CN101649781A - Jet engine - Google Patents
Jet engine Download PDFInfo
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- CN101649781A CN101649781A CN200810150584A CN200810150584A CN101649781A CN 101649781 A CN101649781 A CN 101649781A CN 200810150584 A CN200810150584 A CN 200810150584A CN 200810150584 A CN200810150584 A CN 200810150584A CN 101649781 A CN101649781 A CN 101649781A
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- gas compressor
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Abstract
The invention provides a jet engine, which is mainly characterized by consisting of an air inlet (1), a gas compressor (2), a combustion chamber (3), a tail nozzle (5) and an independent power plant (7), wherein a power output shaft (8) of the independent power plant (7) is connected with the compressor (2) and drives the gas compressor (2) to rotate to work. By adopting the independent power plant capable of independently changing the output power to replace a turbine in the prior art, the jet engine effectively reduces the pressure ratio of the gas compressor under the condition of same thrust, and avoids the problem of poor aerodynamic stability caused by the matched work of the gas compressor and the turbine; and the engine can better work under different loads, thereby simplifying a structure of the engine, avoiding the surge phenomenon of the gas compressor, and increasing the work scope and the reliability.
Description
(1) technical field:
The present invention relates to the aeroengine field, especially jet engine.
(2) background technique:
The jet engine of the jet generation thrust of continous way that aviation aircraft adopts mainly is a turbojet engine, and turbofan engine and turbojet engine are similarly, all is to produce thrust by the high speed exhaust, but structure is complicated more.Turbojet engine has the advantages that size is little, in light weight, thrust is big, and still, the exhaust velocity of its jet pipe outlet is higher, and when aircraft during in low-speed operations, the propulsive efficiency of motor is lower, and oil consumption rate is higher.The exhaust velocity of turbofan engine is less than turbojet engine, and the propulsive efficiency during low-speed operations is higher than the turbojet motor, but when high-speed flight, propulsive efficiency will descend.
The turbojet engine of prior art is made up of intake duct (1), gas compressor (2), firing chamber (3), turbine (4) and jet pipe critical pieces such as (5), wherein gas compressor (2) and turbine (4) link together by axle (6), gas compressor (2) relies on turbine (4) driving to carry out rotating with speed, and gas compressor (2) adopts axial flow or radial flow type structural type.The basic functional principle of motor is: air flows into from intake duct (1), carry out the oil jetting combustion heating through entering firing chamber (3) after gas compressor (2) compression, the high temperature that flows out, the combustion gas of high pressure are at first carried out expansion working to drive gas compressor (2) rotation in turbine (4), the corresponding reduction with temperature of gaseous-pressure of flowing out, continuing in jet pipe (5) then expands quickens also to discharge at a high speed to produce jet thrust.
Because turbine drives gaseous-pressure and temperature that gas compressor rotates needs consumption more, in order to produce enough exhaust velocities to obtain the thrust that motor requires in the jet pipe outlet, the pressure ratio of gas compressor and the fuel gas temperature of combustor exit are all had relatively high expectations.High pressure ratio needs more gas compressor progression to be achieved, the coupling shaft lengthening that can cause gas compressor and turbine, high fuel gas temperature then needs high performance exotic material, makes complex structure, technical difficulty height, processing cost increase, structure and the strength reliability of motor reduce.In addition, because the output power of turbine is subjected to the flow of gas compressor, factors such as the rotating speed restriction of supercharging combustor exit temperature, rotating shaft when, there is the problem of gas compressor and turbine work coupling.Pressure ratio height, progression cause the aerodynamic stability of gas compressor low speed state to reduce more, unstable working state such as rotating stall and surge occur.In order to alleviate the stability problem of work under the gas compressor slow-speed of revolution, turbojet engine often needs to adopt measures such as the venting of multistage compressor intergrade, many rotors (double rotor or triple-spool), inlet guide vane and stator blade be adjustable to prevent compressor surge, makes the structure of motor and control system complicated more.
(3) summary of the invention:
For overcoming the deficiency that prior art exists, the present invention proposes a kind of novel jet motor.
Similar with prior art, jet engine of the present invention still comprises intake duct (1), gas compressor (2), firing chamber (3) and jet pipe critical pieces such as (5) composition, and these parts still adopt prior art, and install successively along gas flow direction.The main distinction of the present invention and prior art is: replace turbine part of the prior art with an independent power device (7), the working state of these power plant (7) directly is not limited by gas compressor (2) outlet air pressure, flow and firing chamber (3) outlet fuel gas temperature, its output power can independent regulation, be connected with gas compressor (2) by pto (8), be used to drive gas compressor (2) rotation.Independent power device (7) can adopt stroke piston combustion engine of the prior art (petrol engine and diesel engine), rotary polygonal piston engine, motor or gas turbine etc.Basic functional principle of the present invention is: air flows into from intake duct (1), independent power device (7) drives gas compressor (2) rotation, the air that flows into gas compressor (2) is compressed supercharging, high-pressure air flows into firing chamber (3) and carries out the oil jetting combustion heating, and the high temperature of outflow, high-pressure gas directly expand to quicken and discharge at a high speed at jet pipe (5) and produce jet thrust.In motor, independent power device (7) is positioned at import one side of gas compressor (2), and outlet one side that also can be arranged in gas compressor (2) is to shorten the axial length of motor.
Compared with prior art, the present invention has the following advantages:
(1) because the gas after the gas compressor compression is directly discharged generation thrust from jet pipe after heating through the firing chamber, therefore, gas compressor can adopt lower pressure ratio and less progression, and the rotating component that does not have high speed rotating under the hot environment, requirement to exotic material reduces greatly, and the independent power device adopts existing mature technology, and the design difficulty of motor, manufacture cost are significantly reduced, and structural reliability increases.
(2) the independent power device working state that drives gas compressor directly is not limited by the variation of aerodynamic parameters such as the flow of gas compressor and pressure ratio, and the pressure ratio of gas compressor is low, progression is few, under the dual regulation of power plant output power and firing chamber fuel injection quantity, can guarantee that under the less situation of gas compressor working state off-design state motor works reliably in off-design behaviour, operating range is widened, and can realize not having the work of surge ground.
(3) during engine start, directly start the independent power device and forward the gas compressor band to design speed, firing chamber ignition then, motor just can normally produce thrust, makes start-up course simple, convenient.Because in the start-up course of gas compressor, do not light a fire in the firing chamber, flow can realize that with bigger than normal gas compressor does not have the work of surge ground in the start-up course during gas compressor work, need not extra anti-asthma and controlling mechanism, and engine structure is simplified, and weight reduces.
(4) high temperature of combustor exit, pressurized gas directly produce thrust through the jet pipe ejection, even the firing chamber is in flameout state, the jet pipe outlet still has certain exhaust velocity, then just can directly control the jet velocity of jet pipe outlet, make aircraft under different flying speeds, all have higher propulsive efficiency by the fuel injection quantity of regulating the firing chamber.
(4) description of drawings:
Fig. 1 is the turbojet engine schematic representation that has axial flow compressor in the prior art.
Fig. 2 is the turbojet engine schematic representation that has the footpath flow air compressor in the prior art.
Fig. 3 be among the present invention the independent power device at the schematic representation of axial flow compressor airflow inlet one side.
Fig. 4 be among the present invention the independent power device at the schematic representation of axial flow compressor flow outlet one side.
Fig. 5 be among the present invention the independent power device at the schematic representation of footpath flow air compressor airflow inlet one side.
Fig. 6 be among the present invention the independent power device at the schematic representation of footpath flow air compressor flow outlet one side.
In the accompanying drawing: the 4-turbine 5-jet pipe of 1-intake duct 2-gas compressor 3-firing chamber
6-gas compressor and turbine coupling shaft 7-independent power device
8-independent power device pto
(5) embodiment:
Embodiment one
The jet engine of present embodiment is made up of intake duct (1), gas compressor (2), firing chamber (3), jet pipe (5) and independent power device (7), independent power device (7) is a gas turbine installation, be installed in import one side of gas compressor (2), and its pto (8) linked to each other with gas compressor (2), gas compressor (2) adopts axial-flow compressor.
Embodiment two
The jet engine of present embodiment is made up of intake duct (1), gas compressor (2), firing chamber (3), jet pipe (5) and independent power device (7), independent power device (7) is a rotary polygonal piston engine, be installed in outlet one side of gas compressor (2), and its pto (8) linked to each other with gas compressor (2), gas compressor (2) adopts axial-flow compressor.
Embodiment three
The jet engine of present embodiment is made up of intake duct (1), gas compressor (2), firing chamber (3), jet pipe (5) and independent power device (7), independent power device (7) is a conventional engine, be installed in import one side of gas compressor (2), and its pto (8) linked to each other with gas compressor (2), gas compressor (2) adopts radial-flow compressor.
Embodiment four
The jet engine of present embodiment is made up of intake duct (1), gas compressor (2), firing chamber (3), jet pipe (5) and independent power device (7), independent power device (7) is a motor, be installed in outlet one side of gas compressor (2), and its pto (8) linked to each other with gas compressor (2), gas compressor (2) adopts radial-flow compressor.
Claims (4)
1. jet engine, be characterised in that its critical piece comprises intake duct (1), gas compressor (2), firing chamber (3), jet pipe (5) and independent power device (7), wherein intake duct (1), gas compressor (2), firing chamber (3), jet pipe (5) are installed successively along gas flow direction.Independent power device (7) directly is not limited by the working state of gas compressor (2) and firing chamber (3), can independently change output power.The power output shaft (8) of independent power device (7) links to each other with gas compressor (2), and drives gas compressor (2) rotary work.
2. jet engine according to claim 1, independent power device (7) adopts stroke piston combustion engine (petrol engine and diesel engine), rotary polygonal piston engine, motor or gas turbine.
3. jet engine according to claim 2, independent power device (7) are installed in airflow inlet one side of gas compressor (2).
4. jet engine according to claim 2, independent power device (7) are installed in flow outlet one side of gas compressor (2).
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810150584A CN101649781A (en) | 2008-08-11 | 2008-08-11 | Jet engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200810150584A CN101649781A (en) | 2008-08-11 | 2008-08-11 | Jet engine |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN101649781A true CN101649781A (en) | 2010-02-17 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200810150584A Pending CN101649781A (en) | 2008-08-11 | 2008-08-11 | Jet engine |
Country Status (1)
| Country | Link |
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| CN (1) | CN101649781A (en) |
Cited By (17)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102146858A (en) * | 2010-08-12 | 2011-08-10 | 靳北彪 | Stamping engine for pneumatic turbine |
| WO2011160441A1 (en) * | 2010-06-21 | 2011-12-29 | Jin Beibiao | Thermal ramjet |
| CN102452401A (en) * | 2010-11-01 | 2012-05-16 | 吴德滨 | Ultrahigh-speed train with electromagnetic-induction turbine engine |
| CN103867336A (en) * | 2014-04-07 | 2014-06-18 | 邱世军 | Jet propulsion and power output integrated system |
| CN105240159A (en) * | 2015-10-30 | 2016-01-13 | 常胜 | Jet engine |
| CN105888878A (en) * | 2016-04-18 | 2016-08-24 | 夏建国 | Turbineless jet engines |
| CN106121861A (en) * | 2016-06-21 | 2016-11-16 | 王启振 | Jet engine without efficient turbine |
| CN106224126A (en) * | 2016-08-29 | 2016-12-14 | 曾令霞 | Intermediate layer and the jet engine of following height |
| CN106555705A (en) * | 2015-09-25 | 2017-04-05 | 袁晓冬 | Topping turbine jet engine |
| CN107701312A (en) * | 2017-11-10 | 2018-02-16 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of hypersonic jets |
| CN107701313A (en) * | 2017-11-10 | 2018-02-16 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of electric mixed aviation engine of oil |
| CN107696812A (en) * | 2017-10-10 | 2018-02-16 | 中国人民解放军国防科技大学 | Oil-electricity hybrid power system and vertical take-off and landing hovercar with same |
| CN107842442A (en) * | 2017-11-10 | 2018-03-27 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of aero-engine |
| CN108167089A (en) * | 2017-09-08 | 2018-06-15 | 邹国泉 | Supersonic speed internal combustion aero-engine |
| CN111237084A (en) * | 2020-02-17 | 2020-06-05 | 王镇辉 | Electric-driven jet aircraft engine and aircraft |
| CN114790955A (en) * | 2022-05-06 | 2022-07-26 | 哈尔滨工业大学 | Hybrid power engine capable of realizing oil-electricity range extension |
| CN116697752A (en) * | 2023-07-03 | 2023-09-05 | 河南省远洋粉体科技股份有限公司 | Environment-friendly aluminum ingot smelting furnace |
-
2008
- 2008-08-11 CN CN200810150584A patent/CN101649781A/en active Pending
Cited By (22)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| WO2011160441A1 (en) * | 2010-06-21 | 2011-12-29 | Jin Beibiao | Thermal ramjet |
| WO2012019419A1 (en) * | 2010-08-12 | 2012-02-16 | Jin Beibiao | Wind-driven turbine ramjet engine |
| CN102146858A (en) * | 2010-08-12 | 2011-08-10 | 靳北彪 | Stamping engine for pneumatic turbine |
| CN102452401A (en) * | 2010-11-01 | 2012-05-16 | 吴德滨 | Ultrahigh-speed train with electromagnetic-induction turbine engine |
| CN103867336A (en) * | 2014-04-07 | 2014-06-18 | 邱世军 | Jet propulsion and power output integrated system |
| CN106555705A (en) * | 2015-09-25 | 2017-04-05 | 袁晓冬 | Topping turbine jet engine |
| CN105240159A (en) * | 2015-10-30 | 2016-01-13 | 常胜 | Jet engine |
| CN105240159B (en) * | 2015-10-30 | 2017-03-29 | 常胜 | A kind of jet engine |
| CN105888878A (en) * | 2016-04-18 | 2016-08-24 | 夏建国 | Turbineless jet engines |
| CN106121861A (en) * | 2016-06-21 | 2016-11-16 | 王启振 | Jet engine without efficient turbine |
| CN106224126A (en) * | 2016-08-29 | 2016-12-14 | 曾令霞 | Intermediate layer and the jet engine of following height |
| CN108167089A (en) * | 2017-09-08 | 2018-06-15 | 邹国泉 | Supersonic speed internal combustion aero-engine |
| CN107696812A (en) * | 2017-10-10 | 2018-02-16 | 中国人民解放军国防科技大学 | Oil-electricity hybrid power system and vertical take-off and landing hovercar with same |
| CN107696812B (en) * | 2017-10-10 | 2019-06-28 | 中国人民解放军国防科技大学 | Oil-electricity hybrid power system and vertical take-off and landing hovercar with same |
| CN107701313A (en) * | 2017-11-10 | 2018-02-16 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of electric mixed aviation engine of oil |
| CN107842442A (en) * | 2017-11-10 | 2018-03-27 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of aero-engine |
| CN107701312A (en) * | 2017-11-10 | 2018-02-16 | 中国空气动力研究与发展中心计算空气动力研究所 | A kind of hypersonic jets |
| CN111237084A (en) * | 2020-02-17 | 2020-06-05 | 王镇辉 | Electric-driven jet aircraft engine and aircraft |
| CN114790955A (en) * | 2022-05-06 | 2022-07-26 | 哈尔滨工业大学 | Hybrid power engine capable of realizing oil-electricity range extension |
| CN114790955B (en) * | 2022-05-06 | 2024-06-25 | 哈尔滨工业大学 | Hybrid power engine capable of realizing range increase of oil and electricity |
| CN116697752A (en) * | 2023-07-03 | 2023-09-05 | 河南省远洋粉体科技股份有限公司 | Environment-friendly aluminum ingot smelting furnace |
| CN116697752B (en) * | 2023-07-03 | 2024-03-12 | 河南省远洋粉体科技股份有限公司 | Environment-friendly aluminum ingot smelting furnace |
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Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| C02 | Deemed withdrawal of patent application after publication (patent law 2001) | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Open date: 20100217 |