CN103971580B - Turbofan/turbojet aero-engine combined model used for teaching - Google Patents
Turbofan/turbojet aero-engine combined model used for teaching Download PDFInfo
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- CN103971580B CN103971580B CN201410177190.4A CN201410177190A CN103971580B CN 103971580 B CN103971580 B CN 103971580B CN 201410177190 A CN201410177190 A CN 201410177190A CN 103971580 B CN103971580 B CN 103971580B
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Abstract
Provided is a turbofan/turbojet aero-engine combined model used for teaching. The turbofan/turbojet aero-engine combined model used for teaching comprises a low-pressure compressor, a core engine, a low-pressure turbine, an exhaust nozzle, an outer duct and a fairing. When the turbofan/turbojet aero-engine combined model serves as a turbofan aero-engine model, the turbofan aero-engine model is composed of the outer duct, the low-pressure compressor, the core engine, the low-pressure turbine and the exhaust nozzle, wherein the outer duct is installed on the axis end of a shaft of the low-pressure compressor. When the turbofan/turbojet aero-engine combined model serves as a turbojet aero-engine teaching model, the turbojet aero-engine teaching model is composed of the fairing, the low-pressure compressor, the core engine, the low-pressure turbine and the exhaust nozzle, wherein the fairing is installed at the axis end of the shaft of the low-pressure turbine. Common parts in an aero-engine are combined with different parts in different aero-engines so as to form aero-engine models of different types, students can deeply and comprehensively understand the structures of engines of different types conveniently, the effect of experiment teaching is improved effectively, experiment content can be extended, labor intensity is relieved, and experiment cost is lowered.
Description
Technical field
The invention belongs to a kind of aero-engine model, more particularly to a kind of teaching turbofan/whirlpool spray aero-engine
Built-up pattern.
Background technology
At present, aero-engine model is used in existing teaching, mainly uses the overdue aero-engine of service life and passes through
Cutting is processed and is obtained, or the teaching engine mockup manufactured by specialized company.
Existing teaching engine mockup mainly has the disadvantage that：
1. existing teaching engine mockup is all the aero-engine research manufacture for specific model or type, work(
Can be single, only can be simulated demonstration to a model electromotor or a type of electromotor, function be restricted it is impossible to
Make student that whole aero-engine family System forming system is comprehensively recognized.
2. to the longevity electromotor as teaching mode, bulky, be not easy to movement, limited amount, obtain difficult, and
Can only show in particular places such as laboratorys it is impossible to be placed in using it is impossible to synchronously carry out with teaching process in classroom, in teaching
Hold and be difficult to be fitted close, good effect can not be played to helping student's intensification to be appreciated and understood by the content of courses.
3. although the teaching engine mockup emulator manufactured by specialized company is high, expensive, one
As universities and colleges cannot realize promoting on a large scale.This class model mostly is mock-up model, equally exists and is difficult to dismount, and is not easy to move,
Student at any time, observe the drawbacks such as electromotor with hall can not be unfavorable for that student grasps the internal structure of electromotor as soon as possible, religion
Learn effect and be subject to a certain degree of impact.
Therefore, develop one kind vdiverse in function, highly versatile, it is easy to dismount, is easy to carry, cheap, is not limited by place
The teaching of system, with multifunction combined aero-engine model, has important dissemination and wide application prospect.
Content of the invention
For overcoming the shortcomings of that special engine model prices present in prior art are expensive and dismounting is inconvenient, the present invention carries
Go out a kind of teaching turbofan/whirlpool spray aero-engine built-up pattern.
The present invention includes low-pressure compressor, core engine, low-pressure turbine, jet pipe, by-pass air duct and trouserss, its mesolow pressure
The architectural feature of mechanism of qi, core engine, low-pressure turbine and jet pipe and annexation are all same as the prior art.As turbofan aviation
During engine mockup, this turbofan aero-engine model is by by-pass air duct, low-pressure compressor, core engine, low-pressure turbine and jet pipe
Composition, and by-pass air duct is arranged on the axle head of low-pressure compressor axle；During as whirlpool spray aero-engine teaching mode, this whirlpool spray boat
Empty electromotor teaching mode is made up of trouserss, low-pressure compressor, core engine, low-pressure turbine and jet pipe, and trouserss peace
It is contained in the axle head of low-pressure compressor axle.
Described by-pass air duct includes big fan trouserss, big duct shell leading portion, multiple big ducted fan movable vane piece, big duct
Fan stator blade, big duct shell back segment and big duct inner housing.Wherein, one end of each big ducted fan movable vane piece is uniform simultaneously
It is fixed on the external peripheral surface of big fan trouserss, the other end is free end.Big duct shell back segment and big duct inner shell body phase
Mutually nested and coaxial, one end of each big ducted fan stator blade is uniformly arranged on big duct inner housing by way of grafting
External peripheral surface, will be uniform for the other end of described each big ducted fan stator blade and be fixed in big duct shell back segment
Circumferential surface.The end face of described big duct shell back segment one end end face with big duct shell leading portion one end by way of grafting
Connect.
Described big duct shell back segment and big duct inner housing are 2/3 round thin-wall barrel.
Described big duct inner housing is combined by three lobes, and the circumferential lengths of every lobe big duct inner housing are according to being pacified
The quantity of the big ducted fan stator blade of dress determines, to meet this big ducted fan stator blade in the big duct of 2/3 circle
Being uniformly distributed on housing.
Described big duct shell back segment is divided into eight lobes, every lobe by-pass air duct housing inner surface all by being welded with
One big ducted fan stator blade.
The front end of described big fan trouserss is conventional cone-shaped hood, and rear end is the construction section of big ducted fan movable vane piece.
Being evenly equipped with many sliver transvers sections in the external peripheral surface of the construction section of this big fan movable vane piece is swallow-tail form blade slot, and this leaf
The construction section of piece slot insertion big fan movable vane piece.
The present invention is a kind of teaching with multifunction combined aero-engine model, by common part in aero-engine
Respectively with different unit construction in variety classes aero-engine, to form different types of aero-engine model,
It is easy to student all kinds engine structure is formed comprehensively recognize deeply, effectively improve the effect of experimental teaching expansible
Experiment content, reduces labor intensity, and reduces experimental cost.
Advantages of the present invention shows as：
1. overcome the simple many drawbacks brought using actual engine, small volume, light weight, be easy to carry, no
Limited by site space, convenient use in classroom, imparted knowledge to students.
2. engine mockup multifunction is used in teaching, by polymorphic type teaching engine mockup integration, can be according to religion
Learn the difference of content, combination forms dissimilar electromotor, intuitively realistically reflection engine interior mainly constructs, and simulation is started
Machine work process, facilitates course teaching as much as possible, and range is more extensive, more effectively saves expense, improves model
Valency ratio.
3. compared to existing teaching engine mockup, price is more cheap, only the ten of available engine model prices
/ mono- about, economy is more preferable, it is possible to achieve large-area popularization and application.
Brief description
Fig. 1 is the structural representation of big Bypass Ratio Turbofan Engine, wherein：1a is front view, and 1b is the left view of 1a, 1c
It is axonometric drawing.
Fig. 2 is the structural representation of turbojet engine, wherein：2a is front view, and 2b is the left view of 2a, and 2c is that axle is surveyed
Figure.
Fig. 3 is the structural representation of big Bypass Ratio Turbofan Engine by-pass air duct, wherein：3a is axonometric drawing, and 3b is front view,
3c is the left view of 3b, and 3d is the aminoacyl site enlarged drawing in 3b.
Fig. 4 is the structural representation of big duct shell leading portion in big Bypass Ratio Turbofan Engine by-pass air duct, wherein：4a is main
View, 4b is axonometric drawing.
Fig. 5 is the structural representation of a lobe big duct inner housing in big Bypass Ratio Turbofan Engine by-pass air duct, wherein：5a is
Axonometric drawing, 5b is side view.
Fig. 6 is a big ducted fan stator blade and a lobe big duct shell in big Bypass Ratio Turbofan Engine by-pass air duct
The cooperation schematic diagram of back segment, wherein 6a are axonometric drawings, and 6b is sectional drawing.
Fig. 7 is the structural representation of big fan trouserss in big Bypass Ratio Turbofan Engine by-pass air duct, wherein：7a is main view
Figure, 7b is right view, and 7c is axonometric drawing.
Fig. 8 is the structural representation of trouserss, wherein：8a is axonometric drawing, and 8b is the sectional view of 8a.
Fig. 9 is the structural representation of jet pipe, wherein：9a is axonometric drawing, and 9b is the sectional view of 9a.
In figure：
1. by-pass air duct；2. low-pressure compressor；3. core engine；4. low-pressure turbine；5. jet pipe；6. trouserss；7. big duct
Shell leading portion；8. big duct shell back segment；9. big ducted fan movable vane piece；10. big duct inner housing；11. big ducted fans are quiet
Blades；12. big fan trouserss.
Specific embodiment
The present embodiment is a kind of teaching turbofan/whirlpool spray aero-engine built-up pattern, described turbofan aero-engine
Teaching mode is big Bypass Ratio Turbofan Engine teaching mode.
The present embodiment improves to big Bypass Ratio Turbofan Engine teaching mode and obtains.
Described big Bypass Ratio Turbofan Engine teaching mode includes by-pass air duct 1, low-pressure compressor 2, core engine 3, low pressure whirlpool
Wheel 4 and jet pipe 5.By-pass air duct 1, low-pressure compressor 2, core engine 3, low pressure in described big Bypass Ratio Turbofan Engine teaching mode
The architectural feature of turbine 4 and jet pipe 5 and connected mode all using prior art, with big Bypass Ratio Turbofan Engine material object phase
With.By-pass air duct 1 is located at the axle front end of low-pressure compressor 2.
Described whirlpool spray aero-engine teaching mode includes low-pressure compressor 2, core engine 3, low-pressure turbine 4, jet pipe 5 and
Trouserss 6, and aero-engine teaching mode mesolow compressor 2, core engine 3, low-pressure turbine 4 and jet pipe 5 are sprayed in whirlpool
Architectural feature and annexation all with described Bypass Ratio Turbofan Engine teaching mode in low-pressure compressor 2, core engine 3, low
Pressure turbine 4 is identical with annexation with the architectural feature of jet pipe 5.Described trouserss 6 are located at whirlpool spray aero-engine teaching mould
Type front end is simultaneously arranged on the axle front end of low-pressure compressor axle；Jet pipe 5 is located at whirlpool and sprays aero-engine teaching mode rear end, and with
Low-pressure turbine 4 connects.
In described big Bypass Ratio Turbofan Engine teaching mode and whirlpool spray aero-engine teaching mode, both are common
Part includes low-pressure compressor 2, core engine 3, low-pressure turbine 4 and jet pipe 5；Both include big bypass ratio turbofan by different parts
Trouserss 6 in by-pass air duct 1 in electromotor teaching mode, and whirlpool spray aero-engine teaching mode.
The present embodiment with whirlpool spray aero-engine teaching mode in trouserss 6 by big Bypass Ratio Turbofan Engine impart knowledge to students mould
By-pass air duct 1 in type is replaced, even if changing into spray aero-engine teaching mode in whirlpool in whirlpool spray aero-engine teaching mode, real
The combination of aero-engine model is sprayed in existing turbofan/whirlpool.
For achieving the above object, the present embodiment takes following technical measures.
Described big Bypass Ratio Turbofan Engine teaching mode by-pass air duct 1 is circular, including big fan trouserss 12, big culvert
In road shell leading portion 7, big ducted fan movable vane piece 9, big ducted fan stator blade 11, big duct shell back segment 8 and big duct
Housing 10.Wherein, one end of 8 big ducted fan movable vane pieces 9 is uniform and external peripheral surface that be fixed on big fan trouserss 12,
The other end is free end.Big duct shell back segment 8 and big duct inner housing 10 are as multiple big ducted fan stator blades 11
Carrier is thin wall circular, in order to clearly show the internal structure of this by-pass air duct 1, plays the effect of teaching mode, this reality
Apply example to cut open the circumference of described big duct shell back segment 8 and big duct inner housing 10 except 1/3 circumference respectively, and by each big duct wind
One end of fan stator blade 11 is uniformly arranged on the external peripheral surface of the big duct inner housing 10 of 2/3 circle by way of grafting,
Inner circle by big duct shell back segment 8 that is uniform for the other end of described each big ducted fan stator blade 11 and being fixed on 2/3 circle
Perimeter surface.In the present embodiment, the quantity of big ducted fan stator blade 11 is 8.The end of described big duct shell back segment 8 one end
Face is connected with the end face of big duct shell leading portion 7 one end by way of grafting.
For ease of changing dismounting during part, described big duct shell back segment 8 and big duct inner housing 10 are all using combination
Formula, described big duct inner housing 10 is divided into three lobes, and the circumferential lengths of every lobe big duct inner housing 10 are according to being installed
Big ducted fan stator blade 11 quantity determine, with meet this big ducted fan stator blade 11 2/3 circle big duct
Being uniformly distributed on inner housing 10.Big duct shell back segment 8 is divided into eight lobes, all passes through in the inner surface of every lobe by-pass air duct housing
It is welded with a big ducted fan stator blade 11.
Big duct shell leading portion 7 one end end face in described by-pass air duct 1 has annular slot, in big duct shell back segment 8
One end end face has annular grafting block, by the cooperation of described annular slot and annular grafting block, realize big duct shell back segment 8 with
The quick connection of big duct shell leading portion 7.
Described big fan trouserss 12 are revolving body, and its front end is conventional cone-shaped hood, and rear end is big ducted fan movable vane
The construction section of piece 9.In order to conveniently install each big fan movable vane piece, in the construction section of described big fan movable vane piece
External peripheral surface is evenly equipped with a plurality of blade slot, and the cross section of described blade slot is swallow-tail form, and this blade slot insertion
The construction section of big fan movable vane piece, when installing big ducted fan movable vane piece 9, the dovetail shaped inserted block of root of blade is inserted trouserss
On slot in, you can realize the Fast Installation of fan rotor blade.Installation in described big fan trouserss big fan movable vane piece
The end face center of section has the axis hole being connected with the low-pressure compressor 2 in big Bypass Ratio Turbofan Engine teaching mode, in high axis hole
Keyway is had on wall, big fan trouserss 12 are scheduled on the axle of described low-pressure compressor 2 by keying.
Described big ducted fan movable vane piece 9 adopts prior art.This big ducted fan movable vane piece blade profile parameters：
Established angle is 12.6 °
The a height of 200mm of leaf
Blade profile angle of bend is 73 °
Blade profile toe angle is：53.25°
Blade profile trailing edge angle is 19.75 °
Chord length is 40.71mm
Maximum defluxion is 5.10mm
Described trouserss 6 are revolving body, for conventional cone-shaped hood.Have dynamic with whirlpool eruption in the end face center of described trouserss
The axis hole that machine teaching mode mesolow compressor 2 connects, has keyway on high axis hole wall, trouserss 6 is scheduled on institute by keying
State on the axle of low-pressure compressor 2.
By the by-pass air duct 1 in described big Bypass Ratio Turbofan Engine teaching mode, after removing according to described assembly and disassembly methods, will
Trouserss 6 are scheduled on the axle of described low-pressure compressor 2 by keying, and combination forms turbojet engine teaching mode.
Claims (5)
1. a kind of teaching turbofan/whirlpool spray aero-engine built-up pattern, including low-pressure compressor, core engine, low-pressure turbine and
Jet pipe；It is characterized in that, also include by-pass air duct and trouserss；During as turbofan aero-engine model, this turbofan aviation is sent out
Motivation Model is made up of by-pass air duct, low-pressure compressor, core engine, low-pressure turbine and jet pipe, and by-pass air duct is arranged on low pressure
The axle head of compressorshaft；As whirlpool spray aero-engine teaching mode when, this whirlpool spray aero-engine teaching mode by trouserss,
Low-pressure compressor, core engine, low-pressure turbine and jet pipe composition, and trouserss are arranged on the axle head of low-pressure compressor axle；Institute
State by-pass air duct and include big fan trouserss, big duct shell leading portion, multiple big ducted fan movable vane piece, big ducted fan stator leaf
Piece, big duct shell back segment and big duct inner housing；Wherein, one end of each big ducted fan movable vane piece is uniform and is fixed on strong wind
The external peripheral surface of fan trouserss, the other end is free end；Big duct shell back segment is mutually nested with big duct inner housing and same
Axle, one end of each big ducted fan stator blade is uniformly arranged on by way of grafting the cylindrical weekly form of big duct inner housing
Face, by inner circumferential surface that is uniform for the other end of described each big ducted fan stator blade and being fixed on big duct shell back segment；
The end face of described big duct shell back segment one end is connected with the end face of big duct shell leading portion one end by way of grafting.
2. teaching as claimed in claim 1 with turbofan/whirlpool spray aero-engine built-up pattern it is characterised in that described big duct
Shell back segment and big duct inner housing are 2/3 round thin-wall barrel.
3. teaching as claimed in claim 1 with turbofan/whirlpool spray aero-engine built-up pattern it is characterised in that described big duct
Inner housing is combined by three lobes, and the circumferential lengths of every lobe big duct inner housing are according to the big ducted fan stator installed
The quantity of blade determines, to meet this big ducted fan stator blade being uniformly distributed on the big duct inner housing of 2/3 circle.
4. teaching as claimed in claim 1 with turbofan/whirlpool spray aero-engine built-up pattern it is characterised in that described big duct
Shell back segment is divided into eight lobes, every lobe by-pass air duct housing inner surface all by being welded with a big ducted fan stator
Blade.
5. teaching as claimed in claim 1 with turbofan/whirlpool spray aero-engine built-up pattern it is characterised in that described big fan
The front end of trouserss is conventional cone-shaped hood, and rear end is the construction section of big ducted fan movable vane piece；In this big fan movable vane piece
It is swallow-tail form blade slot that the external peripheral surface of construction section is evenly equipped with many sliver transvers sections, and this blade slot insertion strong wind is agitated
The construction section of blade.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410177190.4A CN103971580B (en) | 2014-04-29 | 2014-04-29 | Turbofan/turbojet aero-engine combined model used for teaching |
Applications Claiming Priority (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201410177190.4A CN103971580B (en) | 2014-04-29 | 2014-04-29 | Turbofan/turbojet aero-engine combined model used for teaching |
Publications (2)
| Publication Number | Publication Date |
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| CN103971580A CN103971580A (en) | 2014-08-06 |
| CN103971580B true CN103971580B (en) | 2017-02-08 |
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| CN201410177190.4A Expired - Fee Related CN103971580B (en) | 2014-04-29 | 2014-04-29 | Turbofan/turbojet aero-engine combined model used for teaching |
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Families Citing this family (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN105458648B (en) * | 2015-11-23 | 2018-01-16 | 沈阳黎明航空发动机(集团)有限责任公司 | A kind of aero-engine elongated lumens deep hole method for splitting |
| US11043146B2 (en) * | 2018-08-20 | 2021-06-22 | Raytheon Technologies Corporation | Fan blade refurbishment training device |
| CN112364453B (en) * | 2020-11-12 | 2023-03-14 | 北京理工大学重庆创新中心 | Engine modeling and analyzing method and system |
| CN114708784B (en) * | 2022-04-12 | 2022-12-30 | 西北工业大学 | Aeroengine fan model for teaching and assembling method |
| CN114882784B (en) * | 2022-04-14 | 2023-03-10 | 西北工业大学 | Assembly high-pressure turbine teaching model and method for bearing force by using turbine guider |
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| CN203882531U (en) * | 2014-04-29 | 2014-10-15 | 中国人民解放军空军工程大学 | Aeroengine combined model |
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|---|---|---|---|---|
| US7341652B2 (en) * | 2003-06-20 | 2008-03-11 | Groton Biosytems, Llc | Stationary capillary electrophoresis system |
| CN101624945A (en) * | 2009-08-07 | 2010-01-13 | 陈效刚 | Jet pressing burning splitting ring curled turbine engine |
| WO2011154280A1 (en) * | 2010-06-07 | 2011-12-15 | Eads Deutschland Gmbh | Exhaust gas treatment of gas turbine engines |
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