CN106441902A - Sub-scale simulated aero-engine rotation test device - Google Patents

Sub-scale simulated aero-engine rotation test device Download PDF

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CN106441902A
CN106441902A CN 201610857702 CN201610857702A CN106441902A CN 106441902 A CN106441902 A CN 106441902A CN 201610857702 CN201610857702 CN 201610857702 CN 201610857702 A CN201610857702 A CN 201610857702A CN 106441902 A CN106441902 A CN 106441902A
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simulated
mounting
connected
via
bolts
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CN 201610857702
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Chinese (zh)
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CN106441902B (en )
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刘璐璐
赵振华
陈伟
张晟
刘双丽
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南京航空航天大学
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    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR
    • G01M15/00Testing of engines
    • GPHYSICS
    • G01MEASURING; TESTING
    • G01MTESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES; TESTING STRUCTURES OR APPARATUS NOT OTHERWISE PROVIDED FOR
    • G01M7/00Vibration-testing of structures; Shock-testing of structures
    • G01M7/08Shock-testing

Abstract

The invention discloses a sub-scale simulated aero-engine rotation test device which comprises simulated casings, a simulated support plate, a simulated rotor shaft, a simulated blade disc, a simulated drum, a front fulcrum bearing, a middle fulcrum bearing, a rear fulcrum bearing and simulated front and rear mounting sections. The sub-scale simulated aero-engine rotation test device is driven by a motor to rotate through a set of breaking shaft protection devices. The simulated casings are connected via mounting side bolts. The simulated support plate is in welded connection with the simulated casings. The simulated blade disc is connected with a mounting plate and a shaft via bolts. The simulated drum is connected with the simulated support plate via bolts. The simulated front mounting section is connected with a rigid mounting base via bolts and a suspend rod. The simulated rear mounting section is connected with the rigid mounting base via bolts and a hinge. The various components of the sub-scale simulated aero-engine rotation test device can be disassembled and assembled to meet the needs of different tests.

Description

一种亚尺度模拟航空发动机旋转试验装置及试验方法 Scale simulation of one subunit Aeroengine rotation test apparatus and test method

技术领域 FIELD

[0001] 本发明涉及航空发动机冲击动力学与适航符合性验证技术领域。 [0001] The present invention relates to an impact Aeroengine kinetics and airworthiness compliance verification art.

背景技术 Background technique

[0002] 航空发动机在工作时有可能遭遇外来物如飞鸟、冰雹的撞击,也有可能遭遇转子叶片失效而发生叶片飞失事故,由于外物撞击或叶片飞失破坏了航空发动机的稳定工作状态,瞬间会产生极大的突加不平衡载荷,在设计和使用航空发动机时,必须考虑此类突加载荷对发动机安全工作的影响。 [0002] Aircraft engines have at work may encounter foreign objects such as birds, hail impact, is also likely to encounter a rotor blade failure blade flying out accident occurs due to foreign object impact or blade-out destabilizing the operating state of aircraft engines, will have a great moment of sudden unbalanced load in the design and use of aircraft engines, we must consider the impact of such a sudden load on the engine security. 目前国际上多采用真实发动机的外物吞咽和叶片飞失试验来验证发动机在遭遇上述突加载荷时的安全性,代价昂贵。 The current use of true engine was internationally swallowing and an outer blade-out tests to verify the safety of the above-described engine in the event of shock loading, expensive. 为探索航空发动机在遭遇突加载荷时的结构安全分析方法,必须采用试验、分析、验证等手段,因此,需要发展一种新的试验装置来解决上述问题,部分替代真实发动机的整机试验。 In order to explore the structure of the safety analysis of aircraft engines in the event of sudden load must be used test, analysis, verification and other means, therefore, we need to develop a new test apparatus to solve the above problem, a partial substitute for the real engine test machine.

发明内容 SUMMARY

[0003] 针对上述问题和存在不足,本发明提供了一套试验装置,该装置能可模拟航空发动机转子的主承力和主传力结构,开展外物撞击和模拟叶片飞失试验,有助于探索航空发动机在遭遇外物撞击或叶片飞失等突加载荷时的结构安全分析。 [0003] For the above-described problems and shortcomings, the present invention provides a test device, the device can be simulated and the main load-bearing structure of the engine main rotor transmission power air, carry foreign object impact test and a dummy vane fly loss, help safety analysis aeronautic engine in the event of foreign object impact or blade-like sudden loss of load in the exploration.

[0004] 为实现上述目的,本发明亚尺度模拟航空发动机旋转试验装置可采用如下技术方案: [0004] To achieve the above object, the present invention Minya Aeroengine rotating scale simulation test device may employ the following technical solutions:

[0005] —种亚尺度模拟航空发动机旋转试验装置,包括转轴、驱动转轴转动的电机、位于转轴前端的模拟叶盘、安装在转轴上的前支点轴承、安装于前支点轴承上的前模拟鼓筒、安装在转轴上的中支点轴承、安装于中支点轴承上的支板、自支板前端延伸出并包围模拟叶盘的前机匣、安装在转轴上的后支点轴承、安装于后支点轴承上的后模拟鼓筒、固定连接支板及后模拟鼓筒的后机匣;后机匣包围部分的转轴;所述中支点轴承位于前支点轴承和后支点轴承之间;前机匣的后端固定于支板的前表面上;所述前模拟鼓筒上设有第一传感器、支板上设有第二传感器、前机匣外表面上设有第三传感器、后机匣外表面设有第四传感器。 [0005] - species alkylene scale simulation of aero-engine rotation test apparatus, comprising a shaft, a drive shaft to rotate the motor, located at the front end of the rotating shaft analog leaf discs front pivot mounted to the shaft bearing, is mounted to the front simulated drum front pivot bearing cartridge, the pivot bearing mounted to the shaft, mounted on the support plate on the pivot bearing, extends from the distal end and surrounds the support plate receiver analog front leaf disks, mounted on the pivot shaft bearing mounted on the pivot post after the casing on the drum after the simulated bearing support fixedly connected to the analog board and the rear drum; rear casing surrounding the shaft portion; the rear pivot bearing in the front bearing and the pivot bearing between pivot; a front casing the rear end is fixed on the front surface of the support plate; a first sensor is provided on the front simulated drum, support plate is provided with a second sensor, the third sensor is provided on the outer surface of the front casing, the outer surface of the rear casing a fourth sensor is provided.

[0006] 本发明中通过设置前、后机匣、支板、模拟转子轴的转轴、模拟叶盘、前、后鼓筒等关键承力和传力部件,实现模拟转子结构航空发动机的结构,并方便安装各类冲击动力学参数传感器,以满足不同试验测试的需求。 [0006] The present invention, by setting the front, rear casing, support plate, the rotor shaft axis simulation, simulation leaf discs, before and after the drum and other key-bearing force transmission member, an analog implementation structure aeroengine rotor structure, and easy installation of various types of impact kinetic parameters of sensors to meet the needs of different experimental tests. 能够开展外物撞击和模拟叶片飞失试验,有助于探索航空发动机在遭遇外物撞击或叶片飞失等突加载荷时的结构安全分析。 And to carry out foreign object impact test dummy vane fly loss, contributes to evaluate the safety analysis of the structure in the event of aeroengine foreign object impact or blade-like sudden loss of load.

[0007] 而本发明中的试验方法可采用以下技术方案: [0007] Test Method and the present invention adopt the following technical solutions:

[0008] 在开展冲击强度试验时,第一、第二、第三、第四传感器均使用应变片,获得四个位置的变形与受力情况; [0008] In carrying out impact strength test, first, second, third, fourth strain gauge sensors are used to obtain the deformation and the forces of four positions;

[0009] 在开展振动试验时,第一、第二、第三、第四传感器均使用振动加速度计,获得机匣、鼓筒与支板位置的振动特性; [0009] In carrying out the vibration test, the first, second, third, fourth accelerometer vibration sensors are used to obtain a casing, the vibration characteristics of the drum position and support plate;

[0010] 在开展鸟撞、冰撞试验时,第二传感器使用应变片,而第一、第三、第四传感器使用加速度计进行测量,获得瞬时冲击载荷下的振动响应; [0010] In carrying out bird impact, ice collision test, a second strain gauge sensor, and the first, third, fourth accelerometer sensors is measured to obtain an instantaneous impact vibration response under load;

[0011] 在开展叶片丢失试验时,第三、四传感器使用应变片,而第一、第二传感器使用加速度计进行测量,获得机匣处的变形与应变,以及鼓筒及支板处由于不平衡载荷导致的振动。 [0011] due to the first and second measurements using an accelerometer sensor, strain deformation is obtained at the receiver, and the drum and the blade support plate carried at the missing test, the third and fourth strain gauge sensor, load balancing due to vibration.

[0012]上述的试验方法,通过亚尺度模拟航空发动机旋转试验装置的结构设置,能够在第一、第二、第三、第四传感器处按照不同的试验所要得到的测量数据而灵活的进行传感器设置,在同一个试验装置上即可进行不同的试验,大大提高了试验装置的通用性。 [0012] The test method, structure is provided by sub-scale simulation test device aeronautical engine revolution, it is possible first, second, third, fourth sensor according to the different experimental measurement data to be obtained by a sensor and flexible provided, on the same test device to different tests, greatly increasing the versatility of the testing device.

附图说明 BRIEF DESCRIPTION

[0013]图1是本发明模拟航空发动机旋转试验装置的结构示意图。 [0013] FIG. 1 is a schematic structural diagram of an analog aeroengine test device of the present invention, the rotation.

具体实施方式 detailed description

[0014]下面结合附图,进一步阐明本发明,应理解这些实施例仅用于说明本发明而不用于限制本发明航空发动机环境试验用可控冰雹发射装置的范围,在阅读了本发明之后,本领域技术人员对本发明的各种等价形式的修改均落于本申请所附权利要求所限定的范围。 After [0014] DRAWINGS further illustrate the invention, it should be understood that these embodiments are illustrative only and the present invention is not intended to limit the present invention aeroengine test environment with controlled range hail emitting device of the present invention upon reading, Those skilled in the art various modifications of the equivalents of the present invention fall within the present application are defined by the claims appended range.

[0015] 请参阅图1所示,本发明公开一种亚尺度模拟航空发动机旋转试验装置,包括转轴 [0015] Please refer to FIG. 1, the present invention discloses a sub-scale simulation test Aeroengine rotating means comprises a shaft

9、驱动转轴9转动的电机13、位于转轴9前端的模拟叶盘21、安装在转轴9上的前支点轴承20、安装于前支点轴承20上的前模拟鼓筒19、安装在转轴9上的中支点轴承17、安装于中支点轴承17上的支板18、自支板18前端延伸出并包围模拟叶盘21的前机匣1、安装在转轴9上的后支点轴承14、安装于后支点轴承14上的后模拟鼓筒10、固定连接支板18及后模拟鼓筒10的后机匣16。 9, the drive shaft 9 to rotate the motor 13, is located in the shaft 9 the front end analog leaf disks 21, the front pivot mounted on the rotary shaft 9 of bearing 20, attached to the front pivot bearing analog front drum 20 on 19 mounted on the rotary shaft 9 the pivot bearing 17, mounted in the pivot bearing 17 on the support plate 18, support plate 18 extends from the distal end and enclosing an analog front casing 21 of the leaf disk 1, the pivot bearing 14 is mounted on the rotary shaft 9 is attached to after the simulated pivot bearing 10 on the drum 14, is fixedly connected to the support plate 18 and the rear casing 10 after the simulation of the drum 16. 后机匣16包围部分的转轴9。 After the casing 16 surrounds the shaft portion 9. 所述中支点轴承17位于前支点轴承20和后支点轴承14之间;前机匣I的后端固定于支板的前表面上并共同形成模拟发动机外涵道。 The pivot bearing 17 is located in the front and the rear pivot bearing 20 between the pivot bearing 14; an analog outer engine duct on the front surface of the rear end of the front support fixed to the casing I and collectively form a plate. 后机匣16与支板18及后模拟鼓筒10共同形成模拟发动机内涵道。 After the casing 16 and the support plate 18 and the rear drum 10 together form a simulated engine connotation analog channel. 支板与前、后机匣间通过焊接连接成整体承力框架,可模拟航空发动机转子主承力框架。 And the front support plate, between the rear casing are integrally connected by welding load-bearing frame, can be simulated main load-bearing frame aeroengine rotor. 另,在本实施方式中,前、后机匣为薄壁圆筒带安装边和加强筋结构。 Also, in the present embodiment, the front, a thin-walled cylindrical casing with the mounting edge and the rib structure. 模拟叶片通过螺栓和安装盘与轴连接,可模拟航空发动机风扇旋转时产生的载荷;模拟鼓筒与模拟支板间通过螺栓连接,可模拟航空发动机轴承传力状态。 Simulation blade mounting plate by bolts and connected to the shaft, the rotation may be simulated load produced aviation engine fan; mock analog drum by bolting support plate, the bearing can be simulated Aeroengine force-transmitting state. 而上述的结构是固定在刚性支架上。 And said structure is fixed on a rigid support. 本实施方式中设置用以固定支板18及后模拟鼓筒10的刚性支架;所述支板18设有前安装节6,前安装节6通过吊杆5安装在刚性支架上;所述后模拟鼓筒10上设有后安装节8,后安装节8通过铰链拉杆7安装在刚性支架上,前、后安装节与刚性支架的连接可模拟航空发动机安装节的主传力路线。 Later; rigid support is provided for fixing the support plate 18 and the drum 10 after the simulation of the present embodiment; the support plate 18 is provided with a front mounting section 6, the front mounting section 6 is mounted on a rigid support by a boom 5 after analog drum 10 is provided on the installation section 8, after the installation section 8 via a hinge rod 7 is mounted on a rigid support, before, after installation connected with the rigid support section may be simulated primary load path section aeroengine installation.

[0016] 所述前模拟鼓筒19上设有第一传感器2、支板18上设有第二传感器3、前机匣I外表面上设有第三传感器4、后机匣16外表面设有第四传感器15。 [0016] The analog front provided with a first sensor 19 of the drum 2, a second sensor 3 is provided on the support plate 18, the third sensor is provided with an outer surface of the front casing 4 I, the outer surface of the casing 16 is provided A fourth sensor 15. 其中,所述转轴9与电机13输出轴同轴连接,且转轴9与输出轴之间通过预应力槽保护装置12连接。 Wherein said rotation shaft 9 is coaxially connected to the output shaft of the motor 13, and is connected by a prestressing groove 12 between the protection device and the output shaft 9 rotating shaft. 电机13通过预应力槽保护装置12驱动转轴9旋转,以完成旋转状态下的外物撞击或叶片飞失试验,预应力槽保护装置12在正常运转时为联轴器,在过载超过设计限度时自动扭断,断开动力连接,保护试验装置。 Motor protector 13 by prestressing groove 12 rotary drive shaft 9, to complete the foreign objects in rotation or blade strikes fly loss test, the protection device 12 is a prestressed coupling groove during normal operation, when an overload exceeding design limits automatically broken, disconnect the power connector, protection test apparatus.

[0017]另外,本实施方式中,三个支点轴承的设置使转轴9由三点轴承系统支撑:前支点轴承20为止推轴承,承受转轴遇突加载荷的轴向力,中支点轴承17和后支点轴承14为滚珠轴承,承受转轴9遇突加载荷的径向力,并支撑整个转轴。 [0017] In the present embodiment, three pivot bearing 9 is provided so that the rotary shaft is supported by a three-point bearing system: Front bearing 20 is pushed until the pivot bearing, to withstand axial forces encountered shaft of shock loading, the pivot bearing 17 and the pivot bearing 14 is a ball bearing, radial force in case of shock loading of the rotating shaft 9, and the entire support shaft.

[0018] 试验时,电动机带动转子转动,叶盘遭遇冲击或模拟叶片飞失时,突加载荷通过轴承系统、鼓筒、支板、主承力框架、后支点承力框架传出,通过前后安全节传递到刚性支架上,期间各项动力学参数有安装在各特征位置的传感器记录以供分析。 [0018] During the test, the motor drives the rotor to rotate, or simulate the impact suffered blisk blades fly lost time, by sudden load bearing system, the drum, the support plate, main load-bearing frame, the fulcrum of the load-bearing frame came, before and after security section transmitted to the rigid support, during the kinetic parameters of a sensor installed in a recording position for each feature analysis.

[0019]另外,本实施方式中提供以下优选的试验实施例以体现上述亚尺度模拟航空发动机旋转试验装置能够具体应用的试验方法。 [0019] Further, the present embodiment provides the following preferred embodiments are presented to reflect the Test Test Method above-described sub-scale simulation test apparatus capable of rotating Aeroengine particular application.

[0020] 在开展冲击强度试验时,第一、第二、第三、第四传感器均使用应变片,获得四个位置的变形与受力情况; [0020] In carrying out impact strength test, first, second, third, fourth strain gauge sensors are used to obtain the deformation and the forces of four positions;

[0021] 在开展振动试验时,第一、第二、第三、第四传感器均使用振动加速度计,获得机匣、鼓筒与支板位置的振动特性; [0021] In carrying out the vibration test, the first, second, third, fourth accelerometer vibration sensors are used to obtain a casing, the vibration characteristics of the drum position and support plate;

[0022] 在开展鸟撞、冰撞试验时,第二传感器使用应变片,而第一、第三、第四传感器使用加速度计进行测量,获得瞬时冲击载荷下的振动响应; [0022] In carrying out bird impact, ice collision test, a second strain gauge sensor, and the first, third, fourth accelerometer sensors is measured to obtain an instantaneous impact vibration response under load;

[0023] 在开展叶片丢失试验时,第三、四传感器使用应变片,而第一、第二传感器使用加速度计进行测量,获得机匣处的变形与应变,以及鼓筒及支板处由于不平衡载荷导致的振动。 [0023] due to the first and second measurements using an accelerometer sensor, strain deformation is obtained at the receiver, and the drum and the blade support plate carried at the missing test, the third and fourth strain gauge sensor, load balancing due to vibration.

[0024]另外,本发明的具体实现方法和途径很多,以上所述仅是本发明的优选实施方式。 [0024] Further, the specific ways and means of the present invention to achieve many of the above embodiments are only preferred embodiment of the present invention. 应当指出,对于本技术领域的普通技术人员来说,在不脱离本发明原理的前提下,还可以做出若干改进和润饰,这些改进和润饰也应视为本发明的保护范围。 It should be noted, for the ordinary person skilled in the art, without departing from the principles of the invention premise, can make various improvements and modifications, and these improvements and modifications should be the scope of the invention. 本实施例中未明确的各组成部分均可用现有技术加以实现。 The various components are not explicitly described in this embodiment can be realized by the prior art.

Claims (5)

  1. 1.一种亚尺度模拟航空发动机旋转试验装置,其特征在于:包括转轴、驱动转轴转动的电机、位于转轴前端的模拟叶盘、安装在转轴上的前支点轴承、安装于前支点轴承上的前模拟鼓筒、安装在转轴上的中支点轴承、安装于中支点轴承上的支板、自支板前端延伸出并包围模拟叶盘的前机匣、安装在转轴上的后支点轴承、安装于后支点轴承上的后模拟鼓筒、固定连接支板及后模拟鼓筒的后机匣;后机匣包围部分的转轴;所述中支点轴承位于前支点轴承和后支点轴承之间;前机匣的后端固定于支板的前表面上;所述前模拟鼓筒上设有第一传感器、支板上设有第二传感器、前机匣外表面上设有第三传感器、后机匣外表面设有第四传感器。 An aero engine rotation alkylene scale simulation test device comprising: a shaft, a motor drive shaft rotates, the rotation shaft at the front leaf disks analog front pivot bearing mounted to the shaft, mounted on the front of the pivot bearing the analog front drum, the pivot shaft mounted on a bearing attached to the support plate on the pivot bearing, extends from the distal end and surrounds the support plate receiver analog front leaf disks, mounted on the pivot shaft bearing mounted after the drum casing after analog rear pivot bearing on the fixed support plate and the rear connecting analog drum; rear casing surrounding the shaft portion; said fulcrum bearing positioned between the front and rear pivot bearing pivot bearing; before the rear end of the casing is fixed on the front surface of the support plate; a first sensor is provided on the front simulated drum, support plate is provided with a second sensor, the third sensor is provided on the outer surface of the front casing, the machine an outer surface of the cartridge is provided with a fourth sensor.
  2. 2.根据权利要求1所述的亚尺度模拟航空发动机旋转试验装置,其特征在于:所述转轴与电机输出轴同轴连接,且转轴与输出轴之间通过预应力槽保护装置连接。 2. The sub-scale simulation of the aero engine according to claim 1, the rotation test apparatus, wherein: said rotation shaft is coaxial with the motor output shaft is connected, and between the shaft and the output shaft are connected by the protection device prestressing groove.
  3. 3.根据权利要求1或2所述的亚尺度模拟航空发动机旋转试验装置,其特征在于:前支点轴承为止推轴承,中支点轴承为滚珠轴承,后支点轴承为滚珠轴承。 The sub-scale simulation of aero-engine of claim 1 or claim 2 rotates test apparatus, wherein: the front pivot bearing of the thrust bearing, the pivot bearing is a ball bearing, the pivot bearing is a ball bearing.
  4. 4.根据权利要求3所述的亚尺度模拟航空发动机旋转试验装置,其特征在于:还包括用以固定支板及后模拟鼓筒的刚性支架;所述支板设有前安装节,前安装节通过吊杆安装在刚性支架上;所述后模拟鼓筒上设有后安装节,后安装节通过铰链拉杆安装在刚性支架上。 The dimensions of the sub-engine 3, the rotating analog aerial test apparatus as claimed in claim, characterized in that: the bracket further comprises a rigid support plate and for fixing the simulated drum; said support plate is provided with front mounting section, before installation by boom section mounted on a rigid support; simulation after the mounting section is provided on the drum, after the mounting section is mounted by hinges on a rigid support rod.
  5. 5.如权利要求1至4中任一项所述亚尺度模拟航空发动机旋转试验装置的试验方法,其特征在于: 在开展冲击强度试验时,第一、第二、第三、第四传感器均使用应变片,获得四个位置的变形与受力情况; 在开展振动试验时,第一、第二、第三、第四传感器均使用振动加速度计,获得机匣、鼓筒与支板位置的振动特性; 在开展鸟撞、冰撞试验时,第二传感器使用应变片,而第一、第三、第四传感器使用加速度计进行测量,获得瞬时冲击载荷下的振动响应; 在开展叶片丢失试验时,第三、四传感器使用应变片,而第一、第二传感器使用加速度计进行测量,获得机匣处的变形与应变,以及鼓筒及支板处由于不平衡载荷导致的振动。 1 5. The method of testing a sub-scale simulation test Aeroengine rotating device according to any of claims 1-4, characterized in that: in carrying out impact strength test, first, second, third and fourth sensors are strain gauge, the forces obtained with the four modified position; vibration test carried out at the first, second, third, fourth accelerometer vibration sensors are used to obtain the casing, the drum position and support plate vibration characteristics; in carrying out bird impact, ice collision test, a second strain gauge sensor, and the first, third, fourth measurement sensor using an accelerometer, vibration response obtained under impact load transient; lost in carrying out the test blade when the third and fourth strain gauge sensors, and a first, a second sensor measurement using accelerometers, strain deformation is obtained at the receiver, and the drum and the support plate due to the unbalanced load due to vibration.
CN 201610857702 2016-09-27 2016-09-27 Scale simulation of one subunit Aeroengine rotation test apparatus and test method CN106441902B (en)

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