CN101806259A - Inner culvert turbofan and ram-type double-mode engine - Google Patents
Inner culvert turbofan and ram-type double-mode engine Download PDFInfo
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- CN101806259A CN101806259A CN200910008924A CN200910008924A CN101806259A CN 101806259 A CN101806259 A CN 101806259A CN 200910008924 A CN200910008924 A CN 200910008924A CN 200910008924 A CN200910008924 A CN 200910008924A CN 101806259 A CN101806259 A CN 101806259A
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Abstract
The invention discloses a turbofan and a ram-type double-mode engine. In a propulsion working mode of the turbofan, an inner culvert turbofan engine is adopted, and then a fan blade and a main shaft form a certain angle to make the rotating fan blade propel the air backwards. When the external air velocity reaches high subsonic velocity or supersonic velocity, the inner culvert turbofan stops active rotation; the angle between the fan blade and the main shaft is adjusted to be small so as to reduce the windward sides of the inner culvert turbofan and the fan blade and adjust the airflow; the airflow enters a rear spray pipe through the inner culvert turbofan and the fan blade, and is mixed, burned and expanded with the fuel oil in the rear spray pipe to generate a backward thrust; and then the rear spray pipe is equivalent to the ram-type engine. By adjusting the angle between the fan blade and the main shaft, the engine has two different working modes and reaches an optimal working state under different speed conditions.
Description
Technical field
The present invention relates to a kind of can be at the double mode motor of work down of turbofan engine and ramjet propulsion, especially the series arrangement that is different from known turbofan and ramjet propulsion, its unique distinction is that it only can finish the conversion of two kinds of patterns by the flabellum of adjusting the main duct fan.
Background technique
At present, known turbojet/turbofan engine and the double mode motor of ramjet propulsion is with the series arrangement before turbojet/turbofan engine arrangement ramjet propulsion.When air speed was in subsonic speed, turbojet/turbofan engine work, Jet Stream were by rearmounted ramjet propulsion, and this moment, ramjet propulsion was not worked; When air speed reached high subsonic speed or supersonic speed, turbojet/turbofan engine quit work, and extraneous air-flow is walked around turbojet/turbofan engine to entering ramjet propulsion, and ramjet propulsion work produces thrust.When high subsonic speed or supersonic speed, air-flow need be walked around turbojet/turbofan engine, and turbojet/turbofan engine can produce resistance to the air-flow of process like this, and has influence on the work of ramjet propulsion; And existing axial-flow turbine jet/complex structure of turbofan engine, movable component are many, produce, operation and maintenance cost are higher.
Summary of the invention
The present invention be directed to prior art, especially (application number: " inner culvert turbofan engine " patent of 200910008823.8) having applied for is further improved at the inventor.
In order to solve the problem of existing turbojet/turbofan engine and the double mode motor of ramjet propulsion, at first be existing axial-flow turbine jet/complex structure of turbofan engine, the problem that movable component are many; And under the ramjet propulsion mode of operation, extraneous air-flow need be walked around axial-flow turbine jet/turbofan engine, and axial-flow turbine jet/turbofan engine can produce the problem of resistance and turbulent flow to air-flow.The invention provides more simple turbofan engine, reduced its amount of parts; Extraneous air-flow needn't be walked around turbofan engine under the ramjet propulsion mode of operation, has improved intake efficiency.
The present invention solves the scheme that its technical problem adopts: adopt inner culvert turbofan engine (application number: 200910008823.8), and further improve its main duct fan, make the electric fan of main duct fan can change angle with main shaft as required.Under the subsonic speed state, inner culvert turbofan engine work, the angular adjustment of electric fan and main shaft produces the angle of best back thrust to the main duct fan that makes rotation.Under high subsonic speed and supersonic speed state, inner culvert turbofan engine quits work, the flabellum of main duct fan is adjusted to and the approaching parallel angle of main shaft, the windward side of main duct fan is reduced, extraneous air-flow can waltz through the main duct fan and enter rear jet, and the main duct fan also plays a part rectification to air-flow simultaneously; In rear jet, air and fuel oil mixed combustion produce thrust, and the rear jet of this moment is equivalent to ramjet propulsion.
The invention has the beneficial effects as follows, by utilization inner culvert turbofan engine (application number: 200910008823.8), and on the basis of this invention, increase the function of the electric fan of adjusting the main duct fan, make its pattern work under subsonic speed with turbofan engine; Under high subsonic speed and ultrasonic condition,, make inner culvert turbofan and ram-type double-mode engine all reach optimum Working in the friction speed situation with the pattern work of ramjet propulsion.
Description of drawings
The present invention is further described below in conjunction with drawings and Examples.
Fig. 1 is a mechanical side schematic view of the present invention.
Fig. 2 is the mechanical front schematic view of turbofan mode of operation of the present invention.
Fig. 3 is the mechanical front schematic view of punching type mode of operation of the present invention.
Fig. 4 is the mechanical back schematic representation of turbofan mode of operation of the present invention.
Fig. 5 is the mechanical back schematic representation of punching type mode of operation of the present invention.
Fig. 6 is a main duct fan front schematic view under the turbofan mode of operation of the present invention.
Fig. 7 is a main duct fan side schematic view under the turbofan mode of operation of the present invention.
Fig. 8 is the leading flank schematic representation of turbofan mode of operation of the present invention.
Fig. 9 is the trailing flank schematic representation of turbofan mode of operation of the present invention.
Figure 10 is the main duct fan front schematic view under the punching type mode of operation of the present invention.
Figure 11 is the main duct fan side schematic view under the punching type mode of operation of the present invention.
Figure 12 is the leading flank schematic representation of punching type mode of operation of the present invention.
Figure 13 is the trailing flank schematic representation of punching type mode of operation of the present invention.
Figure 14 is the cross sectional representation of punching type mode of operation of the present invention.
Embodiment
In Fig. 1, Fig. 2, Fig. 3, Fig. 4 and Fig. 5,1. main shaft, 2. main duct fan, 3. electric fan, 4. centrifugal-flow compressor impeller, 5. turbine wheel, 6. preceding shell wall, 7. gas collecting tube, 8. gas collection conduit, 9. firing chamber, 10. nozzle, 11. nozzle air current passages, 12. rear jets, 13. the afterbunring oil delivering device, 14. back shell walls.
In Fig. 6 and Fig. 7, main shaft (1), main duct fan (2) and electric fan (3) are in turbofan promotion pattern, electric fan (3) is certain angle with main shaft (1), and the main duct fan (2) and the electric fan (3) that are beneficial to rotate advance ambient air backward.
In Fig. 8 and Fig. 9, main shaft (1), main duct fan (2), electric fan (3) centrifugal-flow compressor impeller (4) and turbine wheel (5) are what be fixed together; Electric fan (3) and main shaft (1) adjustable angle; When starting, external force drive main spindle (1) rotation, main shaft (1) drives main duct fan (2), electric fan (3), centrifugal-flow compressor impeller (4) and turbine wheel (5) and rotates simultaneously; Ambient air is divided into two partly, enters centrifugal-flow compressor impeller (4) and main duct fan (2) respectively; Electric fan (3) and main shaft (1) angular adjustment are to the most suitable angle that air is promoted backward; Enter the air of main duct fan (2), under pushing away of main duct fan (2) and electric fan (3) rotation used, air is moved backward; The air that enters centrifugal-flow compressor impeller (4) is under the high speed rotating of centrifugal-flow compressor impeller (4), centrifugal force makes air compression, pressurized air is transported to firing chamber (9) through gas collecting tube (7) and gas collection conduit (8), (9) internal combustion expands the back by nozzle (10) to pressurized air in the firing chamber, promote turbine wheel (5) rotation, nozzle air current passage (11) makes high-temperature combustion gas promote turbine wheel (5) rotation better, turbine wheel (5) drives centrifugal-flow compressor impeller (4) simultaneously, main duct fan (2) and electric fan (3) rotation; High-temperature gas contacts with the cryogenic gas of main duct fan (2) discharge after promoting turbine wheel (5) rotation, and two-part gas traffic direction becomes approximate an angle of 90 degrees to meet; And the Hand of spiral of high-temperature gas and cryogenic gas near or overlap, thereby produced Crow many (Crocco) theorem-tornado effect: high-temperature gas is in the periphery that main duct fan (2) is discharged the low temperature helical vortex that gas produced, produced one along the enthalpy gradient that refers in the radial direction, this temperature gradient is that the high-temperature gas and the main duct fan (2) of combustion gas discharged the poor of gas at normal temperature, surpasses 1000 degree; Like this in rear jet (12), high-temperature gas makes the spin intensity of the rotation gas that main duct fan (2) is discharged strengthen, and the heat energy of high-temperature gas is become kinetic energy, thereby improved the propulsive efficiency of motor; After the abundant mixing of high cryogenic gas, promptly under the uniform state of the oxygen content of gas, afterbunring oil delivering device (13) is injected fuel as required, mixes with oxygen-containing gas and secondary combustion, produces the afterbunring jet thrust.
In Figure 10 and Figure 11, main shaft (1), main duct fan (2) and electric fan (3) are under the punching type mode of operation, and the electric fan (3) of main duct fan (2) is smaller angle to reduce the windward side with main shaft (1).
In Figure 12, Figure 13 and Figure 14, when airspeed reached high subsonic speed or supersonic speed, the electric fan (3) of main duct fan (2) was adjusted under the punching type mode of operation; This moment main duct fan (2) and electric fan (3) active rotation not, electric fan (3) can be done corresponding the adjustment with the angle of main shaft (1) simultaneously, adjusting charge air flow, and the minimizing windward side; Behind the extraneous air communication passing through fan flabellum (3), enter rear jet (12), the rear jet (12) of this moment is equivalent to ramjet propulsion; Fuel oil that afterbunring oil delivering device (13) sprays and the air mixing burning expansion that enters produce jet thrust.
Claims (3)
1. inner culvert turbofan and ram-type double-mode engine comprise main shaft (1), main duct fan (2), electric fan (3), centrifugal-flow compressor impeller (4), turbine wheel (5), preceding shell wall (6), gas collecting tube (7), gas collection conduit (8), firing chamber (9), nozzle (10), nozzle air current passage (11), rear jet (12), afterbunring oil delivering device (13), back shell wall (14);
It is characterized in that: main shaft (1), main duct fan (2), electric fan (3) centrifugal-flow compressor impeller (4) and turbine wheel (5) are what be fixed together; Electric fan (3) and main shaft (1) adjustable angle;
During startup, external force drive main spindle (1) rotation makes the common rotation of main duct fan (2), electric fan (3), centrifugal-flow compressor impeller (4) and turbine wheel (5); Ambient air is divided into two partly, enters centrifugal-flow compressor impeller (4) and main duct fan (2) respectively;
Electric fan (3) causes the most suitable angle that air is promoted backward with main shaft (1) angular adjustment; Enter the air of main duct fan (2), under the effect of main duct fan (2) and electric fan (3) rotation thereof, air is moved backward;
The air that enters centrifugal-flow compressor impeller (4) is under the high speed rotating of centrifugal-flow compressor impeller (4), centrifugal force makes air compression, pressurized air is transported to firing chamber (9) through gas collecting tube (7) and gas collection conduit (8), (9) internal combustion expands the back by nozzle (10) to pressurized air in the firing chamber, promote turbine wheel (5) rotation, nozzle air current passage (11) has improved high-temperature combustion gas and has promoted the efficient that turbine wheel (5) rotates, turbine wheel (5) drives main duct fan (2) simultaneously, centrifugal-flow compressor impeller (4) and turbine wheel (5) rotation; High-temperature gas contacts with the cryogenic gas of main duct fan (2) discharge after promoting turbine wheel (5) rotation, and two-part gas traffic direction becomes approximate an angle of 90 degrees to meet; In rear jet (12), high-temperature gas makes the spin intensity of the rotation gas that main duct fan (2) is discharged strengthen, and the heat energy of high-temperature gas is become kinetic energy, has improved the propulsive efficiency of motor; After the abundant mixing of high cryogenic gas, promptly under the uniform state of the oxygen content of gas, afterbunring oil delivering device (13) is injected fuel as required, mixes with oxygen-containing gas and secondary combustion, produces afterburning jet thrust;
When airspeed reached high subsonic speed or supersonic speed, the electric fan (3) of main duct fan (2) was adjusted under the punching type mode of operation with main shaft (1); This moment main duct fan (2) and electric fan (3) active rotation not, electric fan (3) can be done corresponding adjustment with the angle of main shaft (1) simultaneously, to adjust charge air flow, the minimizing windward side; After extraneous air communication is crossed the electric fan (3) of main duct fan (2), enter rear jet (12), the rear jet (12) of this moment is equivalent to ramjet propulsion; Fuel oil that afterbunring oil delivering device (13) sprays and the air mixing burning expansion that enters produce jet thrust.
2. inner culvert turbofan according to claim 1 and ram-type double-mode engine is characterized in that: making centrifugal-flow compressor impeller (4), main duct fan (2) and electric fan (3) is that the axle center rotates synchronously with main shaft (1).
3. turbofan engine according to claim 1 is characterized in that: the electric fan (3) and the angle of main shaft (1) can be regulated as required.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910008924A CN101806259A (en) | 2009-02-13 | 2009-02-13 | Inner culvert turbofan and ram-type double-mode engine |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN200910008924A CN101806259A (en) | 2009-02-13 | 2009-02-13 | Inner culvert turbofan and ram-type double-mode engine |
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| Publication Number | Publication Date |
|---|---|
| CN101806259A true CN101806259A (en) | 2010-08-18 |
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| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN200910008924A Pending CN101806259A (en) | 2009-02-13 | 2009-02-13 | Inner culvert turbofan and ram-type double-mode engine |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102128084A (en) * | 2011-02-18 | 2011-07-20 | 张旭 | Thermal power device for turbine fan engine |
| CN102155331A (en) * | 2011-05-05 | 2011-08-17 | 西北工业大学 | Turboramjet combined engine based on knocking combustion |
| CN106523186A (en) * | 2016-12-30 | 2017-03-22 | 黄祖辉 | Jet engine and airplane |
| CN109026439A (en) * | 2018-05-28 | 2018-12-18 | 华中科技大学 | A kind of combination power device and method based on adjustable fan and sub- burning ramjet |
| CN113466408A (en) * | 2021-06-23 | 2021-10-01 | 新疆生产建设兵团第八师生态环境监测站(石河子市生态环境监测站) | Mobile atmospheric ozone monitoring and processing device and method |
-
2009
- 2009-02-13 CN CN200910008924A patent/CN101806259A/en active Pending
Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN102128084A (en) * | 2011-02-18 | 2011-07-20 | 张旭 | Thermal power device for turbine fan engine |
| CN102155331A (en) * | 2011-05-05 | 2011-08-17 | 西北工业大学 | Turboramjet combined engine based on knocking combustion |
| CN106523186A (en) * | 2016-12-30 | 2017-03-22 | 黄祖辉 | Jet engine and airplane |
| CN106523186B (en) * | 2016-12-30 | 2018-08-10 | 黄祖辉 | Jet engine and aircraft |
| CN109026439A (en) * | 2018-05-28 | 2018-12-18 | 华中科技大学 | A kind of combination power device and method based on adjustable fan and sub- burning ramjet |
| CN113466408A (en) * | 2021-06-23 | 2021-10-01 | 新疆生产建设兵团第八师生态环境监测站(石河子市生态环境监测站) | Mobile atmospheric ozone monitoring and processing device and method |
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Application publication date: 20100818 |