CN103437914B - A kind of change circulating air turborocket combined engine - Google Patents
A kind of change circulating air turborocket combined engine Download PDFInfo
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- CN103437914B CN103437914B CN201310374377.9A CN201310374377A CN103437914B CN 103437914 B CN103437914 B CN 103437914B CN 201310374377 A CN201310374377 A CN 201310374377A CN 103437914 B CN103437914 B CN 103437914B
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Abstract
The present invention's one becomes circulating air turborocket combined engine, comprises gas compressor, axle, main combustion chamber, air duct, turbine, tail pipe burner and jet pipe; Gas compressor is positioned at main combustion chamber air inlet side, and turbine is positioned at main combustion chamber air outlet side, and gas compressor is connected by axle with turbine; Air duct is positioned at outside main combustion chamber, is communicated with gas compressor and tail pipe burner; Tail pipe burner is positioned at turbine exhaust side, and jet pipe is communicated with tail pipe burner; Combined engine also comprises gas generator and the second turbine, and gas generator second turbine between air duct and main combustion chamber is positioned at the blade tip place of turbine and is connected with gas compressor by axle; Gas generator outlet is just to the second turbine.The present invention for aviation aircraft provides one can economical cruise for a long time, again can with the power system solution of higher comprehensive performance high-speed maneuver in the short time, and existing aero-turbine can be solved cannot self-running problem.
Description
Technical field
The present invention relates to and a kind of become circulating air turborocket combined engine, be specially adapted to that long-time low pressure economy is cruised, the aviation aircraft of short time high-speed maneuver.
Background technique
Aviation aircraft power in-service at present mainly comprises turbogenerator, pressed engine and rocket motor.These power respectively have pluses and minuses: turbogenerator fuel economy is high, and thrust weight ratio is low, and general work height is lower than 20km, and operating rate is no more than 2Ma; Pressed engine is suitable for high-altitude high speed operation, and fuel economy is good, but cannot zero-speed independently start and high-speed maneuver; Rocket motor can spatial domain, All Speed Range work entirely, but fuel economy is poor.These power of single use are all difficult to make aviation aircraft possess the ability of long-time economical cruise, short time high-speed maneuver simultaneously, govern the development of aerospace flight vehicle.
By the mode of combination, two or more power cycle is integrated, make power system be a kind of means expanding aviation aircraft operating range to become the mode work of circulation.It is turbine base combined cycle engine (TurbineBasedCombinedCycle, TBCC) combined that turbogenerator circulation and pressed engine circulated that current change circulation combined engine mainly contains two kinds: one.This power is at low speed segment with turbogenerator work pattern, and in high regime with pressed engine work pattern, operating range is wide, and fuel economy is good, but needs the high-speed turbine accelerator that development system is complicated, technical difficulty is large; Two is the rocket based combined cycle motors (RocketBasedCombinedCycle, RBCC) combined that rocket motor circulation and pressed engine circulated.This power is at low speed segment, high-speed maneuver or high-altitude (about more than 30km) with rocket motor work pattern, and at cruise section with pressed engine work pattern, operating range is wide, and thrust-mass ratio is large, but the fuel economy of rocket motor pattern is poor.
Summary of the invention
Technical problem to be solved by this invention is: for aviation aircraft provides one can economical cruise for a long time, again can with the power system solution of higher comprehensive performance high-speed maneuver in the short time, and existing aero-turbine can be solved cannot self-running problem.
Technical solution of the present invention is as follows:
A kind of change circulating air turborocket combined engine, its special way is:
Comprise turbogenerator, described turbogenerator comprises gas compressor 1, axle 9, main combustion chamber 3, air duct 4, turbine 6, tail pipe burner 7 and jet pipe 8;
Described gas compressor 1 is positioned at main combustion chamber air inlet side, and described turbine 6 is positioned at main combustion chamber 3 air outlet side, and described gas compressor 1 is connected by axle 9 with turbine 6; Described air duct 4 is positioned at outside main combustion chamber 3, is communicated with gas compressor 1 and tail pipe burner 7; Described tail pipe burner 7 is positioned at turbine 6 exhaust side, and described jet pipe 8 is communicated with tail pipe burner 7;
Described combined engine also comprises gas generator 2 and the second turbine, and described gas generator 2 is between air duct 4 and main combustion chamber 3, and described second turbine is positioned at the blade tip place of turbine 6 and is connected with gas compressor 1 by axle 9; Described gas generator 2 exports just to the second turbine.
Above-mentioned gas generator 2 carries propellant agent for medium with aviation aircraft, described in carry propellant agent be SP, bipropellant or tripropellant.
Above-mentioned second turbine is blade-tip turbine.
Above-mentioned gas generator 2 is ring generators.
The present invention compared with prior art has following features:
1, turbogenerator and turborocket combine by combined engine of the present invention cleverly, and with existing aero-turbine for basic structure, common components is many, change less to existing aero-turbine system, are easy to realize.Can with turbogenerator and turborocket two kinds of work patterns.
2, combined engine of the present invention is compared with air turbo rocket motor, and low speed segment is with turbogenerator work pattern, and fuel economy is high; Compared with aero-turbine, self-starting fast can be realized on ground, improve the capacity of will of aircraft, shorten the urgent time for lift off, improve the corresponding speed of aircraft; And this combined engine can work in two modes simultaneously, ensure that rotor is all the time with greatest physical rotary speed working, to produce maximum thrust, improve existing aero-turbine Thrust and to decay fast shortcoming, meet the needs of aviation aircraft high-speed maneuver.
3, when combined engine of the present invention occurs flame-out in flight with turbogenerator work pattern, restarting continuously, is repeatedly carried out by turborocket pattern.Even if start unsuccessfully, aircraft still turborocket pattern can carry out dynamic giving an encore or emergency landing.
4, combined engine of the present invention, blade-tip turbine has the high speed that rotates in a circumferential direction, and Gas-Generator Flow required under identical output power is little, and turborocket pattern has good fuel economy.
5, combined engine of the present invention, adopts ring gas generator, makes each part fits of combined engine compacter.
Accompanying drawing explanation
Fig. 1 is system schematic of the present invention;
Fig. 2 is the B-B view of Fig. 1;
Fig. 3 is turbogenerator mode of operation schematic diagram of the present invention;
Fig. 4 is that the present invention is with air turbo rocket engine working mode schematic diagram;
Wherein, reference character is: 1-gas compressor, 2-gas generator, 3-main combustion chamber, 4-air duct, 5-blade-tip turbine, 6-turbine, 7-tail pipe burner, 8-jet pipe, 9-axle.
Embodiment,
Below in conjunction with accompanying drawing, the present invention will be further described:
Fig. 1-2 is depicted as system schematic of the present invention, the present invention includes gas compressor 1, gas generator 2, main combustion chamber 3, air duct 4, blade-tip turbine 5, turbine 6, tail pipe burner 7, jet pipe 8, axle 9, gas generator 2, blade-tip turbine 5 are combined to form air turbo rocket motor with turbogenerator; Wherein, gas compressor 1 can be axial flow or centrifugal, and function sucks air and supercharging from atmosphere environment, provides pressurized air to air duct or main combustion chamber; Gas generator 2 is carry with aviation aircraft the firing unit that propellant agent is medium, carries propellant agent and can be SP, bipropellant or tripropellant; Wherein bipropellant is fuel and oxygenant.
The function of main combustion chamber 3 sprays into fuel, and realize the efficient mixed combustion with air; Air duct 4 is an annular pass, is communicated with gas compressor 1 and tail pipe burner 7; Turbine 6 is connected with gas compressor 1 by axle 9, with the products of combustion of main combustion chamber 3 for medium, drives gas compressor 1 to work; Blade-tip turbine 5 is installed on the blade tip position of turbine 6, and the high-temperature fuel gas produced with gas generator 2, for medium, drives gas compressor 1 to work; Tail pipe burner 7 can spray into fuel, and realizes the burning with high-temperature fuel gas or air, improves fuel gas temperature; Jet pipe 8 realizes combustion gas and accelerates, and expands and produces thrust; Axle 9 is for connecting gas compressor 1 and turbine 6.
As shown in Figure 3, when with turbogenerator work pattern, gas compressor 1 sucks air and supercharging from air.Air after supercharging is divided into two-way: a road enters main combustion chamber 3, burns with the fuel mix sprayed in firing chamber 3, and produce the oil-poor combustion gas of high temperature, the oil-poor gas driven turbine 6 of high temperature drives gas compressor 1 to work; Another road enters tail pipe burner 7 through air duct 4, burns with the oil-poor combustion gas of high temperature of doing work through turbine 6 and the fuel mix sprayed in tail pipe burner 7, produces high-temperature fuel gas.High-temperature fuel gas is discharged through jet pipe 8 accelerated expansion, makes motor generation thrust forward.In working procedure, can open as required or close spray into fuel in tail pipe burner.
As shown in Figure 4, when the present invention works with air turbo rocket engine working mode, gas generator 2 work produces high-temperature fuel gas and drives blade-tip turbine 5 to work, blade-tip turbine 5 drives gas compressor 1 to rotate by axle 9, air is sucked and supercharging from air, air after supercharging is divided into two-way: a road enters tail pipe burner 7 through air passageways 4, and another road enters firing chamber 3, with the kerosene sprayed into burn produce oil-poor gas driven turbine 6 after enter tail pipe burner 7.Through blade-tip turbine 5 do work high-temperature fuel gas, through turbine 6 do manual work oil-poor combustion gas and mix in tail pipe burner 7 through the pure air of air passageways 4, fuel combustion can be sprayed into improve fuel gas temperature if desired in tail pipe burner 7, products of combustion is discharged by jet pipe 8 accelerated expansion, makes motor generation thrust forward.
Claims (4)
1. become a circulating air turborocket combined engine, its feature is:
Comprise turbogenerator, described turbogenerator comprises gas compressor (1), axle (9), main combustion chamber (3), air duct (4), turbine (6), tail pipe burner (7) and jet pipe (8);
Described gas compressor (1) is positioned at main combustion chamber air inlet side, described turbine (6) is positioned at main combustion chamber (3) air outlet side, and described gas compressor (1) is connected by axle (9) with turbine (6); Described air duct (4) is positioned at main combustion chamber (3) outside, is communicated with gas compressor (1) and tail pipe burner (7); Described tail pipe burner (7) is positioned at turbine (6) exhaust side, and described jet pipe (8) is communicated with tail pipe burner (7);
Described change circulating air turborocket combined engine also comprises gas generator (2) and the second turbine, described gas generator (2) is positioned between air duct (4) and main combustion chamber (3), and described second turbine is positioned at the blade tip place of turbine (6) and is connected with gas compressor (1) by axle (9); Described gas generator (2) outlet is just to the second turbine.
2. change circulating air turborocket combined engine according to claim 1, it is characterized in that: described gas generator (2) carries propellant agent for medium with aviation aircraft, described in carry propellant agent be SP, bipropellant or tripropellant.
3. change circulating air turborocket combined engine according to claim 1 and 2, is characterized in that: described second turbine is blade-tip turbine.
4. change circulating air turborocket combined engine according to claim 3, is characterized in that: described gas generator (2) is ring generators.
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| Application Number | Priority Date | Filing Date | Title |
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| CN201310374377.9A CN103437914B (en) | 2013-08-23 | 2013-08-23 | A kind of change circulating air turborocket combined engine |
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| CN201310374377.9A CN103437914B (en) | 2013-08-23 | 2013-08-23 | A kind of change circulating air turborocket combined engine |
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| CN103437914A CN103437914A (en) | 2013-12-11 |
| CN103437914B true CN103437914B (en) | 2015-12-09 |
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Families Citing this family (12)
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| CN103758662B (en) * | 2014-02-12 | 2016-04-06 | 苟仲武 | A kind of rocket motor method and apparatus of liquid air mixed power |
| CN105841193B (en) * | 2016-05-18 | 2018-07-20 | 葛明龙 | Two kinds of aerospace fanjets |
| CN106050472A (en) * | 2016-07-08 | 2016-10-26 | 西北工业大学 | Turbo-rocket combined ramjet engine and operating method thereof |
| CN108049985B (en) * | 2018-01-29 | 2020-05-08 | 余四艳 | Rotary jet type variable circulation aviation jet engine |
| CN109826721A (en) * | 2019-04-03 | 2019-05-31 | 中南大学 | It is a kind of that the device and its engine of air and fuel-rich combustion gas are provided |
| CN110131074B (en) * | 2019-05-24 | 2020-06-30 | 西安航天动力研究所 | Bipropellant air turbine rocket propulsion system |
| CN110939529B (en) * | 2019-11-25 | 2020-11-06 | 西安航天动力研究所 | Integrated gas supply device |
| CN111042918B (en) * | 2019-12-31 | 2021-08-03 | 罗辉 | Variable cycle engine |
| CN111594315B (en) * | 2020-04-07 | 2021-03-05 | 浙江省涡轮机械与推进系统研究院 | Composite mechanism full-flow circulation supersonic propulsion system and working method thereof |
| CN112901344B (en) * | 2021-01-26 | 2022-04-01 | 厦门大学 | Interstage rotary detonation variable-circulation turboshaft engine |
| CN115653790A (en) * | 2022-10-15 | 2023-01-31 | 中国科学院力学研究所 | Dual-mode variable-cycle turbine rocket engine |
| CN115680940A (en) * | 2022-10-15 | 2023-02-03 | 中国科学院力学研究所 | Crown turbine variable-cycle turbine rocket engine and engine thrust implementation method |
Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2986003A (en) * | 1957-04-04 | 1961-05-30 | Napier & Son Ltd | Fuel supply systems for compound ramjet-turborocket engines |
| CN100417801C (en) * | 1999-03-10 | 2008-09-10 | 威廉国际有限责任公司 | Rocket engine |
-
2013
- 2013-08-23 CN CN201310374377.9A patent/CN103437914B/en active Active
Patent Citations (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| US2986003A (en) * | 1957-04-04 | 1961-05-30 | Napier & Son Ltd | Fuel supply systems for compound ramjet-turborocket engines |
| CN100417801C (en) * | 1999-03-10 | 2008-09-10 | 威廉国际有限责任公司 | Rocket engine |
Non-Patent Citations (2)
| Title |
|---|
| 涡轮增压固体冲压发动机热力循环分析;莫然，刘佩进，刘洋，杨飒;《固体火箭技术》;20111031;第34卷(第5期);第0598-0602页 * |
| 空气涡轮火箭发动机研究的进展及展望;南向谊，王拴虎，李平;《火箭推进》;20081231;第34卷(第6期);第0031-0034页 * |
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