kind of punching press-turbojet compound aeroengine - Google Patents
A kind of punching press-turbojet compound aeroengine Download PDFInfo
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- CN105221295A CN105221295A CN201510747821.6A CN201510747821A CN105221295A CN 105221295 A CN105221295 A CN 105221295A CN 201510747821 A CN201510747821 A CN 201510747821A CN 105221295 A CN105221295 A CN 105221295A
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Abstract
The invention discloses a kind of punching press-turbojet compound aeroengine, object is to solve existing gas turbine engine complex structure, operational speed range is limited, and pressed engine can not start voluntarily, cannot run under the low speed, cooling is difficulty comparatively, and requires higher problem to complete machine high temperature resistant property.This aeroengine comprises punching press suction cone, by-pass air duct casing, air-intake guide vane, liquid oxygen modulating valve, liquid nitrogen modulating valve, main duct casing, straightener(stator) blade, fuel regulator valve, centrifugal compressor, Diffuser, firing chamber, concentric shafts, turbine, main duct rectification spout, starting electrical machinery etc.The present invention effectively utilizes the advantage of punching press effect and turbojet engine, and adds pre-cooled process, efficiently solves pressed engine and starts and fast state air inlet, and the problem of engine power restriction.Structure of the present invention is simple, and with low cost, efficiency is high, and operational speed range is wide, and complete machine running temperature is low, has good application prospect.
Description
Technical field
The present invention relates to aviation field, especially aeroengine field, be specially a kind of punching press-turbojet compound aeroengine.The present invention, as a kind of punching press-turbojet compound aeroengine of low cost, has good application prospect.
Background technique
Aeroengine provides the motor of flight required drive as aircraft, and it is a kind of high complexity and accurate thermal machine.Aeroengine, as the heart of aircraft, is described as " flower of industry ", and it directly affects the performance of aircraft, reliability and Economy, is the important embodiment of a national science and technology, industry and military capability of the country.Because the technical threshold of aeroengine is very high, only have a few countries such as the U.S., Russia, Britain, France independently can develop High Performance Aeroengine at present in the world.
According to the difference of operation mechanism, aeroengine is divided into piston aviation engine, gas turbine engine, pressed engine three class.
Wherein, piston aviation engine is the aeroengine applied on aircraft or helicopter in early days, is mainly used in carrying screws or rotor.At present, piston aviation engine is widely used on light airplane, helicopter and ultra light aircraft.
Gas turbine engine is the aeroengine be most widely used, and it has gas compressor, firing chamber and gas turbine, and main Types comprises turbojet engine, turbofan engine, turboprop engine and turboaxle motor.Wherein, turboprop engine is mainly used in the aircraft that speed per hour is less than 800 kms; Turboaxle motor is mainly used in as helicopter provides power; Turbofan engine is mainly used in the higher aircraft of speed; Turbojet engine is mainly used in supersonic aircraft.
Pressed engine has the feature without gas compressor and gas turbine, and the air entering firing chamber utilizes punching press effect supercharging during high-speed flight.Thus, it has simple structure, advantage that thrust is large, is specially adapted to high speed high-altitude flight.
But also there is certain deficiency in existing aeroengine.Gas turbine engine applies maximum aeroengines as current, and its parts are various, and blade structure is complicated, and thus its processing cost is high, and processing technology is very complicated.In addition, along with the raising of motion speed, by the impact that airspeed uprises, the temperature rise of gas turbine engine is also obvious gradually, causes it to be difficult to work, causes the operational speed range of gas turbine engine limited.Pressed engine, owing to acting on based on high-speed air punching press effect, therefore can not start voluntarily, must be promoted by other advancing means, to obtain toggle speed, also cannot run under the low speed.Meanwhile, due to the rising of intake temperature under punching press effect, require also to improve further for complete machine high temperature resistant property, its requirement for firing chamber is very harsh.In addition, the cooling of pressed engine is also itself insoluble problem always.
For this reason, in the urgent need to a kind of new aeroengine, to solve the problem.
Summary of the invention
Goal of the invention of the present invention is: limited for existing gas turbine engine complex structure, operational speed range, and pressed engine can not start voluntarily, cannot run under the low speed, cooling is difficulty comparatively, and higher problem is required to complete machine high temperature resistant property, a kind of punching press-turbojet compound aeroengine is provided.The present invention effectively utilizes the advantage of punching press effect and turbojet engine, and adds pre-cooled process, efficiently solves pressed engine and starts and fast state air inlet, and the problem of engine power restriction.Structure of the present invention is simple, and with low cost, efficiency is high, and operational speed range is wide, and complete machine running temperature is low, has good application prospect.
To achieve these goals, the present invention adopts following technological scheme:
A kind of punching press-turbojet compound aeroengine, comprise punching press suction cone, by-pass air duct casing, air-intake guide vane, for the liquid oxygen modulating valve be connected with liquid nitrogen device, for the liquid nitrogen modulating valve be connected with liquid nitrogen plan, be arranged on the main duct casing inside by-pass air duct casing, straightener(stator) blade, for the fuel regulator valve be connected with oil burning installation, centrifugal compressor, Diffuser, firing chamber, concentric shafts, turbine, main duct rectification spout, the starting electrical machinery be connected with main duct casing, the power supply means be connected with starting electrical machinery, control system, be arranged on the projection inside by-pass air duct casing,
The air outlet hole that the rear portion of described punching press suction cone is provided with cavity, is connected with cavity, described air-intake guide vane is hollow structure, described punching press suction cone is connected with by-pass air duct casing by air-intake guide vane, described liquid oxygen modulating valve, liquid nitrogen modulating valve are connected with the hollow structure in air-intake guide vane respectively, and described punching press suction cone and by-pass air duct casing form punching press runner;
Described straightener(stator) blade is hollow structure, described main duct casing is connected with by-pass air duct casing by straightener(stator) blade, described fuel regulator valve is connected with firing chamber by straightener(stator) blade, described Diffuser, firing chamber is successively set in main duct casing, described centrifugal compressor is connected with firing chamber through Diffuser, described concentric shafts is through firing chamber, the outlet of described firing chamber is provided with stator blade, described stator blade is between firing chamber and turbine, described main duct rectification spout is arranged on turbine rear end, described centrifugal compressor, turbine is connected with concentric shafts respectively, described starting electrical machinery is connected with concentric shafts and starting electrical machinery can drive concentric shafts to rotate,
Described projection is between air outlet hole and centrifugal compressor, and described control system is connected with liquid oxygen modulating valve, liquid nitrogen modulating valve, fuel regulator valve respectively.
The nitrogen that can flow out with air outlet hole through the gas of punching press runner, oxygen collide, and realize exchange heat.
Described projection is triangular in shape along the sectional view of by-pass air duct casing radial direction.
Described set-up of control system is in main duct casing one end near punching press suction cone.
Also comprise the liquid nitrogen device be connected with liquid oxygen modulating valve, the liquid nitrogen plan be connected with liquid nitrogen modulating valve.
Also comprise the oil burning installation be connected with fuel regulator valve.
Described power supply means is power line.
For foregoing problems, the invention provides a kind of punching press-turbojet compound aeroengine, be specially a kind of punching press-turbojet compound aeroengine of low cost.It comprises punching press suction cone, by-pass air duct casing, air-intake guide vane, for the liquid oxygen modulating valve be connected with liquid nitrogen device, for the liquid nitrogen modulating valve be connected with liquid nitrogen plan, be arranged on the main duct casing inside by-pass air duct casing, straightener(stator) blade, for the fuel regulator valve be connected with oil burning installation, centrifugal compressor, Diffuser, firing chamber, concentric shafts, turbine, main duct rectification spout, the starting electrical machinery be connected with main duct casing, the power supply means be connected with starting electrical machinery, control system, be arranged on the projection inside by-pass air duct casing.
Arrange one end of punching press suction cone with by-pass air duct casing for front end, the one end arranging main duct casing in by-pass air duct casing is rear end.The air outlet hole that the rear portion of punching press suction cone is provided with cavity, is connected with cavity, air-intake guide vane is hollow structure, punching press suction cone is connected with by-pass air duct casing by air-intake guide vane, liquid oxygen modulating valve, liquid nitrogen modulating valve are connected with the hollow structure in air-intake guide vane respectively, and punching press suction cone and by-pass air duct casing form the first gas-entered passageway.
Straightener(stator) blade is hollow structure, main duct casing is connected with by-pass air duct casing by straightener(stator) blade, fuel regulator valve is connected with firing chamber by straightener(stator) blade, Diffuser, firing chamber is successively set in main duct casing, centrifugal compressor is connected with firing chamber through Diffuser, concentric shafts is through firing chamber, the outlet of firing chamber is provided with stator blade, stator blade is between firing chamber and turbine, main duct rectification spout is arranged on turbine rear end, centrifugal compressor, turbine is connected with concentric shafts respectively, starting electrical machinery is connected with concentric shafts and starting electrical machinery can drive concentric shafts to rotate.
Protruding between air outlet hole and centrifugal compressor, control system is connected with liquid oxygen modulating valve, liquid nitrogen modulating valve, fuel regulator valve respectively.In the present invention, realize heat exchange effect by projection, the nitrogen that namely can flow out with air outlet hole through the gas of punching press runner, oxygen collide, and realize exchange heat.Further, protruding triangular in shape along the sectional view of by-pass air duct casing radial direction.
Further, set-up of control system is in main duct casing one end near punching press suction cone, also comprise the liquid nitrogen device (i.e. liquid oxygen storage tank) be connected with liquid oxygen modulating valve, the liquid nitrogen plan (i.e. nitrogen storage tank) be connected with liquid nitrogen modulating valve, also comprise the oil burning installation be connected with fuel regulator valve, power supply means is power line.
When the present invention works, by-pass air duct casing front end airflow, punching press suction cone and by-pass air duct casing form punching press runner jointly.The front end of punching press suction cone forms centrum shock wave, forms normal shock wave between its rear end and by-pass air duct casing.Liquid oxygen, liquid nitrogen are entered in cavity respectively by liquid oxygen modulating valve, liquid nitrogen modulating valve, and are flowed out by air outlet hole.Through low temperature nitrogen, cryogenic oxygen that pore flows out, mix under the effect of protruding (convex role is mainly heat exchange, and namely protruding is heat exchanger) with the gas entered through by-pass air duct casing front end, realize heat exchange.In the middle part of by-pass air duct casing, main duct casing is set by straightener(stator) blade, thus coordinates with by-pass air duct casing and form little bypass ratio structure.The present invention arranges starting electrical machinery in the front end of main duct casing, starting electrical machinery connects concentric shafts, the front end of concentric shafts arranges centrifugal compressor, the rear end of concentric shafts arranges turbine, Diffuser is arranged in main duct casing, between Diffuser and turbine, be furnished with firing chamber and stator blade, combustion gas is sprayed by rectification spout after turbine.In the present invention, air inlet pressure compression process has been coordinated by punching press air inlet centrum and centrifugal compressor, and control system, by regulating the supply of each modulating valve, realizes complete machine stable operation.Meanwhile, by air-intake guide vane and straightener(stator) blade with the use of, complete entry spin and the rectification of by-pass air duct air-flow.
In the present invention, punching press form and centrifugal compressed form are combined to form supercharging section, and compression efficiency is higher; Possess starting electrical machinery, can realize starting without initial velocity; Complete machine operational speed range is wide, can adapt to low speed to supersonic range of operation; Control methods use injecting gas and fuel oil combine regulation, and mode is more flexible, and the effect reached is more stable; Add pre-cooled process, internal efficiency is improved, make complete machine resist high temperature material requirement in addition and reduce; The modular construction adopted is simple, and manufacturing cost is low.
In sum, owing to have employed technique scheme, the invention has the beneficial effects as follows:
1), in the present invention, adopt ram-compressed to coordinate first-stage centrifugal compression, efficiency is higher, wherein, ram-compressed produces according to air velocity, does not need additional driving force, centrifugal compressed single-stage pressure ratio is higher, and thus whole compression process only needs to apply to drive to centrifugal compressed, the little energy consumed;
2) in the present invention, adding of pre-cooled process, complete machine running temperature is reduced, and inlet end compression efficiency is higher, and also make complete machine reduce for the requirement of cooling system, high temperature resistance material requirements reduces too;
3) the present invention is when low speed, air inlet coordinates firing chamber and turbine to realize with work by combustion work by the centrifugal compressor of one-level, and through transonic speed stage, punching press effect is progressively remarkable, solve the situation of the unit centrifugal compressor pressure ratio deficiency when high speed operation, and speed-adaptive is wider;
4) the present invention is injected by the cavity of front end punching press suction cone and pore, external liquid nitrogen liquid oxygen, aeration ratio can be regulated at any time, when external feed stream condition changes greatly or is unstable, according to circumstances can adjust liquid oxygen liquid nitrogen to inject, and during the injection of liquid oxygen liquid nitrogen, most of heat can be absorbed by heat exchanger, make compression effectiveness better, combine regulation mode is flexible simultaneously, good stability;
5) rotor-support-foundation system of the present invention is single stage rotor, compression process is that punching press coordinates centrifugal compressor, structure is more simple relative to multistage compressor, combustion gas behind firing chamber is through one-level stator blade and turbine, outer flow passage is coordinated jointly to produce thrust, make rotor-support-foundation system more simple, manufacturability is good, and thus the present invention has structure advantage simple, with low cost.
Accompanying drawing explanation
Examples of the present invention will be described by way of reference to the accompanying drawings, wherein:
Fig. 1 is the cross-sectional view of compound aeroengine of the present invention.
In figure: 1 is punching press suction cone, and 2 is by-pass air duct casing, and 3 is air-intake guide vane, and 4 is liquid oxygen modulating valve, 5 is liquid nitrogen modulating valve, and 6 is main duct casing, and 7 is straightener(stator) blade, and 8 is fuel regulator valve, 9 is centrifugal compressor, and 10 is Diffuser, and 11 is firing chamber, 12 is concentric shafts, and 13 is turbine, and 14 is main duct rectification spout, 15 is starting electrical machinery, and 16 is power supply means, and 17 is protruding, 18 is cavity, and 19 is air outlet hole, and 20 is stator blade.
Embodiment
All features disclosed in this specification, or the step in disclosed all methods or process, except mutually exclusive feature and/or step, all can combine by any way.
Arbitrary feature disclosed in this specification, unless specifically stated otherwise, all can be replaced by other equivalences or the alternative features with similar object.That is, unless specifically stated otherwise, each feature is an example in a series of equivalence or similar characteristics.
Embodiment 1
Punching press-turbojet compound the aeroengine of the present embodiment comprises punching press suction cone, by-pass air duct casing, air-intake guide vane, for the liquid oxygen modulating valve be connected with liquid nitrogen device, for the liquid nitrogen modulating valve be connected with liquid nitrogen plan, be arranged on the main duct casing inside by-pass air duct casing, straightener(stator) blade, for the fuel regulator valve be connected with oil burning installation, centrifugal compressor, Diffuser, firing chamber, concentric shafts, turbine, main duct rectification spout, the starting electrical machinery be connected with main duct casing, the power supply means be connected with starting electrical machinery, control system, be arranged on the projection inside by-pass air duct casing.
In the front end of by-pass air duct casing, the air outlet hole that the rear portion of punching press suction cone is provided with cavity, is connected with cavity, air-intake guide vane is hollow structure, punching press suction cone is connected with by-pass air duct casing by air-intake guide vane, liquid oxygen modulating valve, liquid nitrogen modulating valve are connected with the hollow structure in air-intake guide vane respectively, and punching press suction cone and by-pass air duct casing form punching press runner.
Straightener(stator) blade is hollow structure, main duct casing is connected with by-pass air duct casing by straightener(stator) blade, fuel regulator valve is connected with firing chamber by straightener(stator) blade, Diffuser, firing chamber is successively set in main duct casing, centrifugal compressor is connected with firing chamber through Diffuser, concentric shafts is through firing chamber, the outlet of firing chamber is provided with stator blade, stator blade is between firing chamber and turbine, main duct rectification spout is arranged on turbine rear end, centrifugal compressor, turbine is connected with concentric shafts respectively, starting electrical machinery is connected with concentric shafts and starting electrical machinery can drive concentric shafts to rotate.
Protruding between air outlet hole and centrifugal compressor, control system is connected with liquid oxygen modulating valve, liquid nitrogen modulating valve, fuel regulator valve respectively.
In the present embodiment, set-up of control system is in main duct casing one end near punching press suction cone, and power supply means adopts power line.Liquid oxygen modulating valve is connected with liquid oxygen storage tank, and liquid nitrogen modulating valve is connected with liquid nitrogen storage tank, and fuel regulator valve is connected with fuel reservoir.
The working procedure of aeroengine of the present invention is mainly divided into subsonic speed and across, supersonic speed stage.
When subsonic speed, air velocity is lower, punching press suction cone coordinates with by-pass air duct casing can not form punching press effect, now air inlet mainly relies on centrifugal compressor to carry out supercharging and air inlet, inject two kinds of gases by liquid oxygen modulating valve and liquid nitrogen modulating valve simultaneously simultaneously, after heat exchanger (namely protruding), as precooling before air inlet, and regulate Charge-Air Oxygen ratio.The pre-cold energy of air inlet effectively improves pressure ratio and the efficiency of centrifugal compressor, and oxygen proportion regulates to adapt to combustion chambers burn, and control system combines the input ratio reconciling each modulating valve according to complete machine runnability.Subsonic speed air is after by-pass air duct casing flows into, through air-intake guide vane, certain inlet velocity angle is obtained after guiding, thus can fully mix at heat exchanger with the low temperature nitrogen flowed out from air outlet hole, oxygen, complete the gas after combination cooling and enter centrifugal compressor, complete compression process through Diffuser.
Another part gas, via the runner between main duct casing and by-pass air duct casing, sprays from afterbody as complete machine cooling and rectification.After compression, gas is through firing chamber and oil inflame, and high-speed fuel gas promotes turbine acting through stator blade, eventually passes the ejection of main duct rectification spout, coordinates with outer cool stream, obtain thrust.
Across in the working procedure in, supersonic speed stage, the difference maximum from the subsonic speed stage is: compress mode different.Across, supersonic speed stage, along with the raising of speed, punching press suction cone coordinates with by-pass air duct casing and forms punching press and to calm the anger effect, and the high pressure-temperature air after punching press is after air-intake guide vane, the air obtained has the characteristic of High Temperature High Pressure, namely obtains high temperature and high pressure gas.Now, tune up the ratio passing into liquid nitrogen, reduce the temperature of high temperature and high pressure gas, retain its high pressure characteristics, make the gas entering centrifugal compressor still can keep high efficiency compression effectiveness.Under this state, compression process forms the first order by punching press suction cone and the cooperation of by-pass air duct casing and compresses, and centrifugal compressor is second level compression, jointly completes compression process.Liquid oxygen modulating valve and liquid nitrogen modulating valve regulate oxygen proportion in real time according to generator operating conditions, and suitably cooling is pre-cooled, after completing mixing, enters centrifugal compressor, completes compression process through Diffuser.Another part gas, via the runner between main duct casing and by-pass air duct casing, sprays from afterbody after straightener(stator) blade rectification.After compression, gas is through firing chamber and oil inflame, and high-speed fuel gas promotes turbine (12) acting through stator blade, eventually passes the ejection of main duct rectification spout, coordinates with outer runner, obtain thrust.
Above by reference to the accompanying drawings to invention has been exemplary description; but the present invention is not limited to aforesaid way; as long as adopt method of the present invention is conceived and technological scheme is carried out the improvement of various unsubstantialities or directly apply to other occasions, all drop in protection scope of the present invention.The present invention is not limited to aforesaid embodiment.The present invention expands to any new feature of disclosing in this manual or any combination newly, and the step of the arbitrary new method disclosed or process or any combination newly.
Claims (7)
1. punching press-turbojet compound aeroengine, it is characterized in that, comprise punching press suction cone, by-pass air duct casing, air-intake guide vane, for the liquid oxygen modulating valve be connected with liquid nitrogen device, for the liquid nitrogen modulating valve be connected with liquid nitrogen plan, be arranged on the main duct casing inside by-pass air duct casing, straightener(stator) blade, for the fuel regulator valve be connected with oil burning installation, centrifugal compressor, Diffuser, firing chamber, concentric shafts, turbine, main duct rectification spout, the starting electrical machinery be connected with main duct casing, the power supply means be connected with starting electrical machinery, control system, be arranged on the projection inside by-pass air duct casing,
The air outlet hole that the rear portion of described punching press suction cone is provided with cavity, is connected with cavity, described air-intake guide vane is hollow structure, described punching press suction cone is connected with by-pass air duct casing by air-intake guide vane, described liquid oxygen modulating valve, liquid nitrogen modulating valve are connected with the hollow structure in air-intake guide vane respectively, and described punching press suction cone and by-pass air duct casing form punching press runner;
Described straightener(stator) blade is hollow structure, described main duct casing is connected with by-pass air duct casing by straightener(stator) blade, described fuel regulator valve is connected with firing chamber by straightener(stator) blade, described Diffuser, firing chamber is successively set in main duct casing, described centrifugal compressor is connected with firing chamber through Diffuser, described concentric shafts is through firing chamber, the outlet of described firing chamber is provided with stator blade, described stator blade is between firing chamber and turbine, described main duct rectification spout is arranged on turbine rear end, described centrifugal compressor, turbine is connected with concentric shafts respectively, described starting electrical machinery is connected with concentric shafts and starting electrical machinery can drive concentric shafts to rotate,
Described projection is between air outlet hole and centrifugal compressor, and described control system is connected with liquid oxygen modulating valve, liquid nitrogen modulating valve, fuel regulator valve respectively.
2. punching press according to claim 1-turbojet compound aeroengine, is characterized in that, the nitrogen that the gas through punching press runner can flow out with air outlet hole, oxygen collide, and realize exchange heat.
3. punching press according to claim 1 or 2-turbojet compound aeroengine, it is characterized in that, described projection is triangular in shape along the sectional view of by-pass air duct casing radial direction.
4. punching press according to claim 1 or 2 or 3-turbojet compound aeroengine, is characterized in that, described set-up of control system is in main duct casing one end near punching press suction cone.
5. punching press according to any one of claim 1 ~ 4-turbojet compound aeroengine, is characterized in that, also comprises the liquid nitrogen device be connected with liquid oxygen modulating valve, the liquid nitrogen plan be connected with liquid nitrogen modulating valve.
6. punching press according to any one of claim 1 ~ 5-turbojet compound aeroengine, is characterized in that, also comprise the oil burning installation be connected with fuel regulator valve.
7. punching press according to any one of claim 1 ~ 6-turbojet compound aeroengine, is characterized in that, described power supply means is power line.
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| CN201510747821.6A CN105221295B (en) | 2015-11-06 | 2015-11-06 | Stamping-turbine air injection composite aero-engine |
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| CN201510747821.6A CN105221295B (en) | 2015-11-06 | 2015-11-06 | Stamping-turbine air injection composite aero-engine |
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| CN105736178A (en) * | 2016-04-11 | 2016-07-06 | 清华大学 | Combined cycle engine |
| CN106224126A (en) * | 2016-08-29 | 2016-12-14 | 曾令霞 | Intermediate layer and the jet engine of following height |
| 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 |
| CN106762221A (en) * | 2017-01-13 | 2017-05-31 | 厦门大学 | Turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method |
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| CN105736178A (en) * | 2016-04-11 | 2016-07-06 | 清华大学 | Combined cycle engine |
| CN106224126A (en) * | 2016-08-29 | 2016-12-14 | 曾令霞 | Intermediate layer and the jet engine of following height |
| 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 |
| CN106762221A (en) * | 2017-01-13 | 2017-05-31 | 厦门大学 | Turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method |
| CN106762221B (en) * | 2017-01-13 | 2018-10-26 | 厦门大学 | Turbo ramjet engine ram-air turbine heat to electricity conversion and forecooling method |
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