CN105699044A - Icing tunnel experiment device for air intake duct support plate of aeroengine - Google Patents
Icing tunnel experiment device for air intake duct support plate of aeroengine Download PDFInfo
- Publication number
- CN105699044A CN105699044A CN201610248433.8A CN201610248433A CN105699044A CN 105699044 A CN105699044 A CN 105699044A CN 201610248433 A CN201610248433 A CN 201610248433A CN 105699044 A CN105699044 A CN 105699044A
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- Prior art keywords
- support plate
- air intake
- intake duct
- pipe
- icing
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- G—PHYSICS
- G01—MEASURING; TESTING
- G01M—TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING OF STRUCTURES OR APPARATUS, NOT OTHERWISE PROVIDED FOR
- G01M9/00—Aerodynamic testing; Arrangements in or on wind tunnels
- G01M9/02—Wind tunnels
Abstract
The invention discloses an icing tunnel experiment device for an air intake duct support plate of an aeroengine. The icing tunnel experiment device comprises an icing tunnel experiment cabin, an installation base, a support unit, a first pipeline and a second pipeline, wherein the installation base is detachably connected with the icing tunnel experiment cabin, the support unit is fixed on the installation base, the air intake duct support plate having a cavity with an inlet end and an outlet end is fixed on the support unit, the second pipeline communicates with the inlet end and is used for inputting a thermal medium into the cavity of the air intake duct support plate, and the first pipeline communicates with the outlet end. When an engine is in an environment where icing is likely to occur, a high temperature medium is pumped in the internal cavity of the air intake duct support plate to increase the temperature of the external surface of the air intake duct support plate to prevent icing on the external surface of the air intake duct support plate. When the air intake duct support plate of the engine is frozen, a high temperature medium is pumped in for deicing to prevent the engine performance from being affected due to sharp decreasing of intake air.
Description
Technical field
The present invention relates to the anti-icing experiment device of a kind of aero-engine, the icing mnncl tcst device of especially a kind of aero-engine air intake duct support plate。
Background technology
Flight icing is one of major reason causing security incident in modern flight safety。By the research to a large amount of flight safety accidents in the past, it was shown that at some key position of aircraft, a small amount of icing also can affect the aeroperformance of aircraft, aircraft controllability and stability。For aero-engine, the position being easiest to freeze is air inlet component, and the icing of air inlet component may block engine charge stream, even causes inlet distortion, causes thrust to strongly reduce。If the ice on air inlet component comes off, then it is likely to the rotor blade of fan blade or the compressor clashing into electromotor, thus causing serious mechanical damage, and then causes the damage of electromotor and cause security incident。Therefore, in the development process of contemporary aircraft, icing and the anti-icing research of critical component are essential。Icing tunnel experiment is the important means that research freezes, and all employ icing tunnel and test in substantial amounts of icing research work。
Engine inlets support plate is the position that electromotor is easiest to freeze, so the anti-icing research work of air intake duct support plate is extremely important。And icing tunnel experiment is one of important means of icing research, therefore it is necessary to provide a kind of device that air intake duct support plate carries out icing tunnel experiment。
Summary of the invention
It is an object of the invention to provide the icing mnncl tcst device of a kind of aero-engine air intake duct support plate, to study the anti-icing of air intake duct support plate and ice condition。
In order to achieve the above object, the invention provides the icing mnncl tcst device of a kind of aero-engine air intake duct support plate, for air intake duct support plate is carried out icing mnncl tcst, including icing tunnel Laboratory Module with for fixing the support plate stuck-module of air intake duct support plate, described support plate stuck-module includes installation chassis, support unit, first pipeline and second pipe, described installation chassis and icing tunnel Laboratory Module removably connect, described support unit is fixed on installation chassis, described air intake duct support plate is fixed on support unit, described air intake duct support plate has cavity, described cavity has arrival end and the port of export, described second pipe is connected with described arrival end, for the cavity to described air intake duct support plate inputs thermal medium, described first pipeline is connected with the described port of export。
Further, described installation chassis is discoid。
Further, described installation chassis includes the first disk and the second disk, and described first disk is fixed on the second disk, and described first disk and support unit fix, and described second disk or the first disk removably connect with described icing tunnel Laboratory Module。
Further, described air intake duct support plate includes support plate body, entrance pipe, entrance transition, outlet transition and outlet pipe, described support plate stuck-module also includes the first joint and the second joint, described support plate body has described cavity, the arrival end of described cavity is provided with described entrance transition and entrance pipe, described support plate body is connected with entrance pipe by entrance transition, described second pipe is pipe, described entrance pipe is connected with second pipe by the second joint, the port of export of described cavity is provided with described outlet transition and outlet pipe, described support plate body is connected with outlet pipe also by outlet transition, described first pipeline is pipe, described outlet pipe is connected by the first joint and the first pipeline, thermal medium is successively through described second pipe, second joint, entrance pipe and entrance transition enter in the cavity of support plate body, and through described outlet transition, outlet pipe, first joint and the first pipeline are discharged。
Further, described air intake duct support plate also includes the export orientation section being arranged on described port of export place, for changing the outflow direction of thermal medium, described support plate body passes sequentially through export orientation section, outlet transition is connected with outlet pipe, thermal medium enters through described second pipe, the second joint, entrance pipe and entrance transition in the cavity of support plate body successively, and discharges through described export orientation section, outlet transition, outlet pipe, the first joint and the first pipeline successively。
Further, described support unit includes support plate locating piece and support plate bracing frame, and described support plate locating piece is fixed on described support plate bracing frame, and is also fixed on described outlet transition or outlet pipe, and described support plate bracing frame is fixed on described installation chassis。
Further, described first pipeline is through described installation chassis, and is connected with described first joint above installation chassis, and described entrance pipe is through described installation chassis, and is connected with described second joint below described installation chassis。
Further, described first joint is L-type quick connector, and described second joint is straight type quick connector。
Further, described thermal medium is steam or deep fat, and when described thermal medium is deep fat, described thermal medium adopts the hot lubricating oil that engine lubrication system provides。
Further, also include dielectric film filter case, for reclaiming the medium discharged through described first pipeline, described icing tunnel Laboratory Module is provided with observation window。
The invention provides the icing mnncl tcst device of a kind of aero-engine air intake duct support plate, can when electromotor be in easy freezing environment, by high-temperature medium is pumped into air intake duct support plate internal cavities, to improve air intake duct support plate hull-skin temperature, thus preventing support plate outer surface from producing icing phenomenon；When engine inlets support plate produces icing phenomenon, icing can also be melted by pumping into high-temperature medium, thus preventing the problem that electromotor affects engine performance because charge flow rate is die-offed。
Accompanying drawing explanation
The axonometric chart of the icing mnncl tcst device that Fig. 1 provides for the embodiment of the present invention；
Air intake duct support plate that Fig. 2 provides for the embodiment of the present invention and the axonometric chart of support plate stuck-module；
Air intake duct support plate that Fig. 3 provides for the embodiment of the present invention and the side view of support plate stuck-module；
The sectional view of the air intake duct support plate that Fig. 4 provides for the embodiment of the present invention。
In figure, 1: icing tunnel Laboratory Module, 2: installation chassis, 21: the first disks, 22: the second disks, 3: air intake duct support plate, 31: support plate body, 32: entrance pipe, 33: entrance transition, 34: export orientation section, 35: outlet transition, 36: outlet pipe, 4: support unit, 41: support plate locating piece, 42: support plate bracing frame, 5: the first joints, 6: the first pipelines, 7: screw, 8: the second joints, 9: second pipe。
Detailed description of the invention
Below in conjunction with schematic diagram, the specific embodiment of the present invention is described in more detail。According to description below and claims, advantages and features of the invention will be apparent from。It should be noted that, accompanying drawing all adopts the form simplified very much and all uses non-ratio accurately, only in order to convenience, the purpose aiding in illustrating the embodiment of the present invention lucidly。
As shown in figures 1-4, present embodiments provide the icing mnncl tcst device of a kind of aero-engine air intake duct support plate, for air intake duct support plate 3 is carried out icing mnncl tcst, including icing tunnel Laboratory Module 1 with for fixing the support plate stuck-module of air intake duct support plate 3, described support plate stuck-module includes installation chassis 2, support unit 4, first joint 5, first pipeline 6, second joint 8 and second pipe 9, described installation chassis 2 removably connects with icing tunnel Laboratory Module 1, described support unit 4 is fixed on installation chassis 2, described air intake duct support plate 3 is fixed on support unit 4, described air intake duct support plate 3 has cavity, described cavity has arrival end and the port of export, described second pipe 9 is connected with described arrival end, for the cavity to described air intake duct support plate 3 inputs thermal medium, described first pipeline 6 is connected with the described port of export。
Further, described installation chassis 2 is discoid。Discoid 1 removably connect with installation chassis 2 with icing tunnel Laboratory Module, drive air intake duct support plate 3 rotation can regulate the air intake duct support plate 3 angle in icing tunnel Laboratory Module 1 by rotating installation chassis 2, this angle is in icing tunnel Laboratory Module ice wind and the angle of air intake duct support plate 3, fixes this installation chassis 2 again adjusting to angle on target。
In the present embodiment, described installation chassis 2 includes the first disk 21 and the second disk 22, described first disk 21 is fixed on the second disk 22, and described first disk 21 fixes with support unit 4, and described second disk 22 or the first disk 21 removably connect with described icing tunnel Laboratory Module 1。This provide two schemes, the first scheme is that the second disk 22 removably connects with icing tunnel Laboratory Module 1, the now size (or title first disk 21 projection on the second disk 22 is positioned at inside the second disk 22, does not overlap with the second disk 22) being sized larger than the first disk 21 of the second disk 22；First scheme is that the first disk 21 removably connects with described icing tunnel Laboratory Module 1, in like manner, the now size being sized larger than the second disk 22 of the first disk 21, also can realize detachable fixing, and can make to regulate by rotating installation chassis 2 angle of air intake duct support plate 3。In the present embodiment, refer to Fig. 2～3, employing is the first scheme。
Described installation chassis 2 can adopt that various ways is detachable with icing tunnel Laboratory Module 1 to be connected, for instance, adopt screw or adopt bolt column and nut, but being not limited to this。In the present embodiment, it adopts that screw 7 is detachable with icing tunnel Laboratory Module 1 to be connected。
Please continue to refer to Fig. 2～4, described air intake duct support plate 3 includes support plate body 31, entrance pipe 32, entrance transition 33, outlet transition 35 and outlet pipe 36, described support plate body 31 has described cavity, the arrival end of described cavity is provided with described entrance transition 33 and entrance pipe 32, described support plate body 31 is connected with entrance pipe 32 by entrance transition 33, described second pipe 9 is pipe, described entrance pipe 32 is connected with second pipe 9 by the second joint 8, the port of export of described cavity is provided with described outlet transition 35 and outlet pipe 36, described support plate body 31 is connected with outlet pipe 36 also by outlet transition 35, described first pipeline 6 is pipe, described outlet pipe 36 is connected with the first pipeline 6 by the first joint 5, thermal medium is successively through described second pipe 9, second joint 8, entrance pipe 32 and entrance transition 33 enter in the cavity of support plate body 31, and through described outlet transition 35, outlet pipe 36, first joint 5 and the first pipeline 6 are discharged。
The structure of inlet porting pipe 32, entrance transition the 33, second joint 8 and second pipe 9 can ensure that high-temperature medium (i.e. thermal medium) smooth delivery of power inside to air intake duct support plate 3, it is possible to prevents from producing the phenomenon of leakage in process of the test。The smooth flow process air intake duct support plate 3 of high-temperature medium after the structure exporting transition 35, outlet pipe the 36, first joint 5 and the first pipeline 6 can ensure that heat exchange is set, it is prevented that export generation leakage phenomenon high-temperature medium process from air intake duct support plate 3。Further, in the present embodiment, described icing mnncl tcst device also includes dielectric film filter case (not shown), for reclaiming the medium discharged through described first pipeline, it is to avoid the thermal medium contaminated environment that the first pipeline 6 is discharged。
In the present embodiment, described air intake duct support plate 3 also includes the export orientation section 34 being arranged on described port of export place, for changing the outflow direction of thermal medium, described support plate body 31 passes sequentially through export orientation section 34, outlet transition 35 is connected with outlet pipe 36, thermal medium enters through described second pipe the 9, second joint 8, entrance pipe 32 and entrance transition 33 in the cavity of support plate body 31 successively, and discharges through described export orientation section 34, outlet transition 35, outlet pipe the 36, first joint 5 and the first pipeline 6 successively。
In the present embodiment, described support unit 4 includes support plate locating piece 41 and support plate bracing frame 42, described support plate locating piece 41 is fixed on described support plate bracing frame 42, and is also fixed on described outlet transition 35 or outlet pipe 36, and described support plate bracing frame 42 is fixed on described installation chassis 2。In the present embodiment, support plate locating piece 41 is fixed on outlet transition 35, it is achieved that fixing air intake duct support plate 3。
Further, described first pipeline 6 is through described installation chassis 2, and is connected with described first joint 5 above installation chassis 2, and described entrance pipe 32 is through described installation chassis 2, and is connected with described second joint 8 below described installation chassis 2。
In the present embodiment, described first joint 5 is L-type quick connector, and described second joint 8 is straight type quick connector, but is not limited to this。
Further, described thermal medium is steam or deep fat。Owing to adopting thermal medium, therefore the first pipeline 6 and second pipe 9 also preferably employ high-temperature resistant pipeline accordingly。When described thermal medium is deep fat, described thermal medium adopts the hot lubricating oil that engine lubrication system provides。Adopt the hot lubricating oil that provides of engine lubrication system to be heated anti-icing, both can reduce the demand to steam, it is to avoid provide steam to air intake duct support plate by compressor, improve the efficiency of compressor, the effect of cooling lubricating oil can also be played simultaneously。
In the present embodiment, described icing tunnel Laboratory Module 1 is provided with observation window, for instance, the icing tunnel Laboratory Module 1 in the present embodiment is the rectangular structure of hollow, sidewall or top is provided with observation window, but is not limited to this。When can observe icing on air intake duct support plate 3 by observation window, from second pipe, input hot lubricating oil again, hot lubricating oil in the cavities with air intake duct support plate 3 heat exchange, improve air intake duct support plate 3 temperature, and then melting icing, the hot lubricating oil after heat exchange is discharged in a dielectric film filter case from the first pipeline 6。
The invention provides the icing mnncl tcst device of a kind of aero-engine air intake duct support plate, can when electromotor be in easy freezing environment, by high-temperature medium is pumped into air intake duct support plate internal cavities, to improve air intake duct support plate hull-skin temperature, thus preventing support plate outer surface from producing icing phenomenon；When engine inlets support plate produces icing phenomenon, icing can also be melted by pumping into high-temperature medium, thus preventing the problem that electromotor affects engine performance because charge flow rate is die-offed。
Above are only the preferred embodiments of the present invention, the present invention is not played any restriction effect。Any person of ordinary skill in the field; without departing from the scope of technical scheme; the technical scheme that the invention discloses and technology contents are made the variations such as any type of equivalent replacement or amendment; all belong to the content without departing from technical scheme, still fall within protection scope of the present invention。
Claims (10)
1. the icing mnncl tcst device of an aero-engine air intake duct support plate, for air intake duct support plate is carried out icing mnncl tcst, it is characterized in that, including icing tunnel Laboratory Module with for fixing the support plate stuck-module of air intake duct support plate, described support plate stuck-module includes installation chassis, support unit, first pipeline and second pipe, described installation chassis and icing tunnel Laboratory Module removably connect, described support unit is fixed on installation chassis, described air intake duct support plate is fixed on support unit, described air intake duct support plate has cavity, described cavity has arrival end and the port of export, described second pipe is connected with described arrival end, for the cavity to described air intake duct support plate inputs thermal medium, described first pipeline is connected with the described port of export。
2. the icing mnncl tcst device of aero-engine air intake duct support plate as claimed in claim 1, it is characterised in that described installation chassis is discoid。
3. the icing mnncl tcst device of aero-engine air intake duct support plate as claimed in claim 1 or 2, it is characterized in that, described installation chassis includes the first disk and the second disk, described first disk is fixed on the second disk, described first disk and support unit fix, and described second disk or the first disk removably connect with described icing tunnel Laboratory Module。
4. the icing mnncl tcst device of aero-engine air intake duct support plate as claimed in claim 1, it is characterized in that, described air intake duct support plate includes support plate body, entrance pipe, entrance transition, outlet transition and outlet pipe, described support plate stuck-module also includes the first joint and the second joint, described support plate body has described cavity, the arrival end of described cavity is provided with described entrance transition and entrance pipe, described support plate body is connected with entrance pipe by entrance transition, described second pipe is pipe, described entrance pipe is connected with second pipe by the second joint, the port of export of described cavity is provided with described outlet transition and outlet pipe, described support plate body is connected with outlet pipe also by outlet transition, described first pipeline is pipe, described outlet pipe is connected by the first joint and the first pipeline, thermal medium is successively through described second pipe, second joint, entrance pipe and entrance transition enter in the cavity of support plate body, and through described outlet transition, outlet pipe, first joint and the first pipeline are discharged。
5. the icing mnncl tcst device of aero-engine air intake duct support plate as claimed in claim 4, it is characterized in that, described air intake duct support plate also includes the export orientation section being arranged on described port of export place, for changing the outflow direction of thermal medium, described support plate body passes sequentially through export orientation section, outlet transition is connected with outlet pipe, thermal medium is successively through described second pipe, second joint, entrance pipe and entrance transition enter in the cavity of support plate body, and successively through described export orientation section, outlet transition, outlet pipe, first joint and the first pipeline are discharged。
6. the icing mnncl tcst device of aero-engine air intake duct support plate as claimed in claim 4, it is characterized in that, described support unit includes support plate locating piece and support plate bracing frame, described support plate locating piece is fixed on described support plate bracing frame, and be also fixed on described outlet transition or outlet pipe, described support plate bracing frame is fixed on described installation chassis。
7. the icing mnncl tcst device of aero-engine air intake duct support plate as claimed in claim 4, it is characterized in that, the described first pipeline described installation chassis of traverse, and be connected with described first joint above installation chassis, described entrance pipe is through described installation chassis, and is connected with described second joint below described installation chassis。
8. the icing mnncl tcst device of aero-engine air intake duct support plate as claimed in claim 7, it is characterised in that described first joint is L-type quick connector, and described second joint is straight type quick connector。
9. the icing mnncl tcst device of aero-engine air intake duct support plate as claimed in claim 1, it is characterised in that described thermal medium is steam or deep fat, when described thermal medium is deep fat, described thermal medium adopts the hot lubricating oil that engine lubrication system provides。
10. the icing mnncl tcst device of aero-engine air intake duct support plate as claimed in claim 1, it is characterised in that also include dielectric film filter case, for reclaiming the medium discharged through described first pipeline, described icing tunnel Laboratory Module is provided with observation window。
Priority Applications (1)
| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610248433.8A CN105699044B (en) | 2016-04-20 | 2016-04-20 | The icing mnncl tcst device of aero-engine air intake duct supporting plate |
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| Application Number | Priority Date | Filing Date | Title |
|---|---|---|---|
| CN201610248433.8A CN105699044B (en) | 2016-04-20 | 2016-04-20 | The icing mnncl tcst device of aero-engine air intake duct supporting plate |
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| CN105699044A true CN105699044A (en) | 2016-06-22 |
| CN105699044B CN105699044B (en) | 2019-03-26 |
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| CN201610248433.8A Expired - Fee Related CN105699044B (en) | 2016-04-20 | 2016-04-20 | The icing mnncl tcst device of aero-engine air intake duct supporting plate |
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Cited By (6)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106644354A (en) * | 2017-02-20 | 2017-05-10 | 西北工业大学 | Miniature wing surface electric heating deicing system icing wind tunnel test device |
| CN106644360A (en) * | 2016-12-08 | 2017-05-10 | 西北工业大学 | Test piece clamping device for ice wind tunnel environmental test chamber |
| CN109060295A (en) * | 2018-08-29 | 2018-12-21 | 南京航空航天大学 | Experimental provision and method occur for multi-functional moisture film |
| CN113047960A (en) * | 2021-03-22 | 2021-06-29 | 南京航空航天大学 | Novel aeroengine backward flow formula lubricating oil anti-icing extension board inner chamber structure |
| CN113639988A (en) * | 2021-07-12 | 2021-11-12 | 江铃汽车股份有限公司 | Throttle valve ice breaking verification method |
| CN114252271A (en) * | 2021-12-09 | 2022-03-29 | 中国船舶重工集团公司第七0三研究所 | High-temperature environment simulation test cabin |
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Cited By (7)
| Publication number | Priority date | Publication date | Assignee | Title |
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| CN106644360A (en) * | 2016-12-08 | 2017-05-10 | 西北工业大学 | Test piece clamping device for ice wind tunnel environmental test chamber |
| CN106644354A (en) * | 2017-02-20 | 2017-05-10 | 西北工业大学 | Miniature wing surface electric heating deicing system icing wind tunnel test device |
| CN106644354B (en) * | 2017-02-20 | 2019-02-05 | 西北工业大学 | A kind of small-sized aerofoil electrical heating deicing system icing mnncl tcst device |
| CN109060295A (en) * | 2018-08-29 | 2018-12-21 | 南京航空航天大学 | Experimental provision and method occur for multi-functional moisture film |
| CN113047960A (en) * | 2021-03-22 | 2021-06-29 | 南京航空航天大学 | Novel aeroengine backward flow formula lubricating oil anti-icing extension board inner chamber structure |
| CN113639988A (en) * | 2021-07-12 | 2021-11-12 | 江铃汽车股份有限公司 | Throttle valve ice breaking verification method |
| CN114252271A (en) * | 2021-12-09 | 2022-03-29 | 中国船舶重工集团公司第七0三研究所 | High-temperature environment simulation test cabin |
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| CN105699044B (en) | 2019-03-26 |
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