CN208831104U - A kind of gear drive fanjet - Google Patents
A kind of gear drive fanjet Download PDFInfo
- Publication number
- CN208831104U CN208831104U CN201821175425.6U CN201821175425U CN208831104U CN 208831104 U CN208831104 U CN 208831104U CN 201821175425 U CN201821175425 U CN 201821175425U CN 208831104 U CN208831104 U CN 208831104U
- Authority
- CN
- China
- Prior art keywords
- pressure
- low
- fan
- shaft
- fanjet
- 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.)
- Active
Links
Abstract
The utility model gear drive fanjet drives high pressure ratio high pressure centrifugal compressor using high-pressure turbine, while starting-generating motor integrating being integrated in the front end of high-pressure shaft, has the characteristics that structure is simple, light-weight, high reliablity；Low-pressure turbine drives fan and booster stage by gear reduction, makes to work under low-pressure turbine shaft and fan and each optimal design speed of leisure of booster stage；Combustion chamber has the characteristics that high combustion efficiency, low pollution object discharge, are compact-sized using reflux toroidal combustion chamber；Main duct and by-pass air duct air are blended by mixer, are reached and are improved exhaust efficiency, increase thrust, reduce the effect of noise.The design configuration of gear drive fanjet has structure simple, compact, the features such as comprehensive performance good (high bypass ratio, high overall pressure tatio, high thrust ratio, long-life, low cost, low oil consumption, low noise, low pollution), it can be widely applied to the aircraft models such as unmanned plane, target drone, trainer aircraft, business airplane.
Description
Technical field
The utility model relates to fanjet technical field of structures, in particular to a kind of gear drive fanjet.
Background technique
The basic configuration of existing fanjet is low pressure axis connection fan, low-pressure compressor (booster stage) and low pressure whirlpool
Wheel, the cross-compound arrangement of high pressure axis connection high-pressure compressor and high-pressure turbine.This twin shaft configuration has passed through nearly development in 60 years
Relative maturity, but in component design aspect, there are some bottlenecks for being difficult to overcome.Fan blade diameter is big, and revolving speed height leads to blade tip
Tangential velocity is high, considerably beyond the velocity of sound in high-altitude, air at fan inlet is made to generate shock wave so as to cause serious gas flowfield
Disorder significantly reduces fan efficiency.Fan blade tip is set to be in subsonic speed state if reducing low-pressure turbine revolving speed, it can be significantly
The output power for reducing low-pressure turbine, causes overall engine efficiency to decline.
In terms of power draw, traditional twin-spool engine design mainly passes through gear and this structure extraction of transmission shaft
Mechanical work is generated electricity and is driven attachment combustion oil pump etc..This structure-design technique is mature but that there are weight is big, structure is multiple
The weakness such as miscellaneous, poor reliability, it is difficult to realize that the development of the modernizations such as accurate electronic control and intelligent Gernral Check-up management needs
It wants.
Utility model content
In order to solve the above-mentioned technical problem, the utility model provides a kind of gear drive fanjet design configuration.
The above-mentioned technical purpose of the utility model has the technical scheme that
A kind of gear drive fanjet, the height including low-pressure shaft and outside low-pressure shaft, with low-pressure shaft coaxial line
Last item, the low-pressure shaft both ends are connected separately with fan and low-pressure turbine, which is characterized in that and the fan is connected to fan shaft,
The fan shaft passes through gear reduction and low pressure axis connection；Built-in starting-generating one electricity is successively arranged in the high-pressure shaft
Machine, high-pressure compressor and high-pressure turbine.
Preferably, including main duct and by-pass air duct, the fan are located at the inlet mouth of inside and outside duct, the fan
Axis is equipped with booster stage, and the booster stage is located at main duct entrance.
By using above scheme, stream pressure and temperature are further improved, is carried out for subsequent high-pressure compressor last
Pressurization is prepared, and is preferably released the acting ability of high-pressure shaft and low-pressure shaft, is produced high-pressure compressor at higher rotational speeds
Raw higher pressure ratio.
Preferably, the high-pressure compressor uses centrifugal-flow compressor.
By using above-mentioned configuration scheme, entire combination is by fan, booster stage, centrifugal-flow compressor, it can be achieved that than passing
The higher overall pressure tatio of system configuration and the thermal efficiency；The design for the single stage centrifugal high-pressure compressor simplified is to built-in starting-generating one
Motor leaves sufficient space, and keeps the structure of engine simpler, compact, and component efficiencies are higher.
Preferably, the outlet of the main duct and by-pass air duct is equipped with mixer.
By using above scheme, so that inside and outside bypass air is sufficiently mixed heel row and go out engine, to reduce exhaust velocity,
Propulsive efficiency is improved, and exhaust noise is effectively reduced.
Preferably, combustion chamber is equipped between the high-pressure compressor and high-pressure turbine, the combustion chamber is using reflux annular
Combustion chamber.
By using above scheme, engine is made to have the characteristics that high combustion efficiency, oil consumption rate are low, compact-sized.
In conclusion the utility model design configuration has the advantages that
1, by installing gear reduction additional between low-pressure turbine and fan and booster stage, rotation speed of the fan can be made significantly low
In low-pressure shaft revolving speed, at the same meet fan slowly run rotation relatively high speed with low-pressure turbine the needs of, and low-pressure turbine can be made
Series reduce, to reduce design difficulty and substantially increase fan efficiency；
2, using a kind of more electric design structures of built-in starting-generating motor integrating, engine is started by magnetoelectric effect,
Until engine reaches normal work revolving speed.After engine enters normal operating conditions, which is converted into power generator, to
Battery charging, and it is transmitted to each accessory unit；Electrical accessory helps to reduce the number of parts of attachment, to reduce hair
The weight of motivation complete machine makes attachment mechanism modularization be easy to carry out fault diagnosis and maintenance, while improving the electrical of engine
Change and Intelligent health diagnosisization is horizontal；
3, by the Combination Design of above-mentioned configuration and component, the engine is relative to pushing away on an equal basis using traditional twin shaft configuration
Force engine, cruise oil consumption rate can be greatly lowered.
Detailed description of the invention
Fig. 1 is the structural schematic diagram of gear drive fanjet.
In figure, 1, fan；2, booster stage；3, gear reduction；4, built-in starting-generating motor integrating；5, high pressure is calmed the anger
Machine；6, combustion chamber；7, high-pressure turbine；8, low-pressure turbine；9, mixer；10, fan shaft；11, low-pressure shaft；12, end-float coupling；
13, high-pressure shaft；14, front support casing；15, rear support casing；16, main duct；17, by-pass air duct.
Specific embodiment
The utility model is described in further detail below in conjunction with attached drawing.
Embodiment:
Referring to Fig. 1, the utility model provides a kind of gear drive turbogenerator, including main duct 16 and by-pass air duct
17, inside, in by-pass air duct 16,17 from entrance to outlet be disposed with fan 1, booster stage 2, gear reduction 3, it is built-in
Dynamic power generation integrated motor 4, high-pressure compressor 5, combustion chamber 6, high-pressure turbine 7, low-pressure turbine 8 and mixer 9.8 He of low-pressure turbine
The blade of high-pressure turbine 9 is made of single crystal super alloy casting；Booster stage 2 specifically uses two-step supercharging grade；Gear reduction unit
Structure 3 is specially double helical tooth or helical teeth planetary reducer；High-pressure compressor 5 specifically uses centrifugal-flow compressor；Combustion chamber 6 has
Body is using reflux toroidal combustion chamber.
Fan 1 and booster stage 2 are connected in turn on fan shaft 10 by bolt and set tooth, and fan 1 is located inside and outside duct
16,17 inlet mouth, booster stage 2 are located at 16 entrance of main duct, and fan shaft 10 passes through gear reduction 3 and low-pressure shaft 11
Connection, wherein low-pressure shaft 11 and gear reduction 3 by can the end-float coupling 12 of self-control connect, low-pressure turbine 8 is pacified
Mounted in the other end of low-pressure shaft 11.11 uter coaxial line of low-pressure shaft is equipped with high-pressure shaft 13, along air current flow direction in high-pressure shaft 13
It is successively arranged built-in starting-generating motor integrating 4, high-pressure compressor 5 and high-pressure turbine 7；Built-in starting-generating motor integrating 4 is pacified
Mounted in the front end of high-pressure shaft 13, the electric energy that issues is exported by cable to attachment mechanism, positioned at built-in starting in high-pressure shaft 13
4 rear of power generation integrated motor is sequentially installed with high-pressure compressor 5 and high-pressure turbine 7, and combustion chamber 6 is set to 5 He of high-pressure compressor
Between high-pressure turbine 7.
Fan shaft 10, low-pressure shaft 11 and high-pressure shaft 13 are respectively by two bearing supports in front support casing 14 and rear support
On the installation section of casing 15, two bearings on fan shaft 10 are between booster stage 2 and gear reduction 3；Low-pressure shaft 11
On two bearings be located at before built-in starting-generating motor integrating 4 and after low-pressure turbine 8, wherein rear bearing bearing is bullet
Property supporting structure；Two bearings in high-pressure shaft 13 are located at the rear and front end of high-pressure compressor 5.
Mixer 9 uses petal mixer, is mounted on the outlet of air jet pipe main duct 16 and by-pass air duct 17, will come from intension
The air-flow of road 16 and by-pass air duct 17 is mixed.
In actual motion, air stream enters air intake duct, is divided into two strands of air-flows after the pressurization of passing through fan 1, respectively by outer
Duct 17 and main duct 16.16 air-flow of main duct is burning behind 1 root of passing through fan and the pressurization of booster stage 2 and high-pressure compressor 5
It burns in room 6, the pressure high temperature hot gas after burning passes sequentially through 8 expansion work of high-pressure turbine 7 and low-pressure turbine, passes through height respectively
Last item 13 and low-pressure shaft 11 drive the high-pressure compressor 5 of front and fan 1, booster stage 2, gear reduction 3 to operate, after expansion
Gas mixed finally by petal mixer 9 with 17 air-flow of by-pass air duct after engine is discharged at a high speed, so that engine be made to produce
Raw forward thrust.
This specific embodiment is only the explanation to the utility model, does not constitute limitations of the present invention, this
Field technical staff can according to need the modification that not creative contribution is made to the present embodiment after reading this specification
And supplement, but as long as all by the protection by Patent Law in the scope of the claims of the utility model.
Claims (5)
1. a kind of gear drive fanjet, including low-pressure shaft (11) and be set to low-pressure shaft (11) it is external, with low-pressure shaft (11)
The high-pressure shaft (13) of coaxial line, low-pressure shaft (11) both ends are connected separately with fan (1) and low-pressure turbine (8), and feature exists
In the fan (1) is connected to fan shaft (10), and the fan shaft (10) passes through gear reduction (3) and low-pressure shaft (11)
Connection；Built-in starting-generating motor integrating (4), high-pressure compressor (5) and high-pressure turbine are successively arranged on the high-pressure shaft (13)
(7)。
2. a kind of gear drive fanjet according to claim 1, which is characterized in that including main duct (16) and outside
Duct (17), the fan (1) are located at the inlet mouth of inside and outside duct (16,17), and the fan shaft (10) is equipped with pressurization
Grade (2), the booster stage (2) are located at main duct (16) entrance.
3. a kind of gear drive fanjet according to claim 2, which is characterized in that the high-pressure compressor (5)
Using centrifugal-flow compressor.
4. a kind of gear drive fanjet according to claim 2, which is characterized in that the main duct (16) and outer
The outlet of duct (17) is equipped with mixer (9).
5. a kind of gear drive fanjet according to claim 1, which is characterized in that the high-pressure compressor (5)
Combustion chamber (6) are equipped between high-pressure turbine (7), the combustion chamber (6) is using reflux toroidal combustion chamber.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821175425.6U CN208831104U (en) | 2018-07-24 | 2018-07-24 | A kind of gear drive fanjet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201821175425.6U CN208831104U (en) | 2018-07-24 | 2018-07-24 | A kind of gear drive fanjet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208831104U true CN208831104U (en) | 2019-05-07 |
Family
ID=66307204
Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201821175425.6U Active CN208831104U (en) | 2018-07-24 | 2018-07-24 | A kind of gear drive fanjet |
Country Status (1)
| Country | Link |
|---|---|
| CN (1) | CN208831104U (en) |
Cited By (3)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110630384A (en) * | 2019-08-30 | 2019-12-31 | 江西洪都航空工业集团有限责任公司 | Combined starting device of gas turbine engine for bomb |
| CN111779592A (en) * | 2020-06-01 | 2020-10-16 | 北京航空航天大学 | Mixed exhaust turbofan engine propulsion system introducing parallel combustion chambers |
| CN113738531A (en) * | 2021-11-03 | 2021-12-03 | 中国航发沈阳发动机研究所 | Indirect cooling type high-total-pressure-ratio middle duct turbofan engine |
-
2018
- 2018-07-24 CN CN201821175425.6U patent/CN208831104U/en active Active
Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN110630384A (en) * | 2019-08-30 | 2019-12-31 | 江西洪都航空工业集团有限责任公司 | Combined starting device of gas turbine engine for bomb |
| CN111779592A (en) * | 2020-06-01 | 2020-10-16 | 北京航空航天大学 | Mixed exhaust turbofan engine propulsion system introducing parallel combustion chambers |
| CN113738531A (en) * | 2021-11-03 | 2021-12-03 | 中国航发沈阳发动机研究所 | Indirect cooling type high-total-pressure-ratio middle duct turbofan engine |
| CN113738531B (en) * | 2021-11-03 | 2022-02-18 | 中国航发沈阳发动机研究所 | Indirect cooling type high-total-pressure-ratio middle duct turbofan engine |
Similar Documents
| Publication | Publication Date | Title |
|---|---|---|
| CN106468219B (en) | Gas-turbine unit stall margin management | |
| CN105164385B (en) | Compressor system | |
| US7770377B2 (en) | Turbofan arrangement | |
| CN208831104U (en) | A kind of gear drive fanjet | |
| US2504181A (en) | Double compound independent rotor | |
| CN107939513B (en) | Electric auxiliary clutch type power turbine composite supercharger | |
| JPH0142879B2 (en) | ||
| CN108518289A (en) | A kind of blade tip jet is from driving wheel-type Duct-Burning Turbofan | |
| CN108518263A (en) | A kind of turbofan generating equipment of vehicle exhaust energy recycling | |
| CN110397519A (en) | A kind of miniature oil electric mixed dynamic fanjet | |
| CN209324517U (en) | Three axis triple channels become duct variable diameter in series and parallel and adaptively recycle to turning jet engine | |
| US20220136402A1 (en) | Electric machine assembly for a turbine engine | |
| IT202000002695A1 (en) | GEAR TRANSMISSION UNIT FITTED WITH AN ELECTRIC MOTOR | |
| CN106988882A (en) | Twin-stage is to turning gas turbine | |
| CN113864083A (en) | Novel variable-cycle gas turbine engine | |
| CN107246330B (en) | Turbine turbofan engine and spacecraft | |
| CN113006940A (en) | Micro turboprop engine without external speed reducer | |
| CN108626026A (en) | A kind of novel microminiature fan postposition fanjet | |
| CN112739896B (en) | Turbojet engine with speed reducing mechanism | |
| CN208040567U (en) | A kind of boosting impacting fanjet | |
| CN112739901A (en) | Turbo-reactor comprising a power supply device | |
| CN212615068U (en) | Distributed propulsion turbofan engine | |
| CN205025617U (en) | Impulse type turbine -propeller engine | |
| CN201730700U (en) | Free fan stress application jet engine | |
| CN208734454U (en) | A kind of novel microminiature fan postposition fanjet |
Legal Events
| Date | Code | Title | Description |
|---|---|---|---|
| GR01 | Patent grant | ||
| GR01 | Patent grant |