CN208138061U - A kind of microminiature fanjet - Google Patents
A kind of microminiature fanjet Download PDFInfo
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- CN208138061U CN208138061U CN201820660144.3U CN201820660144U CN208138061U CN 208138061 U CN208138061 U CN 208138061U CN 201820660144 U CN201820660144 U CN 201820660144U CN 208138061 U CN208138061 U CN 208138061U
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- pressure turbine
- jet pipe
- fancase
- pressure
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- 239000000567 combustion gas Substances 0.000 claims description 6
- 239000007789 gas Substances 0.000 claims description 5
- 238000002485 combustion reaction Methods 0.000 claims description 4
- 238000002347 injection Methods 0.000 claims 1
- 239000007924 injection Substances 0.000 claims 1
- 239000002131 composite material Substances 0.000 abstract description 2
- 238000010586 diagram Methods 0.000 description 4
- 239000000203 mixture Substances 0.000 description 2
- 230000002159 abnormal effect Effects 0.000 description 1
- 230000009286 beneficial effect Effects 0.000 description 1
- 230000006835 compression Effects 0.000 description 1
- 238000007906 compression Methods 0.000 description 1
- 230000007547 defect Effects 0.000 description 1
- 238000009434 installation Methods 0.000 description 1
- 230000010354 integration Effects 0.000 description 1
- 238000000034 method Methods 0.000 description 1
- 238000012986 modification Methods 0.000 description 1
- 230000004048 modification Effects 0.000 description 1
- 239000010705 motor oil Substances 0.000 description 1
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Abstract
The utility model relates to aero-turbine technical fields, more particularly, to a kind of microminiature fanjet.Its main feature is that including core engine, the core engine rear portion is provided with fanjet low-pressure section by Middle casing, the fanjet low-pressure section includes fancase, integrated turbofan is provided in fancase, intension jet pipe is mounted on the inner surface of fancase by fancase rear support, and fancase rear end is additionally provided with outer culvert jet pipe.A kind of microminiature fanjet passes through the composite structure of low-pressure turbine and blade tip fan, enables intension jet pipe that can be arranged in after fan, so that intension jet pipe, to overcome the Layout Problem of intension jet pipe, can save intension thrust with normal design；Incoming air generates interference before avoiding the high-temperature gas and fan of intension jet pipe discharge, ensure that the normal work of fan, utmostly remains the stagnation pressure of working medium, reduce the loss of energy, reduces the complexity of structure.
Description
Technical field
The utility model relates to aero-turbine technical fields, more particularly, to a kind of microminiature fanjet.
Background technique
Turbojet is the major impetus of contemporary aircraft, can be mainly divided into whirlpool spray, turbofan, whirlpool axis and whirlpool paddle
Four class of engine, is chiefly used in passenger plane, transporter, fighter plane, cruise missile etc..And microminiature turbine engine is one point
Branch, refers to several kilograms of thrust Dao several hundred kilograms, the turbogenerator that several kilowatts to several hundred kilowatts of power.Microminiature turbine engine
Have the advantages that power to weight ratio/thrust ratio is high, flying speed is fast relative to piston engine, there is energy density relative to battery
Height, long-endurance feature are the important motivity directions of the following unmanned plane.
Current microminiature turbine engine is mostly micro turbojet engine, such engine oil consumption rate is higher, energy
Utilization efficiency is lower, and fanjet oil consumption rate is low, energy utilization efficiency is higher, cruise duration is long, is more applicable for low speed
The various small aircrafts of (0.8 Mach or less).But since microminiature turbine engine size is smaller, structure is complex, passes
The design means and topology layout mode of the fanjet of system have been difficult to be applicable in, therefore, microminiature turbine Duct-Burning Turbofan
(abbreviation microminiature fanjet) market is more rare.
The utility model patent of publication number 103216361A proposes two kinds of Novel small-size duct turbofan engine schemes, and one
Turbojet engine core engine and postposition free turbine, retarder, the reversed installation concatenated means of fan are completed whirlpool by kind scheme
The realization of fan engine structure.Its problem is that the jet direction of intension jet pipe is consistent with directional velocity, causes intension thrust complete
Total loss, and generate resistance；The thermal current of intension jet pipe can be blown into fan by stream air, cause fan inlet flow field temperature abnormal
Become, influences fan normal work；Fan is fitted without jet pipe, causes the pressure of its fan to rise the promotion for being not converted to speed, leads
Cause declining to a great extent for thrust.Another scheme will be the turbojet engine core engine that will reversely install and free turbine, fan group
Altogether, stream air passes through the core engine reversely installed after fan by pipeline introducing, and the air-flow of core engine passes through pipeline again
It is pierced by the pipeline discharge of core engine bleed.The problem of program, is that (1) structure is excessively complicated, pipeline is interfered, difficult arrangement, difficult
To realize；
(2) excessive pipeline causes the pressure loss of air-flow excessive, and energy utilization efficiency is low.
It to sum up analyzes, the less technical solution about microminiature fanjet of the prior art, and the technology that can be inquired
There is (1) intension jet pipe difficult arrangement in scheme, lead to thrust loss；(2) provided with internal duct and external duct structure uncoordinated unreasonable (3) is high
Thrust loss is pressed, (4) scheme realizes difficulty problem.
Summary of the invention
The purpose of this utility model is that avoiding the defect of the prior art and providing a kind of microminiature fanjet, effectively
It solves the problems, such as of the existing technology.
To achieve the above object, the technical solution that the utility model is taken is：A kind of microminiature fanjet,
Its main feature is that including core engine, the core engine rear portion is provided with fanjet low-pressure section by Middle casing, described
Fanjet low-pressure section include fancase, fancase front end is mounted on Middle casing by fancase front support
Outer surface, fancase rear end is mounted on intension jet pipe outer surface by fancase rear support, is provided in fancase
Integrated turbofan, integrated turbofan are sleeved on low pressure by low pressure rotor axis fore bearing and low pressure rotor axis rear bearing
On armature spindle, low pressure rotor axis fore bearing is installed on low pressure rotor airscoop shroud inner wall, low pressure by low pressure rotor axis front support
Turbine inflow cover is installed on Middle casing inner surface by low-pressure turbine front support；Low pressure rotor axis rear bearing passes through low pressure rotor
Axis rear support is mounted on the inner surface of low pressure turbine exhaust cone；Low pressure turbine exhaust cone is mounted on interior by low-pressure turbine rear support
Contain the inner surface of jet pipe, intension jet pipe is mounted on the inner surface of fancase, fancase rear end by fancase rear support
It is additionally provided with outer culvert jet pipe.
The core engine be micro turbojet engine, core engine mainly by compressor, engine crankcase, combustion chamber,
Armature spindle and turbine composition, core engine provide the combustion gas working medium of high temperature and pressure mainly as gas generator.
The integrated turbofan is an integral structure, and integrated turbofan includes low-pressure turbine disk, low pressure whirlpool
Impeller blade, low-pressure turbine integral shroud and blade tip fan form, and are provided among low-pressure turbine disk for installing bearing and low pressure rotor
The hole of axis, low-pressure turbine blade one end are connected with low-pressure turbine disk, and low-pressure turbine disk and low-pressure turbine blade constitute a kind of axis
Steam turbines structure, low-pressure turbine integral shroud are a ring structure, inner surface and the low-pressure turbine blade phase of low-pressure turbine integral shroud
Even, the outer surface of low-pressure turbine integral shroud is connected with the blade root of blade tip fan.
The Middle casing is a cylindrical housings, the engine crankcase in the front end face and core engine of Middle casing
Rear end face be connected, the outer surface of engine crankcase rear end face flushes with the upper surface of the front end of low-pressure turbine integral shroud and is arranged 2
The gap~5mm constitutes the air inlet runner of a part of blade tip fan.
The fancase is a cylinder-like structure, and integrated turbofan is by fancase, the outer culvert
Jet pipe is the cylinder of a convergent contour, and the outer biggish end face of annulus area for containing jet pipe is connected with the rear end face of fancase,
The intension jet pipe is the cylinder of a convergent contour, table on the rear end upper surface of intension jet pipe 8 and the rear end of low-pressure turbine disk
Face flushes and the gap 2~5mm is arranged for accelerating the air-flow of low-pressure turbine blade fan discharge, generating thrust, and intension jet pipe leans on
Closely outer surface height with the back end outer surface of low-pressure turbine integral shroud highly equal, the intension jet pipe of one end of integration turbofan
It is provided directly with the gap 2~5mm with integrated turbofan, the outer surface of intension jet pipe forms a part row of blade tip fan
Flow channel；Point-blank, the low-pressure turbine airscoop shroud is one to the armature spindle of the low pressure rotor axis and core engine
On the one hand a tubular structure, low-pressure turbine airscoop shroud are used to constitute the runner of air-flow working medium, low-pressure turbine airscoop shroud is on the other hand
For providing support, low-pressure turbine airscoop shroud front end is closed cylinder bottom, low-pressure turbine airscoop shroud rear end upper surface and low pressure whirlpool
Wheel disc front end upper surface flushes and is provided with the gap 2~5mm and constitutes a part of air inlet runner of low-pressure turbine blade, described
Low pressure turbine exhaust cone be a conical shell, low pressure turbine exhaust taper is at grate flow channel and provides support.
The utility model has the beneficial effects that：A kind of microminiature fanjet uses low pressure rotor and height
The separated mode of pressure rotor had both avoided traditional fanjet " axle sleeve axis " scheme by way of " tandem rotor "
The problem of being difficult to realize with " multiple pipeline ".It enables intension jet pipe can be with by composite structure of low-pressure turbine and blade tip fan
It is arranged in after fan, so that intension jet pipe, to overcome the Layout Problem of intension jet pipe, can be saved interior with normal design
Contain thrust；After being arranged in fan due to intension jet pipe, incoming flow is empty before avoiding the high-temperature gas and fan of intension jet pipe discharge
Gas generates interference, ensure that the normal work of fan.In addition, by installing outer culvert jet pipe additional after fan, so that flowing through fan
Pressurized air be able to generate higher thrust；There is no excessive pipeline to introduce in the utility model, utmostly remains work
The stagnation pressure of matter reduces the loss of energy, reduces the complexity of structure.
Detailed description of the invention
Fig. 1 is the utility model principle schematic diagram；
Fig. 2 is the utility model concrete structure schematic diagram
Fig. 3 is schematic cross-sectional view at the C-C in the utility model Fig. 2；
Fig. 4 is the core engine principle schematic diagram in the utility model Fig. 2；
Fig. 5 is the integrated turbofan principle schematic diagram in the utility model Fig. 2；
Fig. 6 is sectional structure schematic illustration at the B-B of the utility model Fig. 5；
As shown in the figure：1, core engine；2, Middle casing；3, fancase front support；4, fancase；5, integrated turbine
Fan；6, outer culvert jet pipe；7, fancase rear support；8, intension jet pipe；9, low-pressure turbine rear support；10, low pressure turbine exhaust
Cone；11, low pressure rotor axis rear bearing；12, low pressure rotor axis rear support；13, low pressure rotor axis front support；14, before low-pressure turbine
Support；15, low pressure rotor axis fore bearing；16, low pressure rotor axis；17, low-pressure turbine airscoop shroud；18, compressor；19, engine
Casing；20, combustion chamber；21, armature spindle；22, turbine；23, low-pressure turbine disk；24, low-pressure turbine blade；25, low-pressure turbine leaf
Hat；26, blade tip fan；27, fanjet low-pressure section.
Specific embodiment
The principles of the present invention and feature are described below in conjunction with attached drawing, example is served only for explaining that this is practical
It is novel, it is not intended to limit the scope of the utility model.
As shown in Figures 1 to 6, a kind of microminiature fanjet, its main feature is that including core engine 1, the core
1 rear portion of scheming is provided with fanjet low-pressure section 27 by Middle casing 2, and the fanjet low-pressure section 27 is wrapped
Fancase 4 is included, 4 front end of fancase is mounted on the outer surface of Middle casing 2, fancase 4 by fancase front support 3
Rear end is mounted on 8 outer surface of intension jet pipe by fancase rear support 7, is provided with integrated turbofan in fancase 4
5, integrated turbofan 5 is sleeved on low pressure rotor axis 16 by low pressure rotor axis fore bearing 15 and low pressure rotor axis rear bearing 11
On, low pressure rotor axis fore bearing 15 is installed on 17 inner wall of low-pressure turbine airscoop shroud, low pressure by low pressure rotor axis front support 13
Turbine inflow cover 17 is installed on 2 inner surface of Middle casing by low-pressure turbine front support 14；Low pressure rotor axis rear bearing 11 passes through
Low pressure rotor axis rear support 12 is mounted on the inner surface of low pressure turbine exhaust cone 10；Low pressure turbine exhaust cone 10 passes through low-pressure turbine
Rear support 9 is mounted on the inner surface of intension jet pipe 8, and intension jet pipe 8 is mounted on fancase 4 by fancase rear support 7
Inner surface, 4 rear end of fancase are additionally provided with outer culvert jet pipe 6.
The core engine 1 is micro turbojet engine, and core engine is mainly by compressor 18, engine crankcase 19, combustion
It burns room 20, armature spindle 21 and turbine 22 to form, core engine provides the combustion gas working medium of high temperature and pressure mainly as gas generator.
The integrated turbofan 5 is an integral structure, and integrated turbofan includes low-pressure turbine disk 23, low pressure
Turbo blade 24, low-pressure turbine integral shroud 25 and blade tip fan 26 form, and are provided among low-pressure turbine disk 23 for installing bearing
With the hole of low pressure rotor axis 16,24 one end of low-pressure turbine blade is connected with low-pressure turbine disk 23, low-pressure turbine disk 23 and low pressure whirlpool
Impeller blade 24 constitutes a kind of axial-flow turbine structure, and low-pressure turbine integral shroud 25 is a ring structure, low-pressure turbine integral shroud 25
Inner surface be connected with low-pressure turbine blade 24, the outer surface of low-pressure turbine integral shroud 25 is connected with the blade root of blade tip fan 26.
The Middle casing 2 is a cylindrical housings, the engine machine in the front end face and core engine of Middle casing 2
The rear end face of casket 19 is connected, and the outer surface of 19 rear end face of engine crankcase is flushed with the upper surface of the front end of low-pressure turbine integral shroud 25
And the air inlet runner that the gap 2~5mm constitutes a part of blade tip fan 26 is set.
The fancase 4 is a cylinder-like structure, and for integrated turbofan 5 in fancase 4, described is outer
Contain the cylinder that jet pipe 6 is a convergent contour, the outer biggish end face of annulus area for containing jet pipe 6 and the rear end face phase of fancase 4
Connection, the intension jet pipe 8 are the cylinder of a convergent contour, rear end upper surface and the low-pressure turbine disk 23 of intension jet pipe 8
Rear end upper surface flushes and the gap 2~5mm is arranged for accelerating the air-flow of the discharge of low-pressure turbine blade 24, generating thrust, intension
Outer surface height and the back end outer surface height phase of low-pressure turbine integral shroud 25 of the jet pipe 8 close to one end of integrated turbofan 5
It is flat, the gap 2~5mm is provided between intension jet pipe 8 and integrated turbofan 5, the outer surface of intension jet pipe forms blade tip
A part of grate flow channel of fan 26；The armature spindle 21 of the low pressure rotor axis 16 and core engine 1 is point-blank, described
Low-pressure turbine airscoop shroud 17 be a tubular structure, 17 one side of low-pressure turbine airscoop shroud is used to constitute the stream of air-flow working medium
Road, on the other hand for providing support, 17 front end of low-pressure turbine airscoop shroud is closed cylinder bottom, 17 rear end of low-pressure turbine airscoop shroud
Upper surface flushes with 23 front end upper surface of low-pressure turbine disk and is provided with the gap 2~5mm and constitutes low-pressure turbine blade 24
A part of air inlet runner, the low pressure turbine exhaust cone 10 are a conical shell, and low pressure turbine exhaust cone 10 forms exhaust
Runner simultaneously provides support.
A kind of microminiature fanjet, when work, core engine 1 sucks incoming air, compression, burning plus
Heat, expansion, and generate the combustion gas working medium of high temperature and pressure high speed；Combustion gas working medium passes through low-pressure turbine airscoop shroud 17 and Middle casing 2
The runner of composition flows into low-pressure turbine blade 24, and driving low-pressure turbine blade 24 rotates, that is, drives entire integrated turbofan 5
Rotation, combustion gas working medium are discharged after 24 decompressional expansion of low-pressure turbine blade by intension jet pipe 8, generate intension thrust；The leaf of rotation
The free incoming air in the sharp sucking of fan 26 front, pressurizes and accelerates, and then by outer 6 Accelerating Removal of culvert jet pipe, generates outer culvert thrust.
To limit the utility model, within the spirit and principle of the utility model, made any modification is equally replaced
It changes, improve, should be included within the scope of protection of this utility model.
Claims (5)
1. a kind of microminiature fanjet, it is characterized in that including core engine, the core engine rear portion is set by Middle casing
It is equipped with fanjet low-pressure section, the fanjet low-pressure section includes fancase, and fancase front end passes through
Fancase front support is mounted on the outer surface of Middle casing, and fancase rear end is mounted on intension by fancase rear support
Jet pipe outer surface, integrated turbofan is provided in fancase, and integrated turbofan passes through low pressure rotor axis fore bearing
It is sleeved on low pressure rotor axis with low pressure rotor axis rear bearing, low pressure rotor axis fore bearing is installed by low pressure rotor axis front support
In low pressure rotor airscoop shroud inner wall, low-pressure turbine airscoop shroud is installed on Middle casing inner surface by low-pressure turbine front support；
Low pressure rotor axis rear bearing is mounted on the inner surface of low pressure turbine exhaust cone by low pressure rotor axis rear support；Low pressure turbine exhaust
Cone is mounted on the inner surface of intension jet pipe by low-pressure turbine rear support, and intension jet pipe is mounted on wind by fancase rear support
The inner surface of casing is fanned, fancase rear end is additionally provided with outer culvert jet pipe.
2. a kind of microminiature fanjet as described in claim 1, it is characterised in that：The core engine is microminiature whirlpool
Fuel-injection engine, core engine are mainly made of compressor, engine crankcase, combustion chamber, armature spindle and turbine, core engine mainly as
The combustion gas working medium of gas generator offer high temperature and pressure.
3. a kind of microminiature fanjet as described in claim 1, it is characterised in that：The integrated turbofan is
Integral structure, integrated turbofan include low-pressure turbine disk, low-pressure turbine blade, low-pressure turbine integral shroud and blade tip fan group
At being provided with the hole for installing bearing Yu low pressure rotor axis among low-pressure turbine disk, low-pressure turbine blade one end and low pressure whirlpool
Wheel disc is connected, and low-pressure turbine disk and low-pressure turbine blade constitute a kind of axial-flow turbine structure, and low-pressure turbine integral shroud is one
The inner surface of ring structure, low-pressure turbine integral shroud is connected with low-pressure turbine blade, the outer surface of low-pressure turbine integral shroud and blade tip wind
The blade root of fan is connected.
4. a kind of microminiature fanjet as described in claim 1, it is characterised in that：The Middle casing is a circle
The rear end face of cylindrical shell, the engine crankcase in the front end face and core engine of Middle casing is connected, engine crankcase rear end face
Outer surface flushed with the upper surface of the front end of low-pressure turbine integral shroud and be arranged the gap 2~5mm constitute blade tip fan a part
Air inlet runner.
5. a kind of microminiature fanjet as described in claim 1, it is characterised in that：The fancase is a circle
Tubular structure, for integrated turbofan by fancase, the outer culvert jet pipe is the cylinder of a convergent contour, outer culvert jet pipe
The biggish end face of annulus area be connected with the rear end face of fancase, the intension jet pipe be a convergent contour circle
Cylinder, the rear end upper surface of intension jet pipe 8 flush with the rear end upper surface of low-pressure turbine disk and the gap 2~5mm are arranged for accelerating
The air-flow of low-pressure turbine blade fan discharge generates thrust, outer surface of the intension jet pipe close to one end of integrated turbofan
Height is equal with the back end outer surface of low-pressure turbine integral shroud height, and intension jet pipe and integrated turbofan be provided directly with 2~
The gap 5mm, the outer surface of intension jet pipe form a part of grate flow channel of blade tip fan；The low pressure rotor axis and core
Point-blank, the low-pressure turbine airscoop shroud is a tubular structure, one side of low-pressure turbine airscoop shroud to the armature spindle of machine
Face is used to constitute the runner of air-flow working medium, on the other hand low-pressure turbine airscoop shroud is used to provide support, before low-pressure turbine airscoop shroud
End is closed cylinder bottom, low-pressure turbine airscoop shroud rear end upper surface flush and is provided with 2 with low-pressure turbine disk front end upper surface~
The gap 5mm simultaneously constitutes a part of air inlet runner of low-pressure turbine blade, and the low pressure turbine exhaust cone is a conical shell
Body, low pressure turbine exhaust taper is at grate flow channel and provides support.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820660144.3U CN208138061U (en) | 2018-05-04 | 2018-05-04 | A kind of microminiature fanjet |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201820660144.3U CN208138061U (en) | 2018-05-04 | 2018-05-04 | A kind of microminiature fanjet |
Publications (1)
| Publication Number | Publication Date |
|---|---|
| CN208138061U true CN208138061U (en) | 2018-11-23 |
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Family Applications (1)
| Application Number | Title | Priority Date | Filing Date |
|---|---|---|---|
| CN201820660144.3U Withdrawn - After Issue CN208138061U (en) | 2018-05-04 | 2018-05-04 | A kind of microminiature fanjet |
Country Status (1)
| Country | Link |
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| CN (1) | CN208138061U (en) |
Cited By (1)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108506111A (en) * | 2018-05-04 | 2018-09-07 | 西北工业大学 | A kind of microminiature fanjet |
-
2018
- 2018-05-04 CN CN201820660144.3U patent/CN208138061U/en not_active Withdrawn - After Issue
Cited By (2)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN108506111A (en) * | 2018-05-04 | 2018-09-07 | 西北工业大学 | A kind of microminiature fanjet |
| CN108506111B (en) * | 2018-05-04 | 2023-11-17 | 西安觉天动力科技有限责任公司 | Microminiature turbofan engine |
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| GR01 | Patent grant | ||
| GR01 | Patent grant | ||
| TR01 | Transfer of patent right | ||
| TR01 | Transfer of patent right |
Effective date of registration: 20220607 Address after: 710075 1-9-291, floor 9, angel building, Chuangye coffee block, No. 9, Gaoxin Second Road, high tech Zone, Xi'an City, Shaanxi Province Patentee after: Xi'an juetian Power Technology Co.,Ltd. Address before: 710072 No. 127 Youyi West Road, Shaanxi, Xi'an Patentee before: Northwestern Polytechnical University |
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| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned | ||
| AV01 | Patent right actively abandoned |
Granted publication date: 20181123 Effective date of abandoning: 20231117 |
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| AV01 | Patent right actively abandoned |
Granted publication date: 20181123 Effective date of abandoning: 20231117 |