WO2022100654A1 - 一种用于航空动力的螺旋桨传动系统 - Google Patents

一种用于航空动力的螺旋桨传动系统 Download PDF

Info

Publication number
WO2022100654A1
WO2022100654A1 PCT/CN2021/130017 CN2021130017W WO2022100654A1 WO 2022100654 A1 WO2022100654 A1 WO 2022100654A1 CN 2021130017 W CN2021130017 W CN 2021130017W WO 2022100654 A1 WO2022100654 A1 WO 2022100654A1
Authority
WO
WIPO (PCT)
Prior art keywords
propeller
disk
transmission system
propeller shaft
shaft
Prior art date
Application number
PCT/CN2021/130017
Other languages
English (en)
French (fr)
Inventor
李兴胜
龚明成
唐中
皮礼平
Original Assignee
重庆宗申航空发动机制造有限公司
Priority date (The priority date is an assumption and is not a legal conclusion. Google has not performed a legal analysis and makes no representation as to the accuracy of the date listed.)
Filing date
Publication date
Application filed by 重庆宗申航空发动机制造有限公司 filed Critical 重庆宗申航空发动机制造有限公司
Priority to US18/036,702 priority Critical patent/US20230391465A1/en
Priority to EP21891174.1A priority patent/EP4238873A4/en
Publication of WO2022100654A1 publication Critical patent/WO2022100654A1/zh

Links

Images

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C11/00—Propellers, e.g. of ducted type; Features common to propellers and rotors for rotorcraft
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/04—Helicopters
    • B64C27/12—Rotor drives
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64D—EQUIPMENT FOR FITTING IN OR TO AIRCRAFT; FLIGHT SUITS; PARACHUTES; ARRANGEMENT OR MOUNTING OF POWER PLANTS OR PROPULSION TRANSMISSIONS IN AIRCRAFT
    • B64D35/00—Transmitting power from power plants to propellers or rotors; Arrangements of transmissions
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D3/00—Yielding couplings, i.e. with means permitting movement between the connected parts during the drive
    • F16D3/02—Yielding couplings, i.e. with means permitting movement between the connected parts during the drive adapted to specific functions
    • F16D3/12—Yielding couplings, i.e. with means permitting movement between the connected parts during the drive adapted to specific functions specially adapted for accumulation of energy to absorb shocks or vibration
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D7/00—Slip couplings, e.g. slipping on overload, for absorbing shock
    • F16D7/02—Slip couplings, e.g. slipping on overload, for absorbing shock of the friction type
    • F16D7/024—Slip couplings, e.g. slipping on overload, for absorbing shock of the friction type with axially applied torque limiting friction surfaces
    • F16D7/025—Slip couplings, e.g. slipping on overload, for absorbing shock of the friction type with axially applied torque limiting friction surfaces with flat clutching surfaces, e.g. discs
    • F16D7/027—Slip couplings, e.g. slipping on overload, for absorbing shock of the friction type with axially applied torque limiting friction surfaces with flat clutching surfaces, e.g. discs with multiple lamellae
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D2300/00—Special features for couplings or clutches
    • F16D2300/12—Mounting or assembling
    • F—MECHANICAL ENGINEERING; LIGHTING; HEATING; WEAPONS; BLASTING
    • F16—ENGINEERING ELEMENTS AND UNITS; GENERAL MEASURES FOR PRODUCING AND MAINTAINING EFFECTIVE FUNCTIONING OF MACHINES OR INSTALLATIONS; THERMAL INSULATION IN GENERAL
    • F16D—COUPLINGS FOR TRANSMITTING ROTATION; CLUTCHES; BRAKES
    • F16D2300/00—Special features for couplings or clutches
    • F16D2300/22—Vibration damping

Definitions

  • the present invention relates to a transmission system, especially a power system for aerodynamic propellers.
  • Aviation power including the power system of helicopters, drones, or various types of aircraft.
  • the power is transmitted from the main drive shaft (crankshaft) to the driving gear, and then the driving gear drives the driven gear to rotate, and finally the propeller shaft transmits its rotation to the rotating member (propeller shaft, driving method).
  • the rotating member propeller shaft, driving method.
  • a clutch is often installed on the rotating member, and the clutch is connected with the rotating member through a spline.
  • the clutch and the rotating component When the rotating component is subjected to an external force that exceeds the component’s ability to withstand during the movement and transmission of power, the clutch and the rotating component will temporarily disengage from the rotating direction, that is, the clutch and the rotating shaft will slip, avoiding the rotating components (including the propeller shaft, driving shaft isometric) damaged by impact. In order to prevent damage to the rotating shaft, the clutch slip torque needs to be properly designed.
  • the vibration damping system is arranged on the box body or externally placed on the box body, and the vibration source or power source of the propeller drive system directly transmits the vibration to the transmission box, reducing the transmission rate. Box lifetime and NVH performance. And the external vibration damping system increases the size, space and weight of the transmission system.
  • the purpose of the present invention is to provide a propeller drive system for aviation power with high safety and small size.
  • a propeller transmission system for aviation power comprising a propeller shaft, one end of the propeller shaft is a power input end, and the other end of the propeller shaft is used for connecting the propeller, It is characterized in that: the power input end of the propeller shaft is provided with a driven gear, and the driven gear is in driving connection with the input end of the overload clutch, and also includes a torsional vibration damper, and the output end of the overload clutch is connected with the torsion damper.
  • the vibration damper is connected in an axial drive through a flexible disk, and the torsional vibration absorber is drive connected with the propeller shaft.
  • the hub core of the overload clutch is hollowly sleeved on the propeller shaft and one end is axially limited, and the driven gear is fixedly connected to the hub core of the overload clutch, so The driven friction plate of the overload clutch is spline-connected to the sleeve portion of the flexible disc.
  • the flexible disc includes the sleeve part, one end of the sleeve part is provided with a disc-shaped part, and the disc-shaped part is connected with the torsional vibration damper.
  • the support plate is fixedly connected.
  • the hub core of the torsional vibration absorber is spline-connected to the propeller shaft.
  • the outer ring of the disk-shaped portion of the flexible disk is fixedly connected with the outer ring of the holding disk of the torsional vibration damper.
  • the outer ring of the disk-shaped portion of the flexible disk is riveted to the outer ring of the holding disk of the torsional vibration damper.
  • the rear end face of the hub core of the overload clutch is axially limited by a shaft sleeve fixed on the propeller shaft.
  • the end of the propeller shaft used for connecting the propeller is provided with a shaft shoulder, and the shaft shoulder is provided with an isolation ring, and the isolation ring is used for the torsional vibration damper.
  • the front end face is axially limited, and the spacer ring is in arc-surface contact with the shaft shoulder.
  • a bearing for supporting the casing is provided between the spacer ring and the front end surface of the disk hub core of the torsional shock absorber, and the bearing is connected to the disk hub of the torsional shock absorber.
  • a bushing is provided between the front end faces of the cores.
  • the torsional vibration damper in the present invention has a torsional angle of 30° and has a large margin of vibration damping performance.
  • the invention adopts the torsional vibration absorber and the overload clutch to realize the axial series connection through the flexible disk, integrates the overload protection function and the vibration damping performance in the existing propeller transmission box, and improves the NVH performance and service life of the propeller transmission system. At the same time, the radial space volume and weight of the propeller drive system are reduced.
  • the connection of the flexible disk can not only realize the integration of the overload function and the vibration damping function, but also can transmit higher torque, improve the reliability of the structure, and reduce the radial dimension of the structure.
  • the transmission system of the present invention is light in weight, small in size, easy to arrange, and has great advantages for mechanical arrangements that are sensitive to size and weight.
  • the isolation ring can not only limit the position of the torsional shock absorber, but also have the function of impact protection.
  • FIG. 1 is a front view of a propeller drive system in an embodiment
  • Fig. 2 is the A-A sectional view of Fig. 1;
  • Fig. 3 is the A-A cross-sectional view of Fig. 1 (box is not included);
  • Figure 4 is an axonometric view of the flex disk.
  • Embodiment As shown in Figures 1-4, this embodiment provides a propeller drive system for aerodynamic power, such as can be used on aircraft such as unmanned aerial vehicles and helicopters.
  • a propeller shaft 1 one end of the propeller shaft is a power input end, the other end of the propeller shaft is used to connect the propeller, the power input end of the propeller shaft is provided with a driven gear 2, the driven gear and the overload
  • the input end of the clutch 3 is drive-connected, and also includes a torsional damper 6.
  • the output end of the overload clutch is axially drive-connected to the torsional damper through a flexible disk 4, and the torsional damper is connected to the propeller. Shaft drive connection.
  • the driven gear receives the power from the driving gear and transmits the power to the overload clutch, and the overload clutch transmits the power to the torsional vibration damper through the flexible disc, and the torsional vibration damper finally transmits the power to the propeller shaft.
  • the overload clutch plays the role of overload protection
  • the torsional vibration damper plays the role of damping the transmitted power and balancing the torque.
  • the driven gear is meshed with the driving gear, and the driving gear is connected to the driving shaft or the crankshaft of the engine, and the power output by the engine is transmitted to the driven gear on the propeller shaft by means of gear meshing.
  • the driven gear is fixedly connected with the input end of the overload clutch installed on the propeller shaft, and transmits the power to the overload clutch.
  • the flexible disk 4 includes a sleeve portion 41 and a disk-shaped portion 42, and the disk-shaped portion is provided on one end face of the sleeve portion.
  • the sleeve part is hollowly sleeved on the propeller shaft, and the outer wall of the sleeve part is provided with splines, the friction plates 32 of the overload clutch and the outer wall splines of the sleeve part of the flexible disk connect. Therefore, the power is transmitted to the flexible disk through the splined connection of the overload clutch with the flexible disk.
  • the disk-shaped portion of the flexible disk is connected to the torsional vibration absorber, the torsional vibration absorber includes a holding disk 62 and a disk hub core 61, and the disk-shaped portion of the flexible disk is connected to the torsional vibration absorber.
  • the holding disc is fixedly connected, and the disc hub core of the torsional vibration damper is splined to the propeller shaft.
  • the support disk of the torsional vibration absorber is driven to rotate, and the support disk of the torsional shock absorber compresses the spring during the rotation, and the buffering of the spring can absorb vibration and uniform torque.
  • the hub core 31 of the overload clutch is hollowly sleeved on the propeller shaft and one end is axially limited
  • the driven gear is sleeved on the hub core of the overload clutch
  • the end face and the hub core of the overload clutch are fixedly connected by screws or other means.
  • an elastic bushing 12 is arranged on the propeller shaft, and the hub core of the overload clutch is sleeved on the elastic bushing, so that the wear on the propeller shaft can be reduced.
  • the end face of the disk hub core of the overload clutch that is far away from the propeller shaft where the propeller is installed is axially limited by the shaft sleeve 7 or other means.
  • the overload force value of the overload clutch is preset according to the engine power.
  • the length of the sleeve portion of the flexible disc is greater than the length of the friction plate of the overload clutch, and a gasket is also provided between the end face of the sleeve portion of the flexible disc and the end face of the hub core of the overload clutch .
  • the outer ring of the disk-shaped portion of the flexible disk is fixedly connected to the outer ring of the holding disk of the torsional vibration damper.
  • the outer ring of the disk-shaped portion of the flexible disk is The outer ring of the holding plate of the torsional shock absorber is riveted, and the multi-point uniform rivets 5 are fixedly connected in the circumferential direction.
  • the end of the torsional vibration damper facing the installation of the propeller is also axially limited.
  • the end of the propeller shaft used for connecting the propeller is provided with a shaft shoulder 11, and an isolation ring 8 is provided at the shaft shoulder, and the isolation ring axially provides the front end surface of the hub core of the torsional vibration damper.
  • the spacer ring is in arc-surface contact with the shaft shoulder.
  • a bearing 9 for supporting the box is provided between the spacer ring and the front end surface of the hub core of the torsional vibration damper, and the bearing is connected to the torsional vibration damper.
  • a bushing 10 is provided between the front end faces of the hub core of the device.
  • the torsional shock absorber in this embodiment is a shock absorber with a conventional structure that can be purchased on the market, but the torsion angle of the torsional shock absorber in this embodiment is 30°, that is to say, the angle of the spring compression can reach 30° °, with a large margin of vibration damping performance.
  • the overload clutch is also a commercially available overload clutch of conventional structure.
  • the flexible disk is provided with a weight reduction hole 43 .
  • the casing of the transmission system is set in separate parts, including the first casing 13 in front and the second casing 14 at the rear.
  • the second sub-box surface is the back of the flexible disc.
  • the box body 1 and the box body 2 are connected by screws.
  • the propeller shaft is a hollow shaft
  • an inner shaft 15 is arranged in the propeller shaft
  • an oil cavity is formed between the inner shaft and the propeller shaft
  • the oil cavity is The end is provided with an oil inlet hole.
  • the oil inlet hole 17 is arranged on the propeller shaft and communicates with the external oil circuit.
  • Two oil seals 16 are arranged at the oil inlet hole, and the oil inlet is formed by the two oil seals. Chamber.
  • the oil cavity is provided with a plurality of lubricating oil holes, the lubricating oil holes are disposed on the propeller shaft, and the lubricating oil holes are opposite to the places on the propeller shaft where other components are assembled, for example, the The lubricating oil holes are used to deliver lubricating oil to overload clutches, driven gears, torsional vibration dampers, etc. Oil passages may also be provided on the flexible disc, and components such as friction plates of the overload clutch are lubricated through the oil passages.
  • the propeller shaft in the present invention takes the propeller end as the front and the power input end as the rear.
  • the torsional vibration absorber and the overload clutch are connected in axial series and parallel transmission through the flexible disk, and the overload protection function and vibration reduction performance are integrated into the existing propeller transmission box, which improves the NVH performance and the performance of the propeller transmission system. service life. At the same time, the radial space volume and weight of the propeller drive system are reduced.
  • the connection of the flexible disk can not only realize the integration of the overload function and the vibration damping function, but also can transmit higher torque, improve the reliability of the structure, and reduce the radial dimension of the structure.
  • the transmission system of the present invention is light in weight, small in size, easy to arrange, and has great advantages for mechanical arrangements that are sensitive to size and weight.
  • the isolation ring can not only limit the position of the torsional shock absorber, but also have the function of impact protection.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • General Engineering & Computer Science (AREA)
  • Mechanical Operated Clutches (AREA)

Abstract

一种用于航空动力的螺旋桨传动系统，包括螺旋桨轴（1），螺旋桨轴（1）的一端为动力输入端，螺旋桨轴（1）的另一端用于连接螺旋桨，螺旋桨轴（1）的动力输入端设置有从动齿轮（2），从动齿轮（2）与过载离合器（3）的输入端传动连接，还包括扭转减振器（6），过载离合器（3）的输出端与扭转减振器（6）通过挠性盘（4）轴向传动连接，扭转减振器（6）与螺旋桨轴（1）传动连接。

Description

一种用于航空动力的螺旋桨传动系统 技术领域
本发明涉及一种传动系统，尤其是用于航空动力的螺旋桨的动力系统。
背景技术
航空动力，包括直升机、无人机、或者各类飞行器的动力系统。其发动机传动机构中，动力由主传动轴(曲轴)传递到主动齿轮上，再由所述主动齿轮带动从动齿轮转动，最后由螺旋桨轴将其转动传递到旋转构件上(螺旋桨轴、驱动法兰等)。在现有的从动齿上，往往所述旋转构件上安装有离合器，离合器通过花键与旋转构件连接。当所述旋转构件在运动传递动力过程中若受到超过构件能承受的外力时，离合器与旋转构件短暂脱离旋转方向，即离合器与旋转轴出现打滑的现象，避免旋转部件(包括螺旋桨轴，主动轴等轴类)受冲击损坏。为了防止旋转轴损坏，离合器打滑扭转力矩就需要设计合理。
另外，现有的螺旋将传动系统一般而言是将减振系统设置在箱体上或者外置于箱体上，螺旋桨传动系统的振动源或动力源直接将振动传递给传动箱，降低了传动箱的寿命和NVH性能。并且外置的减振系统增加了传动系统的尺寸空间和重量。
发明内容
本发明的目的在于提供一种安全性高且体积小的用于航空动力的螺旋桨传动系统。
为了实现上述目的，本发明是这样设置的：一种用于航空动力的螺旋桨传 动系统，包括螺旋桨轴，所述螺旋桨轴的一端为动力输入端，所述螺旋桨轴的另一端用于连接螺旋桨，其特征在在于：所述螺旋桨轴的动力输入端设置有从动齿轮，所述从动齿轮与过载离合器的输入端传动连接，还包括扭转减振器，所述过载离合器的输出端与扭转减振器通过挠性盘轴向传动连接，所述扭转减振器与所述螺旋桨轴传动连接。采用上述过载离合器与扭转减振器结合的方式，不但使得螺旋桨转动系统具备减振性能和扭矩过载保护，还能够减小设计空间和尺寸，取得更好的NVH性能和寿命。
为进一步减小径向尺寸，所述过载离合器的盘毂芯空套在所述螺旋桨轴上且一端被轴向限位，所述从动齿轮与所述过载离合器的盘毂芯固定连接，所述过载离合器的从动摩擦片与所述挠性盘的套筒部分花键连接。
为进一步减小径向尺寸其提高减振效果，所述挠性盘包括所述套筒部分，所述套筒部分的一端设置有盘状部分，所述盘状部分与所述扭转减振器的加持盘固定连接。
为进一步实现螺旋桨轴的转动，所述扭转减振器的盘毂芯与所述螺旋桨轴花键连接。
为进一步传递更大的扭矩，所述挠性盘的盘状部分的外圈与所述扭转减振器的加持盘的外圈固定连接。
为进一步传递更大的扭矩，所述挠性盘的盘状部分的外圈与所述扭转减振器的加持盘的外圈铆接连接。
优选的，所述过载离合器的盘毂芯后端端面被固定在所述螺旋桨轴上的轴套轴向限位。
为进一步保护螺旋桨轴不损坏，所述螺旋桨轴的用于连接螺旋桨的一端设 置有轴肩，所述轴肩处设置有隔离环，所述隔离环对所述扭转减振器的盘毂芯的前端面进行轴向限位，所述隔离环与所述轴肩为弧面接触。采用隔离环，在受到超过系统能承受的最大轴向力时，隔离环因受到斜向力有变大的趋势，在超过隔离环能承受的力时，隔离环损坏，保护螺旋桨轴不损坏。
为进一步减小轴向长度，所述隔离环与所述扭转减振器的盘毂芯的前端面之间设置有用于支撑箱体的轴承，所述轴承与所述扭转减振器的盘毂芯的前端面之间设置有衬套。
本发明中的扭转减振器的扭转角度为30°，具有大裕度的减振性能。
有益效果：
本发明采用扭转减振器与过载离合器通过挠性盘实现轴向串联连接，在现有的螺旋桨传动箱内集成了过载保护功能和减振性能，提高了螺旋桨传动系统的NVH性能和使用寿命。同时，减小了螺旋桨传动系统的径向空间体积和重量。通过挠性盘的连接不但能够实现将过载功能和减振功能集成，还能够传递更高扭矩，提高结构的可靠性，减小结构的径向尺寸。
第二，本发明的传动系统重量较小，尺寸小，容易布置，对于尺寸及重量敏感的机械布置有较大的优势。
第三，通过隔离环的设计，不但能够对扭转减振器进行限位，还能够具有冲击保护的功能。
附图说明
图1为实施例中螺旋桨传动系统主视图；
图2为图1的A-A剖视图；
图3为图1的A-A剖视图(不含箱体)；
图4为挠性盘的轴测图。
标号说明：1螺旋桨轴、11轴肩、2从动齿轮、3过载离合器、31过载离合器的盘毂芯、32过载离合器的摩擦片、4挠性盘、41套筒部分、42盘状部分、43减重孔、5铆钉、6扭转减振器、61扭转减振器的盘毂芯、62加持盘、7轴套、8隔离环、9轴承、10衬套、12弹性衬套、13箱体一、14、箱体二、15内轴、16油封、17进油孔。
具体实施方式
下面结合附图对本发明的具体实施方式作进一步详细的说明，但本发明并不局限于这些实施方式，任何在本实施例基本精神上的改进或代替，仍属于本发明权利要求所要求保护的范围。
实施例：如图1-4所示，本实施例提供一种用于航空动力的螺旋桨传动系统，如可用于无人机、直升机等飞行器上。包括螺旋桨轴1，所述螺旋桨轴的一端为动力输入端，所述螺旋桨轴的另一端用于连接螺旋桨，所述螺旋桨轴的动力输入端设置有从动齿轮2，所述从动齿轮与过载离合器3的输入端传动连接，还包括扭转减振器6，所述过载离合器的输出端通过挠性盘4与所述扭转减振器轴向传动连接，所述扭转减振器与所述螺旋桨轴传动连接。
其中，所述从动齿轮接受来自主动齿轮的动力，并将动力传递给过载离合器，过载离合器通过挠性盘将动力传递给扭转减振器，而扭转减振器最终将动力传递给螺旋桨轴。此过程中，所述过载离合器起到过载保护的作用，而扭转减振器起到对传递过来的动力进行减振以及均匀扭矩的效果。
在本实施例中，所述从动齿轮与主动齿轮啮合，所述主动齿轮与主动轴或者发动机曲轴传动连接，将发动机输出的动力通过齿轮啮合的方式传递到螺旋 桨轴上的从动齿轮上。所述从动齿轮与安装在螺旋桨轴上的过载离合器的输入端固定连接，并将动力传递到过载离合器。所述挠性盘4包括套筒部分41和盘状部分42，所述盘状部分设置在套筒部分的一端面。所述套筒部分空套在所述螺旋桨轴上，并且所述套筒部分的外壁上设置有花键，所述过载离合器的摩擦片32与所述挠性盘的套筒部分的外壁花键连接。因此，动力通过过载离合器与挠性盘的花键连接被传递到挠性盘上。而所述挠性盘的盘状部分与所述扭转减振器连接，所述扭转减振器包括加持盘62和盘毂芯61，所述挠性盘的盘状部分与扭转减振器的加持盘固定连接，所述扭转减振器的盘毂芯与螺旋桨轴花键连接。所述挠性盘转动的过程中带动所述扭转减振器的加持盘转动，所述扭转减振器的加持盘转动的过程中压缩弹簧，通过弹簧的缓冲能够吸收振动并且能够均匀扭矩。
在本实施例中，所述过载离合器的盘毂芯31空套在所述螺旋桨轴上且一端被轴向限位，所述从动齿轮套设在所述过载离合器的盘毂芯上，且端面与过载离合器的盘毂芯采用螺钉或者其他方式进行固定连接。并且，在所述螺旋桨轴上设置有弹性衬套12，所述过载离合器的盘毂芯套设在所述弹性衬套上，这样设置能够减少对螺旋桨轴的磨损。所述过载离合器的盘毂芯的远离螺旋桨轴的安装螺旋桨的一端端面通过轴套7或者其他方式实现轴向限位。
所述过载离合器的过载力值根据发动机功率进行预先设置。所述挠性盘的套筒部分的长度大于过载离合器的摩擦片的长度，且所述挠性盘的套筒部分的端面与所述过载离合器的盘毂芯的端面之间还设置有垫片。
所述挠性盘的盘状部分的外圈与所述扭转减振器的加持盘的外圈进行固定连接，在本实施例中，所述挠性盘的盘状部分的外圈与所述扭转减振器的加持 盘的外圈采用铆接的方式，在圆周方向上进行多点均匀铆钉5固定连接。
另外，所述扭转减振器的朝向安装螺旋桨的一端也被轴向限位。具体的，螺旋桨轴的用于连接螺旋桨的一端设置有轴肩11，所述轴肩处设置有隔离环8，所述隔离环对所述扭转减振器的盘毂芯的前端面进行轴向限位，所述隔离环与所述轴肩为弧面接触。采用隔离环，不但能够对扭转减振器进行轴向限位，而且在受到超过系统能承受的最大轴向力时，隔离环因受到斜向力有变大的趋势，在超过隔离环能承受的力时，隔离环损坏，保护螺旋桨轴不损坏。
作为本实施例中的另一实施方式，所述隔离环与所述扭转减振器的盘毂芯的前端面之间设置有用于支撑箱体的轴承9，所述轴承与所述扭转减振器的盘毂芯的前端面之间设置有衬套10。
另外，本实施例中的扭转减振器为市面上可购买的常规结构的减振器，但是本实施例的扭转减振器的扭转角度为30°，也就是说弹簧压缩的角度可达到30°，具有大裕度的减振性能。所述过载离合器也为市面上可购买的常规结构的过载离合器。
作为本实施例中的另一实施方式，所述挠性盘上设置有减重孔43。
另外，作为本实施例中的另一实施方式，所述传动系统的箱体为分体设置，包括在前的箱体一13和在后的箱体二14，所述箱体一和箱体二的分箱面为挠性盘的后面。所述箱体一和箱体二采用螺钉进行连接。在安装时，能够现将扭转减振器和挠性盘安装到箱体一内再将箱体一和箱体二合箱固定，然后再在箱体二中安装所述过载离合器以及从动齿。
作为本实施例中的另一实施方式，所述螺旋桨轴为空心轴，所述螺旋桨轴内设置有内轴15，所述内轴与所述螺旋桨轴之间形成油腔，所述油腔的端部设 置有进油孔，所述进油孔17设置在所述螺旋桨轴上，且与外部油路相通，所述进油孔处设置有两个油封16，通过两个油封形成了进油腔室。所述油腔上设置有多个润滑油孔，所述润滑油孔设置在所述螺旋桨轴上，并且所述润滑油孔与螺旋桨轴上的装配有其他部件的地方相对，比如所，所述润滑油孔用于向过载离合器、从动齿轮、扭转减振器等输送润滑油。在所述挠性盘上还可设置油道，通过油道对过载离合器的摩擦片等部件进行润滑。
本发明中的螺旋桨轴，以螺旋桨端为前，动力输入端为后。
本实施例采用扭转减振器与过载离合器通过挠性盘实现轴向串联并传动连接，在现有的螺旋桨传动箱内集成了过载保护功能和减振性能，提高了螺旋桨传动系统的NVH性能和使用寿命。同时，减小了螺旋桨传动系统的径向空间体积和重量。通过挠性盘的连接不但能够实现将过载功能和减振功能集成，还能够传递更高扭矩，提高结构的可靠性，减小结构的径向尺寸。
第二，本发明的传动系统重量较小，尺寸小，容易布置，对于尺寸及重量敏感的机械布置有较大的优势。
第三，通过隔离环的设计，不但能够对扭转减振器进行限位，还能够具有冲击保护的功能。

Claims (10)

  1. 一种用于航空动力的螺旋桨传动系统，包括螺旋桨轴，所述螺旋桨轴的一端为动力输入端，所述螺旋桨轴的另一端用于连接螺旋桨，其特征在在于：所述螺旋桨轴的动力输入端设置有从动齿轮，所述从动齿轮与过载离合器的输入端传动连接，还包括扭转减振器，所述过载离合器的输出端与扭转减振器通过挠性盘轴向传动连接，所述扭转减振器与所述螺旋桨轴传动连接。
  2. 如权利要求1所述的用于航空动力的螺旋桨传动系统，其特征在于：所述过载离合器的盘毂芯空套在所述螺旋桨轴上且一端被轴向限位，所述从动齿轮与所述过载离合器的盘毂芯固定连接，所述过载离合器的从动摩擦片与所述挠性盘的套筒部分花键连接。
  3. 如权利要求1或2所述的用于航空动力的螺旋桨传动系统，其特征在于：所述挠性盘包括所述套筒部分，所述套筒部分的一端设置有盘状部分，所述盘状部分与所述扭转减振器的加持盘固定连接。
  4. 如权利要求3所述的用于航空动力的螺旋桨传动系统，其特征在于：所述扭转减振器的盘毂芯与所述螺旋桨轴花键连接。
  5. 如权利要求4所述的用于航空动力的螺旋桨传动系统，其特征在于：所述挠性盘的盘状部分的外圈与所述扭转减振器的加持盘的外圈固定连接。
  6. 如权利要求5所述的用于航空动力的螺旋桨传动系统，其特征在于：所述挠性盘的盘状部分的外圈与所述扭转减振器的加持盘的外圈铆接连接。
  7. 如上述任一项权利要求所述的用于航空动力的螺旋桨传动系统，其特征在于：所述过载离合器的盘毂芯后端端面被固定在所述螺旋桨轴上的轴套轴向 限位。
  8. 如上述任一项权利要求所述的用于航空动力的螺旋桨传动系统，其特征在于：所述螺旋桨轴的用于连接螺旋桨的一端设置有轴肩，所述轴肩处设置有隔离环，所述隔离环对所述扭转减振器的盘毂芯的前端面进行轴向限位，所述隔离环与所述轴肩为弧面接触。
  9. 如权利要求8所述的用于航空动力的螺旋桨传动系统，其特征在于：所述隔离环与所述扭转减振器的盘毂芯的前端面之间设置有用于支撑箱体的轴承，所述轴承与所述扭转减振器的盘毂芯的前端面之间设置有衬套。
  10. 如上述任一项权利要求所述的用于航空动力的螺旋桨传动系统，其特征在于：所述扭转减振器的扭转角度为30°。
PCT/CN2021/130017 2020-11-13 2021-11-11 一种用于航空动力的螺旋桨传动系统 WO2022100654A1 (zh)

Priority Applications (2)

Application Number Priority Date Filing Date Title
US18/036,702 US20230391465A1 (en) 2020-11-13 2021-11-11 Propeller transmission system for aircraft powerplant
EP21891174.1A EP4238873A4 (en) 2020-11-13 2021-11-11 PROPELLER TRANSMISSION SYSTEM FOR AVIATION POWER

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN202011265392.6A CN112373675B (zh) 2020-11-13 2020-11-13 一种用于航空动力的螺旋桨传动系统
CN202011265392.6 2020-11-13

Publications (1)

Publication Number Publication Date
WO2022100654A1 true WO2022100654A1 (zh) 2022-05-19

Family

ID=74583580

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2021/130017 WO2022100654A1 (zh) 2020-11-13 2021-11-11 一种用于航空动力的螺旋桨传动系统

Country Status (4)

Country Link
US (1) US20230391465A1 (zh)
EP (1) EP4238873A4 (zh)
CN (1) CN112373675B (zh)
WO (1) WO2022100654A1 (zh)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN112373675B (zh) * 2020-11-13 2022-02-08 重庆宗申航空发动机制造有限公司 一种用于航空动力的螺旋桨传动系统
CN117157231A (zh) * 2022-08-31 2023-12-01 广东逸动科技有限公司 船用推进器及船舶

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB589281A (en) * 1943-07-13 1947-06-17 Robert William Corbitt Improved means for damping torsional vibrations
CN101610949A (zh) * 2007-01-15 2009-12-23 Gif工业研究有限责任公司 飞机螺旋桨传动装置，用于驱动飞机螺旋桨的方法，飞机螺旋桨传动装置轴承的用途和电机的用途
CN204691898U (zh) * 2015-06-05 2015-10-07 重庆宗申动力机械股份有限公司 一种发动机的传动机构
CN106697307A (zh) * 2015-11-16 2017-05-24 Brp传动系有限两合公司 飞行器螺旋桨驱动系统
EP3216700A1 (en) * 2016-03-08 2017-09-13 I.C.P. S.r.l. Propeller propulsion device
CN112373675A (zh) * 2020-11-13 2021-02-19 重庆宗申航空发动机制造有限公司 一种用于航空动力的螺旋桨传动系统

Family Cites Families (14)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US2023690A (en) * 1932-11-25 1935-12-10 Kenneth E Lyman Automatic clutch
US3327693A (en) * 1965-09-21 1967-06-27 Wilton G Lundquist Internal combustion engine scavenging blower and load driving arrangement
JPS59181340U (ja) * 1983-05-20 1984-12-04 不二化学工業株式会社 多板式クラツチ装置
DE19904857A1 (de) * 1999-02-05 2000-08-10 Mannesmann Sachs Ag Hydrodynamischer Drehmomentwandler
JP4573549B2 (ja) * 2004-03-22 2010-11-04 カルソニックカンセイ株式会社 動力伝達装置
US7871091B2 (en) * 2006-02-14 2011-01-18 Honda Motor Co., Ltd. Steering damper apparatus and damper apparatus
KR101241555B1 (ko) * 2006-08-17 2013-03-08 현대자동차주식회사 접착식 밸런스 웨이트
US20100130289A1 (en) * 2007-06-01 2010-05-27 Exedy Corporation Damper mechanism
DE112015000319T5 (de) * 2014-02-28 2016-10-27 Aisin Aw Co., Ltd. Dämpfervorrichtung
US20160258494A1 (en) * 2015-03-05 2016-09-08 Schaeffler Technologies AG & Co. KG Pulley damper with one-way clutch
US9745074B2 (en) * 2015-09-30 2017-08-29 Brp-Powertrain Gmbh & Co Kg Aircraft propeller drive system
US10400874B2 (en) * 2016-03-23 2019-09-03 Toyota Jidosha Kabushiki Kaisha Torque converter having torsional vibration damping device
CN205836529U (zh) * 2016-08-01 2016-12-28 北京汽车动力总成有限公司 一种汽车
CN210978284U (zh) * 2019-07-25 2020-07-10 小仓离合机（东莞）有限公司 一种汽车空调离合器过载装置

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB589281A (en) * 1943-07-13 1947-06-17 Robert William Corbitt Improved means for damping torsional vibrations
CN101610949A (zh) * 2007-01-15 2009-12-23 Gif工业研究有限责任公司 飞机螺旋桨传动装置，用于驱动飞机螺旋桨的方法，飞机螺旋桨传动装置轴承的用途和电机的用途
CN204691898U (zh) * 2015-06-05 2015-10-07 重庆宗申动力机械股份有限公司 一种发动机的传动机构
CN106697307A (zh) * 2015-11-16 2017-05-24 Brp传动系有限两合公司 飞行器螺旋桨驱动系统
EP3216700A1 (en) * 2016-03-08 2017-09-13 I.C.P. S.r.l. Propeller propulsion device
CN112373675A (zh) * 2020-11-13 2021-02-19 重庆宗申航空发动机制造有限公司 一种用于航空动力的螺旋桨传动系统

Non-Patent Citations (1)

* Cited by examiner, † Cited by third party
Title
See also references of EP4238873A4 *

Also Published As

Publication number Publication date
EP4238873A1 (en) 2023-09-06
CN112373675A (zh) 2021-02-19
EP4238873A4 (en) 2024-04-24
US20230391465A1 (en) 2023-12-07
CN112373675B (zh) 2022-02-08

Similar Documents

Publication Publication Date Title
WO2022100654A1 (zh) 一种用于航空动力的螺旋桨传动系统
CN109944906B (zh) 基于磁流变液体的半主动控制变惯量双质量飞轮
JP4945831B2 (ja) 複合伝動装置
JPS6134021B2 (zh)
WO2022100653A1 (zh) 一种用于航空动力的传动系统
US4925409A (en) Torsional damper for marine drive unit
WO2022100657A1 (zh) 一种用于航空动力的传动系统
CN102312951B (zh) 引擎侧盖板直连引擎曲轴的阻尼器组件及具有其的动力系
US10006517B2 (en) Torsional vibration damper with planetary gear enhanced by inertial mass
WO2021109015A1 (zh) 车辆用减振器及车辆
JP2009115262A (ja) フライホイール
CN110285207A (zh) 适于航空发动机减速箱的减振装置
CN212028426U (zh) 车辆用减振器及车辆
US1380823A (en) Clutch for turbine-driven geared propeller-shafts
US3686895A (en) Damped shaft coupling
JP5179813B2 (ja) ハイブリッド車用のリミッタ付きダンパの取付け構造
US2623409A (en) Transmission vibration dampener
CN215444918U (zh) 扭矩减振装置和混合动力车辆
US2427505A (en) Vibration damper
CN214304941U (zh) 一种过载减振器
US2961892A (en) Power transmission device
JP4326414B2 (ja) トルクリミッタ装置の製造方法、及びトルクリミッタ装置の組み付け方法
US1815621A (en) Supercharger drive
CN217761885U (zh) 一种可变阻尼器
CN113108016B (zh) 多级橡胶扭转减振器

Legal Events

Date Code Title Description
121 Ep: the epo has been informed by wipo that ep was designated in this application

Ref document number: 21891174

Country of ref document: EP

Kind code of ref document: A1

ENP Entry into the national phase

Ref document number: 2021891174

Country of ref document: EP

Effective date: 20230531

NENP Non-entry into the national phase

Ref country code: DE