CN103726953A - Turbofan engine with reverse ducts - Google Patents
Turbofan engine with reverse ducts Download PDFInfo
- Publication number
- CN103726953A CN103726953A CN201310735912.9A CN201310735912A CN103726953A CN 103726953 A CN103726953 A CN 103726953A CN 201310735912 A CN201310735912 A CN 201310735912A CN 103726953 A CN103726953 A CN 103726953A
- Authority
- CN
- China
- Prior art keywords
- duct
- outer duct
- pressure
- engine
- spindle
- Prior art date
- Legal status (The legal status is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the status listed.)
- Pending
Links
Images
Landscapes
- Structures Of Non-Positive Displacement Pumps (AREA)
Abstract
The invention relates to a turbofan engine with reverse ducts. The turbofan engine comprises a spindle, the inner duct and the outer duct. The spindle, the inner duct and the outer duct are coaxially arranged from the inside to the outside, the front end of the spindle is positioned at an air inlet of the engine and is connected with an air inlet fan, and the rear end of the spindle is connected with a high-pressure turbine; the rear end of the outer duct extends rearwards, and the inner-diameter side of the outer duct is contracted; a high-pressure air compressor is arranged in the front of the outer duct, the high-pressure turbine, the air inlet fan and the high-pressure air compressor rotate synchronously, the rear of the outer duct is positioned at the front of the high-pressure turbine, a combustion chamber is arranged at the rear of the outer duct and is connected with a spray pipe, and high-temperature and high-pressure airflow can be sprayed rearwards by the spray pipe; a turbofan set which is connected onto the spindle is arranged in the inner duct. The turbofan engine has the advantages that functions of the inner duct and the outer duct are swapped, airflow is heated by the outer duct, so that the temperature difference of the inside and the outside of airflow vortexes in a shell of the engine is enlarged, the rotational speed of the airflow vortexes is increased on the original basis by the aid of a Crocco theorem, and thrust of the engine can be increased; the outer duct is lengthened, so that the high-temperature airflow can be recycled, the temperature of sprayed air can be further reduced, infrared characteristics of the air can be decreased, and the safety of a military aircraft can be improved.
Description
Technical field
The present invention relates to engine art, be specifically related to a kind of anti-duct snail fan engine.
Background technique
At present, most aeroengines all adopt turbofan as power resources, the use aboard of snail fan engine is more universal, but there is some drawback in using in existing turbofan engine, first, because existing snail fan engine is heated air in main duct, the thrust that motor produces the place one's entire reliance upon compression strength of gas compressor and the gas flow temperature after heating, cannot realize the increase of thrust; Motor body is shorter in addition, and the heat producing in its working procedure temperature when discharging is still very high, and Btu utilization is insufficient, and infrared signature is obvious, if be used on military aircraft, is easy to be found by the other side.
Summary of the invention
The object of this invention is to provide a kind of anti-duct snail fan engine, it replaces the function of provided with internal duct and external duct, realize by-pass air duct heating air flow, and the air-flow vortex internal-external temperature difference in motor body is strengthened, utilize Crow section theorem on original basis, to make the faster rotational speed of air-flow vortex, strengthened the thrust of motor, and because by-pass air duct lengthens, high temperature gas flow can be secondary use, the gas temperature of ejection is further reduced, reduce its infrared signature, improve the Security of military aircraft.
The present invention is achieved by the following technical solutions: a kind of anti-duct snail fan engine, comprises coaxial main shaft, main duct and the by-pass air duct arranging from inside to outside; The suction port that the front end of described main shaft is positioned at motor connects supply fan, and the rear end of main shaft connects high-pressure turbine; Described by-pass air duct rear end extends backward and internal diameter shrinks; Described by-pass air duct front portion is provided with synchronizes the high-pressure compressor rotating with high-pressure turbine and supply fan, by-pass air duct rear portion is provided with firing chamber before being positioned at high-pressure turbine, and described firing chamber connects the jet pipe that sprays backward high-temperature high-pressure air flow; In described main duct, be provided with the turbofan group being connected on main shaft.
The outside of described main duct is provided with stator and rotor, and described supply fan is connected with rotor, and the flabellum of high-pressure compressor is connected with rotor.
The invention has the beneficial effects as follows: a kind of anti-duct snail fan engine, it replaces the function of provided with internal duct and external duct, realize by-pass air duct heating air flow, and the air-flow vortex internal-external temperature difference in motor body is strengthened, utilize Crow section theorem on original basis, to make the faster rotational speed of air-flow vortex, strengthened the thrust of motor, and because by-pass air duct lengthens, high temperature gas flow can be secondary use, the gas temperature of ejection is further reduced, reduce its infrared signature, improve the Security of military aircraft.
Accompanying drawing explanation
Below in conjunction with drawings and Examples, the invention will be further described.
Accompanying drawing 1 is a kind of structural representation of anti-duct snail fan engine.
In figure, 1. by-pass air duct, 2. main duct, 3. main shaft, 4. firing chamber, 5. supply fan, 6. high-pressure compressor, 7. turbofan group, 8. high-pressure turbine, 9. jet pipe.
Embodiment
In the accompanying drawings, a kind of anti-duct snail fan engine, comprises coaxial main shaft 3, main duct 2 and the by-pass air duct 1 arranging from inside to outside; The suction port that the front end of described main shaft 3 is positioned at motor connects supply fan 5, and the rear end of main shaft 3 connects high-pressure turbine 7; Described by-pass air duct 1 rear end extends backward and internal diameter shrinks; Described by-pass air duct 1 front portion is provided with synchronizes the high-pressure compressor 6 rotating with high-pressure turbine 8 and supply fan 5, by-pass air duct 1 rear portion is provided with firing chamber 4 before being positioned at high-pressure turbine 8, and described firing chamber 4 connects the jet pipe 9 that sprays backward high-temperature high-pressure air flow; In described main duct 2, be provided with the turbofan group 7 being connected on main shaft 3.
The outside of described main duct 2 is provided with stator and rotor, and described supply fan 5 is connected with rotor, and the flabellum of high-pressure compressor 6 is connected with rotor.
During engine operation, air is entered in main duct 2 and by-pass air duct 1 by supply fan 5, and the gas in by-pass air duct 1 enters firing chamber 4 after high-pressure compressor 6 compressions, produces high-temperature high-pressure air flow, high-temperature high-pressure air flow rotates high-pressure turbine 8, and by jet pipe 9, is entered in the prolongation pipeline of by-pass air duct 1; High-pressure turbine 8 drives supply fan 5, turbofan group 7 and high-pressure compressor 6 to rotate together when rotating; Gas in main duct 2 is because the rotation of turbofan group 7 forms air-flow vortex, and the high temperature and high pressure gas that the periphery of this air-flow vortex is sprayed by jet pipe 9 in the extension tube of by-pass air duct 1 heats, and makes air-flow vortex faster rotational speed, thereby has increased the thrust of motor; And because high temperature and high pressure gas is utilized again, its temperature is significantly reduced, reduced the infrared signature of motor.
Claims (2)
1. an anti-duct snail fan engine, comprises coaxial main shaft (3), main duct (2) and the by-pass air duct (1) arranging from inside to outside; It is characterized in that, the suction port that the front end of described main shaft (3) is positioned at motor connects supply fan (5), and the rear end of main shaft (3) connects high-pressure turbine (7); Described by-pass air duct (1) rear end extends backward and internal diameter shrinks; Described by-pass air duct (1) front portion is provided with synchronizes the high-pressure compressor (6) rotating with high-pressure turbine (8) and supply fan (5), by-pass air duct (1) rear portion is positioned at high-pressure turbine (8) and is provided with before firing chamber (4), and described firing chamber (4) connect the jet pipe (9) that sprays backward high-temperature high-pressure air flow; In described main duct (2), be provided with the turbofan group (7) being connected on main shaft (3).
2. a kind of anti-duct snail fan engine according to claim 1, is characterized in that, the outside of described main duct (2) is provided with stator and rotor, and described supply fan (5) is connected with rotor, and the flabellum of high-pressure compressor (6) is connected with rotor.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310735912.9A CN103726953A (en) | 2013-12-29 | 2013-12-29 | Turbofan engine with reverse ducts |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201310735912.9A CN103726953A (en) | 2013-12-29 | 2013-12-29 | Turbofan engine with reverse ducts |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN103726953A true CN103726953A (en) | 2014-04-16 |
Family
ID=50451201
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201310735912.9A Pending CN103726953A (en) | 2013-12-29 | 2013-12-29 | Turbofan engine with reverse ducts |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN103726953A (en) |
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104279076A (en) * | 2014-09-23 | 2015-01-14 | 张朝刚 | Double-rotor cyclone waste heat utilizing device |
| CN104279075A (en) * | 2014-09-23 | 2015-01-14 | 张朝刚 | Single-rotating type cyclone waste heat utilizing device |
| CN109178281A (en) * | 2018-08-10 | 2019-01-11 | 天津大学 | Propulsion device for miniature self-service ship |
| CN111636975A (en) * | 2020-06-08 | 2020-09-08 | 清华大学 | Two-duct turbine jet engine with bearing cooling function |
-
2013
- 2013-12-29 CN CN201310735912.9A patent/CN103726953A/en active Pending
Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN104279076A (en) * | 2014-09-23 | 2015-01-14 | 张朝刚 | Double-rotor cyclone waste heat utilizing device |
| CN104279075A (en) * | 2014-09-23 | 2015-01-14 | 张朝刚 | Single-rotating type cyclone waste heat utilizing device |
| CN104279075B (en) * | 2014-09-23 | 2016-02-03 | 张朝刚 | A kind of single rotating whirlwind residual heat using device |
| CN104279076B (en) * | 2014-09-23 | 2016-02-03 | 张朝刚 | A kind of double-rotation type whirlwind residual heat using device |
| CN109178281A (en) * | 2018-08-10 | 2019-01-11 | 天津大学 | Propulsion device for miniature self-service ship |
| CN111636975A (en) * | 2020-06-08 | 2020-09-08 | 清华大学 | Two-duct turbine jet engine with bearing cooling function |
| CN111636975B (en) * | 2020-06-08 | 2021-12-07 | 清华大学 | Two-duct turbine jet engine with bearing cooling function |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN104675556B (en) | The large Bypass Ratio Turbofan Engine of blade tip reaction driving fan | |
| CN202055935U (en) | Jet engine with parallel combustion chambers | |
| EP2966265B1 (en) | Turbofan gas turbine engine with cleaning system | |
| US8579584B2 (en) | Turbofan jet engine | |
| JP2013249836A5 (en) | ||
| CN107178396A (en) | Active clearance control method and equipment | |
| CN204041245U (en) | The nozzle pipe line structure that a kind of powder gas starts | |
| CN103726953A (en) | Turbofan engine with reverse ducts | |
| CN205823448U (en) | Radial-flow type simple cycle gas turbine engine | |
| CN204663701U (en) | A kind of exhaust mixer of turbofan engine | |
| CN101881237A (en) | Turbofan postpose type engine | |
| CN104879219A (en) | Turbine detonation engine | |
| CN108506111B (en) | Microminiature turbofan engine | |
| CN203730136U (en) | Turbopulse detonation engine | |
| CN103775244A (en) | Double-flow injection rotor engine | |
| CN201739027U (en) | Turbofan rear-mounted engine | |
| CN204783324U (en) | Fanjet with integration of aircraft structure | |
| CN208040567U (en) | A kind of boosting impacting fanjet | |
| CN203476508U (en) | Anti-icing screw-plug assembly structure | |
| CN109869241B (en) | Hypergravity gas engine device and method | |
| CN104131915A (en) | Ramjet started in static state | |
| CN204060937U (en) | A kind of aeroengine | |
| CN201818391U (en) | Duct-suited turbojet engine | |
| CN205078365U (en) | Jet engine | |
| CN105089784A (en) | Energy-efficient turbine fan |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| C06 | Publication | ||
| PB01 | Publication | ||
| WD01 | Invention patent application deemed withdrawn after publication |
Application publication date: 20140416 |
|
| WD01 | Invention patent application deemed withdrawn after publication |