CN203882531U - Aeroengine combined model - Google Patents
Aeroengine combined model Download PDFInfo
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- CN203882531U CN203882531U CN201420214782.4U CN201420214782U CN203882531U CN 203882531 U CN203882531 U CN 203882531U CN 201420214782 U CN201420214782 U CN 201420214782U CN 203882531 U CN203882531 U CN 203882531U
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- pressure compressor
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- 230000000694 effects Effects 0.000 abstract description 4
- TVEXGJYMHHTVKP-UHFFFAOYSA-N 6-oxabicyclo[3.2.1]oct-3-en-7-one Chemical compound C1C2C(=O)OC1C=CC2 TVEXGJYMHHTVKP-UHFFFAOYSA-N 0.000 description 2
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- 238000005516 engineering process Methods 0.000 description 1
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Abstract
The utility model provides an aeroengine combined model which comprises a low pressure compressor, a core machine, a low pressure turbine, a tail nozzle, an outer duct and a fairing. As a turbofan aeroengine model, the turbofan aeroengine model is formed by the outer duct, the low pressure compressor, the core machine, the low pressure turbine and the tail nozzle, and the outer duct is installed at the shaft end of a low pressure compressor shaft. As a turbojet aeroengine teaching model, the turbojet aeroengine teaching model is formed by the fairing, the low pressure compressor, the core machine, the low pressure turbine and the tail nozzle, and the fairing is installed at the shaft end of the low pressure compressor shaft. According to the aeroengine combined model, the common components in an aeroengine and different components in different types of aeroengines are combined to form different types of aeroengine models, thus students can deeply and comprehensively understand various types of engine structures, the effect of experiment teaching is effectively improved and the experiment content can be expanded, the labor intensity is reduced, and the experiment cost is reduced.
Description
Technical field
The invention belongs to a kind of aeromotor model, particularly relate to a kind of turbofan for teaching/whirlpool spray aeromotor built-up pattern.
Background technology
At present, existing teaching aeromotor model, is mainly to utilize serviceable life overdue aeromotor through dissecing processing and obtaining, or the teaching engine mockup of being manufactured by specialized company.
Existing teaching mainly contains following shortcoming with engine mockup:
1. existing teaching is all to manufacture for the aeromotor research of specific model or type with engine mockup, function singleness, only can carry out analog demenstration to the engine of a model engine or a type, function is restricted, and cannot make student comprehensively be familiar with whole aeromotor family System forming system.
To the engine in longevity as teaching mode, bulky, be not easy to movement, limited amount, obtain difficulty, and can only be in laboratory etc. particular place show, cannot be placed in classroom uses, can not synchronize and carry out with teaching process, be difficult to closely cooperate with the content of courses, to helping student deepen understanding and understand the content of courses and can not play good effect.
Although the teaching that 3.You specialized company manufactures is high, expensive by engine mockup emulation degree, in general universities and colleges, cannot realizes on a large scale and promoting.This class model mostly is mock-up model, and same existence is difficult to dismounting, is not easy to mobilely, and student can not be at any time, with hall, observe the drawbacks such as engine, is unfavorable for that student grasps the inner structure of engine as soon as possible, and teaching efficiency is subject to impact to a certain extent.
Therefore, develop a kind of diverse in function, highly versatile, is easy to dismounting, is easy to carry, cheap, is not subject to the multifunction combined aeromotor model for teaching of place restriction, has important dissemination and wide application prospect.
Summary of the invention
For overcoming the deficiency of the expensive and dismounting inconvenience of the special engine model existing in prior art, the present invention proposes a kind of aeromotor built-up pattern.
The present invention includes low-pressure compressor, core engine, low-pressure turbine, jet pipe, by-pass air duct and radome fairing, wherein: during as turbofan aeromotor model, this turbofan aeromotor model is comprised of by-pass air duct, low-pressure compressor, core engine, low-pressure turbine and jet pipe, and by-pass air duct is arranged on the axle head of low-pressure compressor axle; During as whirlpool spray aeromotor teaching mode, this whirlpool spray aeromotor teaching mode is comprised of radome fairing, low-pressure compressor, core engine, low-pressure turbine and jet pipe, and radome fairing is arranged on the axle head of low-pressure compressor axle.
Described by-pass air duct comprises big fan radome fairing, large duct shell leading portion, a plurality of large ducted fan moving vane, large ducted fan stator blade, large duct shell back segment and large duct inner housing.Wherein, one end of each large ducted fan moving vane is uniform and be fixed on the external peripheral surface of big fan radome fairing, and the other end is free end.Large duct shell back segment is mutually nested and coaxial with large duct inner housing, by the uniform external peripheral surface that is arranged on large duct inner housing by the mode of pegging graft in one end of each large ducted fan stator blade, the other end of described each large ducted fan stator blade is uniform and be fixed on the inner circumferential surface of large duct shell back segment.The end face of described large duct shell back segment one end is connected with the end face of large duct shell leading portion one end by the mode of pegging graft.
Described large duct shell back segment and large duct inner housing are the thin-wall barrel of 2/3 circle.
Described large duct inner housing is combined by three lobes, and the circumferential lengths of the large duct inner housing of every lobe is determined according to the quantity of installed large ducted fan stator blade, to meet this large ducted fan stator blade being uniformly distributed on the large duct inner housing of 2/3 circle.
Described large duct shell back segment is divided into eight lobes, at the inside surface of every lobe by-pass air duct housing all by being welded with a large ducted fan stator blade.
The front end of described big fan radome fairing is conventional cone-shaped hood, and rear end is the construction section of large ducted fan moving vane.At the external peripheral surface of the construction section of this big fan moving vane, being evenly equipped with many sliver transvers sections is swallow-tail form blade slot, and this blade slot connects the construction section of big fan moving vane.
The present invention is multifunction combined aeromotor model for a kind of teaching, by parts common in aeromotor respectively with variety classes aeromotor in different component combination, to form dissimilar aeromotor model, be convenient to student all kinds engine structure is formed to deep comprehensively understanding, effectively improve experimental teaching effect and can way of extensive experimentation content, reduce labor intensity, reduce experimental cost.
Advantage of the present invention shows as:
1. overcome many drawbacks of bringing of simple use actual engine, volume is little, quality is light, be easy to carry, and not limited by site space, conveniently in classroom, uses, and imparts knowledge to students.
2. impart knowledge to students and use engine mockup multifunction, polymorphic type teaching is integrated with engine mockup, can be according to the difference of the content of courses, be combined to form dissimilar engine, intuitively reflect realistically that engine interior mainly constructs, the simulated engine course of work, facilitate as much as possible course teaching, usable range is more extensive, and more effectively cost saving improves model cost performance.
3. compared to existing teaching engine mockup, price is more cheap, is only 1/10th left and right of available engine model price, and economy is better, can realize large-area applying.
Accompanying drawing explanation
Fig. 1 is the structural representation of large Bypass Ratio Turbofan Engine, and wherein: 1a is front view, 1b is the left view of 1a, and 1c is axonometric drawing.
Fig. 2 is the structural representation of turbojet engine, and wherein: 2a is front view, 2b is the left view of 2a, and 2c is axonometric drawing.
Fig. 3 is the structural representation of large Bypass Ratio Turbofan Engine by-pass air duct, and wherein: 3a is axonometric drawing, 3b is front view, and 3c is the left view of 3b, and 3d is front view, and 3e is the A position enlarged drawing in 3b.
Fig. 4 is the structural representation of large duct shell leading portion in large Bypass Ratio Turbofan Engine by-pass air duct, and wherein: 4a is front view, 4b is axonometric drawing.
Fig. 5 is the structural representation of the large duct inner housing of a lobe in large Bypass Ratio Turbofan Engine by-pass air duct, and wherein: 5a is axonometric drawing, 5b is side view.
Fig. 6 is the schematic diagram that coordinates of large ducted fan stator blade and the large duct shell of lobe back segment in large Bypass Ratio Turbofan Engine by-pass air duct, and wherein 6a is axonometric drawing, and 6b is sectional drawing.
Fig. 7 is the structural representation of big fan radome fairing in large Bypass Ratio Turbofan Engine by-pass air duct, and wherein: 7a is front view, 7b is right view, and 7c is axonometric drawing.
Fig. 8 is the structural representation of radome fairing, and wherein: 8a is axonometric drawing, 8b is the cut-open view of 8a.
Fig. 9 is the structural representation of jet pipe, and wherein: 9a is axonometric drawing, 9b is the cut-open 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. radome fairing; 7. large duct shell leading portion; 8. large duct shell back segment; 9. large ducted fan moving vane; 10. large duct inner housing; 11. large ducted fan stator blades; 12. big fan radome fairings.
Embodiment
The present embodiment is a kind of turbofan for teaching/whirlpool spray aeromotor built-up pattern, and described turbofan aeromotor teaching mode is large Bypass Ratio Turbofan Engine teaching mode.
The present embodiment improves and obtains large Bypass Ratio Turbofan Engine teaching mode.
Described large Bypass Ratio Turbofan Engine teaching mode comprises by-pass air duct 1, low-pressure compressor 2, core engine 3, low-pressure turbine 4 and jet pipe 5.In described large Bypass Ratio Turbofan Engine teaching mode, architectural feature and the connected mode of by-pass air duct 1, low-pressure compressor 2, core engine 3, low-pressure turbine 4 and jet pipe 5 all adopt prior art, identical with large Bypass Ratio Turbofan Engine material object.By-pass air duct 1 is positioned at the axle front end of low-pressure compressor 2.
Described whirlpool spray aeromotor teaching mode comprises low-pressure compressor 2, core engine 3, low-pressure turbine 4, jet pipe 5 and radome fairing 6, and the architectural feature of whirlpool spray aeromotor teaching mode mesolow pneumatic plant 2, core engine 3, low-pressure turbine 4 and jet pipe 5 and annexation are all identical with architectural feature and the annexation of low-pressure compressor 2, core engine 3, low-pressure turbine 4 and jet pipe 5 in described Bypass Ratio Turbofan Engine teaching mode.Described radome fairing 6 is positioned at whirlpool spray aeromotor teaching mode front end and is arranged on the axle front end of low-pressure compressor axle; Jet pipe 5 is positioned at spray aeromotor teaching mode rear end, whirlpool, and is connected with low-pressure turbine 4.
In described large Bypass Ratio Turbofan Engine teaching mode and whirlpool spray aeromotor teaching mode, both common parts comprise low-pressure compressor 2, core engine 3, low-pressure turbine 4 and jet pipe 5; Both different parts comprise the by-pass air duct 1 in large Bypass Ratio Turbofan Engine teaching mode, and the radome fairing 6 in whirlpool spray aeromotor teaching mode.
The present embodiment is replaced the by-pass air duct in large Bypass Ratio Turbofan Engine teaching mode 1 with the radome fairing 6 in whirlpool spray aeromotor teaching mode, even if change into whirlpool spray aeromotor teaching mode in whirlpool spray aeromotor teaching mode, realize the combination of turbofan/whirlpool spray aeromotor model.
For achieving the above object, the present embodiment has been taked following technical measures.
Described large Bypass Ratio Turbofan Engine teaching mode by-pass air duct 1 is circular, comprises big fan radome fairing 12, large duct shell leading portion 7, large ducted fan moving vane 9, large ducted fan stator blade 11, large duct shell back segment 8 and large duct inner housing 10.Wherein, one end of 8 large ducted fan moving vanes 9 is uniform and be fixed on the external peripheral surface of big fan radome fairing 12, and the other end is free end.Large duct shell back segment 8 and large duct inner housing 10 are thin wall circular as the carrier of a plurality of large ducted fan stator blades 11, in order clearly to show the inner structure of this by-pass air duct 1, play the effect of teaching mode, the present embodiment cuts open respectively the circumference of described large duct shell back segment 8 and large duct inner housing 10 except 1/3 circumference, and by the uniform external peripheral surface that is arranged on the large duct inner housing 10 of 2/3 circle by the mode of pegging graft in one end of each large ducted fan stator blade 11, the other end of described each large ducted fan stator blade 11 is uniform and be fixed on the inner circumferential surface of large duct shell back segment 8 of 2/3 circle.In the present embodiment, the quantity of large ducted fan stator blade 11 is 8.The end face of described large duct shell back segment 8 one end is connected with the end face of large duct shell leading portion 7 one end by the mode of pegging graft.
Dismounting during for ease of replacing parts, described large duct shell back segment 8 and large duct inner housing 10 all adopt combined type, described large duct inner housing 10 is divided into three lobes, and the circumferential lengths of the large duct inner housing 10 of every lobe is determined according to the quantity of installed large ducted fan stator blade 11, to meet this large ducted fan stator blade 11 being uniformly distributed on the large duct inner housing 10 of 2/3 circle.Large duct shell back segment 8 is divided into eight lobes, at the inside surface of every lobe by-pass air duct housing all by being welded with a large ducted fan stator blade 11.
Large duct shell leading portion 7 one end end faces in described by-pass air duct 1 have annular slot, at large duct shell back segment 8 one end end faces, there is annular grafting piece, by the cooperation of described annular slot and annular grafting piece, realize quick connection of large duct shell back segment 8 and large duct shell leading portion 7.
Described big fan radome fairing 12 is solid of revolution, and its front end is conventional cone-shaped hood, and rear end is the construction section of large ducted fan moving vane 9.For each big fan moving vane can be conveniently installed, external peripheral surface at the construction section of described big fan moving vane is evenly equipped with many blade slots, the xsect of described blade slot is swallow-tail form, and this blade slot connects the construction section of big fan moving vane, when large ducted fan moving vane 9 is installed, the dovetail shaped inserted block of root of blade is inserted in the slot on radome fairing, can realize the Fast Installation of fan moving vane.At the end face center of the construction section of described big fan radome fairing big fan moving vane, there is the axis hole being connected with low-pressure compressor 2 in large Bypass Ratio Turbofan Engine teaching mode, on high axis hole wall, there is keyway, big fan radome fairing 12 is fixed on the axle of described low-pressure compressor 2 by key.
Described large ducted fan moving vane 9 adopts prior art.This large ducted fan moving vane blade profile parameters:
Established angle is 12.6 °
Leaf height is 200mm
Blade profile bending angle 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 radome fairing 6 is solid of revolution, is conventional cone-shaped hood.At the end face center of described radome fairing, there is the axis hole being connected with turbojet engine teaching mode mesolow pneumatic plant 2, on high axis hole wall, have keyway, radome fairing 6 is fixed on the axle of described low-pressure compressor 2 by key.
By the by-pass air duct 1 in described large Bypass Ratio Turbofan Engine teaching mode, after removing according to described assembly and disassembly methods, radome fairing 6 is fixed on the axle of described low-pressure compressor 2 by key, be combined to form turbojet engine teaching mode.
Claims (6)
1. an aeromotor built-up pattern, it is characterized in that, comprise low-pressure compressor, core engine, low-pressure turbine, jet pipe, by-pass air duct and radome fairing, wherein: during as turbofan aeromotor model, this turbofan aeromotor model is comprised of by-pass air duct, low-pressure compressor, core engine, low-pressure turbine and jet pipe, and by-pass air duct is arranged on the axle head of low-pressure compressor axle; During as whirlpool spray aeromotor teaching mode, this whirlpool spray aeromotor teaching mode is comprised of radome fairing, low-pressure compressor, core engine, low-pressure turbine and jet pipe, and radome fairing is arranged on the axle head of low-pressure compressor axle.
2. aeromotor built-up pattern as claimed in claim 1, it is characterized in that, described by-pass air duct comprises big fan radome fairing, large duct shell leading portion, a plurality of large ducted fan moving vane, large ducted fan stator blade, large duct shell back segment and large duct inner housing; Wherein, one end of each large ducted fan moving vane is uniform and be fixed on the external peripheral surface of big fan radome fairing, and the other end is free end; Large duct shell back segment is mutually nested and coaxial with large duct inner housing, by the uniform external peripheral surface that is arranged on large duct inner housing by the mode of pegging graft in one end of each large ducted fan stator blade, the other end of described each large ducted fan stator blade is uniform and be fixed on the inner circumferential surface of large duct shell back segment; The end face of described large duct shell back segment one end is connected with the end face of large duct shell leading portion one end by the mode of pegging graft.
3. aeromotor built-up pattern as claimed in claim 2, is characterized in that, described large duct shell back segment and large duct inner housing are the thin-wall barrel of 2/3 circle.
4. aeromotor built-up pattern as claimed in claim 2, it is characterized in that, described large duct inner housing is combined by three lobes, and the circumferential lengths of the large duct inner housing of every lobe is determined according to the quantity of installed large ducted fan stator blade, to meet this large ducted fan stator blade being uniformly distributed on the large duct inner housing of 2/3 circle.
5. aeromotor built-up pattern as claimed in claim 2, is characterized in that, described large duct shell back segment is divided into eight lobes, at the inside surface of every lobe by-pass air duct housing all by being welded with a large ducted fan stator blade.
6. aeromotor built-up pattern as claimed in claim 1, is characterized in that, the front end of described big fan radome fairing is conventional cone-shaped hood, and rear end is the construction section of large ducted fan moving vane; At the external peripheral surface of the construction section of this big fan moving vane, being evenly equipped with many sliver transvers sections is swallow-tail form blade slot, and this blade slot connects the construction section of big fan moving vane.
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420214782.4U CN203882531U (en) | 2014-04-29 | 2014-04-29 | Aeroengine combined model |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201420214782.4U CN203882531U (en) | 2014-04-29 | 2014-04-29 | Aeroengine combined model |
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| CN203882531U true CN203882531U (en) | 2014-10-15 |
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| CN201420214782.4U Expired - Lifetime CN203882531U (en) | 2014-04-29 | 2014-04-29 | Aeroengine combined model |
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Cited By (4)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103971580A (en) * | 2014-04-29 | 2014-08-06 | 中国人民解放军空军工程大学 | Turbofan/turbojet aero-engine combined model used for teaching |
| CN106205346A (en) * | 2016-08-03 | 2016-12-07 | 上海交通大学 | There is the implementation method of the axial-flow compressor of three groups of repacking casings |
| CN106952520A (en) * | 2017-05-26 | 2017-07-14 | 中国人民解放军空军工程大学 | Mutual-style experiments tutoring system based on WLAN and intelligent mobile terminal |
| CN110310523A (en) * | 2019-05-28 | 2019-10-08 | 云南东方飞行培训有限公司 | Teaching method, system electronic device and storage medium based on mixed reality |
-
2014
- 2014-04-29 CN CN201420214782.4U patent/CN203882531U/en not_active Expired - Lifetime
Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN103971580A (en) * | 2014-04-29 | 2014-08-06 | 中国人民解放军空军工程大学 | Turbofan/turbojet aero-engine combined model used for teaching |
| CN106205346A (en) * | 2016-08-03 | 2016-12-07 | 上海交通大学 | There is the implementation method of the axial-flow compressor of three groups of repacking casings |
| CN106205346B (en) * | 2016-08-03 | 2019-01-15 | 上海交通大学 | The implementation method of axial-flow compressor with three groups of repacking casings |
| CN106952520A (en) * | 2017-05-26 | 2017-07-14 | 中国人民解放军空军工程大学 | Mutual-style experiments tutoring system based on WLAN and intelligent mobile terminal |
| CN110310523A (en) * | 2019-05-28 | 2019-10-08 | 云南东方飞行培训有限公司 | Teaching method, system electronic device and storage medium based on mixed reality |
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