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CN102853987A - Tester for researching ice accretion and ice prevention of aero-engine cowling in icing wind tunnel - Google Patents

Tester for researching ice accretion and ice prevention of aero-engine cowling in icing wind tunnel Download PDF

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Publication number
CN102853987A
CN102853987A CN 201210358709 CN201210358709A CN102853987A CN 102853987 A CN102853987 A CN 102853987A CN 201210358709 CN201210358709 CN 201210358709 CN 201210358709 A CN201210358709 A CN 201210358709A CN 102853987 A CN102853987 A CN 102853987A
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icing
tunnel
ice
wind
shaft
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CN 201210358709
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Chinese (zh)
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吉洪湖
胡娅萍
王健
陈宁立
朱强华
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南京航空航天大学
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Abstract

The invention relates to a tester for researching ice accretion and ice prevention of an aero-engine cowling in an icing wind tunnel, belonging to the technical field of ice accretion and ice prevention of an aero-engine. The tester comprises an external component arranged outside an icing wind tunnel and an internal component arranged inside the icing wind tunnel, wherein the external component comprises an electromotor (1), a driving pulley (18) and a protective cover (19) arranged outside the driving pulley; the internal component comprises a substrate (2), a shaft sleeve (9) installed on the substrate by a support (8), and a revolving shaft (12) installed in the shaft sleeve by a left bearing (7) and a right bearing (10); one end of the revolving shaft is equipped with a conical axis connector (4) on which a cowling (3) is installed; the other end of the revolving shaft is equipped with a passive pulley (13); and the passive pulley is connected with the driving pulley (18) by a belt (14). The tester is designed reasonably, so that the structure size is reduced effectively, and block influences on the icing wind tunnel and disturbances of airflows in the icing wind tunnel are decreased.

Description

用于冰风洞中研究航空发动机整流罩积冰和防冰的试验器 In an icing wind tunnel for Aircraft Engine cowling icing and anti-icing tester

[0001] 技术领域 [0001] Technical Field

本发明是一种用于在冰风洞中研究属于航空发动机积冰和防冰技术领域。 The present invention is a method for study belonging aeroengine icing and anti-icing wind tunnel BACKGROUND ice.

背景技术 Background technique

[0002] 飞机在高空低于冰点的温度下飞行时,如果穿越含有过冷水滴(温度低于冰点但仍保持液态的水)的云层,水滴碰在飞机表面上,就会在碰撞区域及其附近发生积冰。 Temperature [0002] In the high-altitude aircraft flying below freezing, if crossing over clouds containing supercooled water droplets (temperatures well below freezing but still maintain liquid water), and water droplets hit the surface on the plane, will be in the region and its impact icing occurs nearby. 飞机积冰不但增加了部件重量,而且会改变绕流流场、破坏气动性能,使操纵性和稳定性受到影响,给飞行安全带来危害。 Aircraft icing not only increase the weight of the components, but also changes the flow around, destroy aerodynamic performance, the handling and stability are affected, harm to flight safety. 近年来,由于对现代航空发动机的运行安全、效率和性能的要求越来越高,有关发动机结冰现象的研究也得到越来越多的重视。 In recent years, due to the requirements of operational safety, efficiency and performance of modern aircraft engines more and more, research on engine icing phenomenon has also been more and more attention. 发动机前端(包括整流帽罩、进气机匣及其支板、以及压气机进ロ导向叶片等)通常是出现结冰现象的主要部件。 Front of the engine (including a rectifying cap, and the intake casing strip, and ro compressor inlet guide vanes, etc.) are typically the main components of the icing phenomenon. 其中发动机进ロ整流帽罩的结冰现象对发动机气动性能有重大影响,轻则使发动机的引气量下降,推进功率减小,重则一旦冰块脱落可能造成发动机及其部件的损坏。 Wherein the engine intake ro rectifying cap icing phenomenon has a significant impact on the aerodynamic performance of the engine, ranging from the air entrainment of the engine drops, to promote the power reduction, once the ice falling weight may cause damage to the engine and its components. 所以研究整流帽罩的防冰/除冰问题具有重要意义。 So study the rectifier cap of anti-icing / de-icing issues of importance.

[0003] 有关发动机结冰现象的研究主要采用数值模拟、地面冰风洞试验、飞行试验等方式进行。 [0003] study of the main engine icing numerical simulation, ground ice wind tunnel testing, flight testing and other ways. 纵观世界各国,凡有能力独立研发飞行器的国家,大多数拥有研究评估飞行器结冰和防冰的试验研究平台——冰风洞。 Throughout the world, every country has the ability to independently develop the aircraft, most of the studies have to evaluate aircraft icing and anti-icing experimental research platform - icing wind tunnel. 冰风洞受制冷能力的限制,通常风洞试验段的尺寸都不大,因此大量的结冰试验是采用縮尺模型进行的。 Icing wind tunnel cooling capacity is limited, the size of the wind tunnel test section is generally not large, and therefore a lot of icing test was conducted using scale model. 目前国内外有关航空发动机进ロ部件的积冰实验大多是针对翼型支板和整流帽罩展开的,但都为静止状态下的实验。 At home and abroad aeronautical engine intake ro icing experiments mostly expanded member against the airfoil and the support plate rectifying the cap, but are experiments in a stationary state. 上述现有的实验系统由于不包含复杂的驱动系统,因此不考虑驱动系统对冰风洞的堵塞影响、冰风洞内结冰条件对传动系统的影响以及试验件旋转所帯来的问题诸如旋转过程中振动、传动装置的设计以及传动装置对于流场的扰动等,有关发动机旋转件结冰和防冰试验器的专利目前尚未见到报道。 Since the above-described conventional experimental system does not contain a complicated drive system, and therefore does not consider the influence of the driving system of the ice clogging wind tunnel, wind tunnel icing conditions, ice influence on the transmission system and the test piece problems such as rotation by rotation Bands design of vibration and a transmission, the transmission of the perturbation of the flow field and the like, icing and anti-icing tester patents engine rotational member currently not been reported.

发明内容 SUMMARY

[0004] 为了在冰风洞中研究航空发动机整流帽罩的结冰现象并探索其防冰措施,本发明提出了一种适用于在冰风洞内研究发动机整流帽罩积冰和防冰的试验器,该试验器经过合理设计有效减小了其结构尺寸、降低了对风洞的阻塞影响和对风洞内气流的扰动。 [0004] In order to study icing of aircraft engines rectified ice cap in the wind tunnel and explore its anti-ice measures, the present invention proposes a research engine suitable for rectification ice cap in the air duct cover icing and anti-icing tester, the tester rational design effectively reduces the size of the structure, reducing the blocking effect on the wind tunnel and disturbance of gas flow within the tunnel.

[0005] 该试验器由位于冰风洞外的外部部件和位于冰风洞内的内部部件组成;上述外部部件包括电动机、主动皮带轮和位于主动皮带轮外的防护罩;上述内部部件包括:基座、通过支柱安装于基座上的轴套、通过ー对轴承安装于轴套内的转轴;转轴一端安装有锥轴连接件,锥轴连接件上安装着整流罩;转轴另一端安装有被动皮带轮;该被动皮带轮通过皮带与上述主动皮带轮相联;基座上开有便于皮带穿过的皮带槽;上述被动皮带轮外具有被动皮带轮密封罩,上述皮带外具有皮带密封罩。 [0005] The test consists of an outer member located outside the wind tunnel ice and located inside the inner member composed of an icing wind tunnel; and the outer member includes a motor drive pulley and the driving pulley located on the outer shield; said inner member comprising: a base by struts attached to the sleeve on the base, the pair of bearings mounted on the shaft ー inner sleeve; driven pulley is attached to the other end of the rotating shaft; end of the shaft connecting member is attached to the cone axis, mounted on the taper shaft connector fairing ; the driven pulley by a belt drive pulley associated with the above-described; opened to facilitate the belt through the belt groove of the base; said driven pulley having an outer sealing cap driven pulley, said belt having an outer belt seal cap.

[0006] 本发明是基于如下思路来解决其技术问题并达到设计目标的:该试验器由位于冰风洞外的外部部件和位于冰风洞内的内部部件组成,这样就能将电动机和主动皮带轮安置于冰风洞的外部,从而显著减小试验器在风洞内的结构尺寸,减小试验器对风洞的堵塞比。 [0006] The present invention is to solve the technical problem is based on the idea and design goals: The test consists of an outer member located outside the wind tunnel ice and located inside the inner member composed of an icing wind tunnel, so that the motor can be active and ice pulley disposed outside wind tunnel, thereby significantly reducing the size of the structure in the wind tunnel test, the test is reduced clogging than wind tunnel. 电机通过皮带与整流帽罩试验台相连并驱动其工作。 Motor through a belt test bed and coupled to the rectifier and the cap drive its work. 将风洞试验段内的被动皮带轮和皮带密封在密封罩内,从而防止皮带运行过程中的结冰现象的发生,确保皮带运行性能的稳定。 The belt and the driven pulley in the wind tunnel test section sealed in the sealing cap, thereby preventing icing of the belt during running to ensure stable running performance of the belt.

[0007] 根据上述分析,本发明将驱动系统与整流帽罩试验台分离开,以达到将驱动系统移出冰风洞、减小冰风洞内整流帽罩试验台尺寸的目的,由此形成了航空发动机整流帽罩积冰和防冰试验器的分离式总体结构特点。 [0007] According to the above analysis, the present invention is a drive system of the rectifier cap separated from the test rig, the drive system in order to achieve the removal of icing wind tunnel, wind tunnel test purpose of reducing the ice cap rectifying table size, thereby forming separate the overall structural features of the cap aeroengine rectifying icing and anti-icing tester.

[0008] 本发明的有益效果是: [0008] Advantageous effects of the present invention are:

(I)驱动系统与整流帽罩试验台相分离,因而能够将驱动系统移出结冰风洞,从而减小了整流帽罩积冰和防冰试验器在风洞内的尺寸,有利于降低试验装置对风洞的堵塞比。 (I) the drive system of the rectifier cap separated test stand, and the driver out of the system can be freeze tunnel, thereby reducing the size of the rectifier cap icing and anti-ice testing in wind tunnel, and helps reduce test clogging than the wind tunnel apparatus.

[0009] (2)密封罩的设计可以防止皮带结冰,确保皮带运行性能稳定。 [0009] (2) a sealing cap designed to prevent freezing belt, the belt run to ensure stable performance. 还能够防止气流从皮带槽中进出,隔绝风洞内外气流的流通。 Also possible to prevent the flow of gas from the slot and out of the belt, isolated and outside the wind tunnel flow stream. 同时减小了皮带和皮带轮对风洞内流场的扰动。 While reducing disturbance to the belt and pulley wind tunnel flow field.

[0010] (3)通过锥轴连接件连接于整流帽罩实验台主轴前端的轴套中,该结构设计使得试验件便于拆装更换。 [0010] (3) connected by a connecting member to the sleeve tapered shaft bench spindle nose cap rectifier, the structure is designed so that the test piece was easy removal replacement.

[0011] (4)如果皮带与整流帽罩试验台的支柱位置对应,即从气流来流的方向看,皮带被支柱完全遮挡,从而进一歩降低了试验装置对风洞的堵塞比。 [0011] (4) If the position of the belt and the strut cap test bench corresponding to the rectified, i.e., to see the direction of the gas flow stream, struts belt is completely blocked, thereby reducing the clogging into a ho than the wind tunnel test apparatus.

附图说明 BRIEF DESCRIPTION

[0012] 图I是航空发动机整流帽罩积冰和防冰试验器的ニ维剖视图。 [0012] Figure I is a cross-sectional view of a Ni-dimensional Aeroengine rectifying cap icing and anti-icing tester.

[0013] 图2是航空发动机整流帽罩积冰和防冰试验器的三维造型图。 [0013] FIG. 2 is a three-dimensional shape of the cap of FIG Aeroengine rectifying icing and anti-icing tester.

[0014] 图3是航空发动机整流帽罩积冰和防冰试验器在冰风洞中的安装位置关系示意图。 [0014] FIG. 3 is a schematic view of the positional relationship aeroengine installation rectifying cap icing and anti-icing wind tunnel tests in the ice.

[0015] 图中:1.电动机;2.基座;3.整流帽罩;4.锥轴连接件;5.螺纹套;6.轴承盖;7.左轴承;8.支柱;9.轴套;10.右轴承;11.螺帽;12.转轴;13.被动皮带轮;14.皮带;15.被动皮带轮密封罩;16.皮带密封罩;17.皮带槽;18. 主动皮带轮;19.防护罩;20.风洞试验段。 . [0015] FIG: a motor; a second base; rectifying the cap 3; 4 taper shaft connecting member; 5 threaded sleeve; bearing cap 6; 7 left bearing; struts 8; 9 shaft....... sets;. right bearing 10; 11 nut; 12 shaft; 13 driven pulley; belt 14;. 15 closure cap driven pulley; belt closure cap 16; 17 belt slots;. the drive pulley 18; 19. shield; 20 tunnel test section.

具体实施方式 detailed description

[0016] 下面结合附图对本发明作进ー步的说明。 [0016] DRAWINGS The present invention will be described further into ー.

[0017] 图I显示出该防冰试验器的总体造型,该试验器由位于冰风洞外的外部部件和位于冰风洞内的内部部件组成。 [0017] Figure I shows the deicing overall shape tester, the tester located outside the outer member of icing wind tunnel located within the inner member composed of an icing wind tunnel. 外部部件包括电动机I、主动皮带轮18和位于主动皮带轮18外的防护罩19 ;内部部件包括:基座2、通过支柱8安装于基座2上的轴套9、通过ー对轴承7、10安装于轴套9内的转轴12 ;转轴一端安装有锥轴连接件4,锥轴连接件4上安装着整流罩3 ;转轴另一端安装有被动皮带轮13 ;该被动皮带轮13通过皮带14与上述主动皮带轮18相联;基座2开有便于皮带14穿过的皮带槽17 ;上述被动皮带轮13外具有被动皮带轮密封罩16,上述皮带14外具有皮带密封罩16。 Outer member includes a motor I, the drive pulley 18 and drive pulley 18 is located outside the shroud 19; interior component comprising: a base 2, is mounted on the sleeve 8 by the pillar on the base 29 by bearing 7, 10 mounted ー9 the shaft 12 within the sleeve; end of the shaft connecting member is mounted to the cone axis 4, is connected to the cone axis fairing 3 mounted on the member 4; the other end of the driven pulley shaft 13 is mounted; the driven pulley 13 via a belt 14 and the above-described active pulley 18 is associated; base 2 is opened to facilitate the belt 14 through the belt grooves 17; and the driven pulley 13 having an outer sealing cover 16 driven pulley, said belt having an outer belt 14 sealing cap 16.

[0018] 如图3所示,为了减小积冰和防冰试验器对结冰风洞的阻塞影响,应尽可能减小其结构尺寸,因此将电动机I移出冰风洞,而冰风洞内仅保留整流帽罩试验台。 [0018] 3, in order to reduce icing and anti-icing effect on blocking tester icing wind tunnel, should minimize the dimensions of the structure, so I out of the motor icing wind tunnel, and icing wind tunnel retaining only the rectifier cap test stand. 整流帽罩试验台通过基座固定于结冰风洞试验段20内壁的沉槽上,使基座上表面与结冰风洞的壁面平齐。 Rectifying cap test station through the base 20 is fixed to the inner wall of the countersink icing wind tunnel test section, the base surface of the wall surface is flush with icing wind tunnel. 同时支柱8和皮带14及其外面所罩的皮带密封罩16前后顺列布置,从冰风洞气流流动方向看皮带密封罩16被支柱8完全遮挡,从而进ー步减小试验器对冰风洞的堵塞。 Meanwhile pillar 8 and the belt 14 and the outer cover belt front-line arrangement the closure cap 16, the sealing cover 16 to see the belt struts 8 is completely blocked from icing wind tunnel flow direction, thereby further reducing the intake ー ice wind Tester plugging holes. [0019] 为了防止皮带运行过程中结冰现象的发生,确保皮带运行性能稳定,将风洞试验段内的皮带14和被动皮带轮13密封在皮带密封罩16和被动皮带轮密封罩15内。 [0019] In order to prevent ice formation during operation of the belt, to ensure stable operation of the belt performance, the belt 13 is sealed inside the wind tunnel test section 14 in the driven pulley and the belt driven pulley 16 and the sealing cap 15 the sealing cap. 密封罩15、16还隔绝风洞内外气流的流通,防止气流从皮带槽17中进出,并减小了皮带和皮带轮对风洞内流场的扰动。 The closure cap 15, 16 inside and outside the tunnel further isolated flow stream to prevent air flow out of the tank 17 from the belt, the belt and pulley is reduced and the disturbance of the flow field in a wind tunnel. · ·

[0020] 整流帽罩3经由锥轴连接件4连接到转轴12的前端,并为螺纹套5所固定,这样设计能够方便的更换和拆装整流帽罩试验件。 [0020] The rectifying cap 3 the rotation shaft 12 connected to the front 4 and 5 is fixed, so that the design can be easily replaced and the cap detachably test rectifying threaded sleeve via the cone axis.

[0021] 该试验器既能进行无防冰涂层帽罩的实验又能进行有防冰涂层帽罩的实验。 [0021] The test is carried out both without the cap deicing coating experiments can be coated with an anti-ice cap experiment.

Claims (2)

1. 一种用于冰风洞中研究航空发动机整流罩积冰和防冰的试验器,其特征在干: 包括位于冰风洞外的外部部件和位于冰风洞内的内部部件; 其中外部部件包括电动机(I)、主动皮带轮(18)和位于主动皮带轮外的防护罩(19);其中内部部件包括:基座(2)、通过支柱(8)安装于基座上的轴套(9)、通过左轴承(7)和右轴承(10)安装于轴套内的转轴(12);转轴一端安装有锥轴连接件(4),锥轴连接件上安装着整流罩(3);转轴另一端安装有被动皮带轮(13);该被动皮带轮通过皮带(14)与上述主动皮带轮(18)相联;基座(2)上开有便于皮带穿过的皮带槽(17);上述被动皮带轮(13)外具有被动皮带轮密封罩(15),上述皮带(14)外具有皮带密封罩(16)。 1. A method for use in an icing wind tunnel Aircraft Engine cowling icing and anti-icing tester, characterized in that the dry: the outer member comprises a wind tunnel and located outside of the ice within the ice tunnel inner member; wherein the external means including an electric motor (the I), drive pulley (18) located outside the drive pulley and the protective cover (19); wherein the inner member comprises: a base (2) by struts (8) mounted on the sleeve on the base (9 ), through the left bearing (7) and the right bearing (10) mounted on the shaft (12) within the sleeve; end of the shaft connecting member is mounted to the cone axis (4), mounted on the taper shaft connector fairing (3); the other end of the driven pulley attached to the rotary shaft (13); the driven pulley by a belt (14) associated with the above-described drive pulley (18); a belt groove opening (17) to facilitate passing the belt (2) a base; and the passive a pulley (13) having a driven pulley outer closure cap (15), said belt (14) having an outer belt closure cap (16).
2.根据权利要求I所述的航空发动机整流帽罩积冰和防冰试验器,其特征在于:从冰风洞气流流动方向看皮带密封罩(16)被上述支柱(8)完全遮挡。 The rectifying cap Aeroengine I according to icing and anti-icing cap tester as claimed in claim, wherein: See belt closure cap (16) is said pillar (8) completely blocked from icing wind tunnel flow direction.
CN 201210358709 2012-09-25 2012-09-25 Tester for researching ice accretion and ice prevention of aero-engine cowling in icing wind tunnel CN102853987A (en)

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