WO2022036985A1 - 刹车冷却风扇装置 - Google Patents

刹车冷却风扇装置 Download PDF

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Publication number
WO2022036985A1
WO2022036985A1 PCT/CN2020/140636 CN2020140636W WO2022036985A1 WO 2022036985 A1 WO2022036985 A1 WO 2022036985A1 CN 2020140636 W CN2020140636 W CN 2020140636W WO 2022036985 A1 WO2022036985 A1 WO 2022036985A1
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WIPO (PCT)
Prior art keywords
gear
cooling fan
shaft
wheel
transmission assembly
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PCT/CN2020/140636
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English (en)
French (fr)
Inventor
张奇
王晓梅
刘杰
廖军辉
陆伟铭
张志强
Original Assignee
中国商用飞机有限责任公司
中国商用飞机有限责任公司上海飞机设计研究院
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Application filed by 中国商用飞机有限责任公司, 中国商用飞机有限责任公司上海飞机设计研究院 filed Critical 中国商用飞机有限责任公司
Publication of WO2022036985A1 publication Critical patent/WO2022036985A1/zh

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    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C25/00—Alighting gear
    • B64C25/32—Alighting gear characterised by elements which contact the ground or similar surface 
    • B64C25/42—Arrangement or adaptation of brakes
    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B60—VEHICLES IN GENERAL
    • B60T—VEHICLE BRAKE CONTROL SYSTEMS OR PARTS THEREOF; BRAKE CONTROL SYSTEMS OR PARTS THEREOF, IN GENERAL; ARRANGEMENT OF BRAKING ELEMENTS ON VEHICLES IN GENERAL; PORTABLE DEVICES FOR PREVENTING UNWANTED MOVEMENT OF VEHICLES; VEHICLE MODIFICATIONS TO FACILITATE COOLING OF BRAKES
    • B60T5/00—Vehicle modifications to facilitate cooling of brakes

Definitions

  • the invention relates to a cooling device used for rapidly cooling the wheel brakes of an aircraft in the phase of ground taxiing, which is used for the rapid dispatch of the aircraft to pass stations in the operation phase, and belongs to the field of airborne brake cooling fan devices.
  • One method is to install an on-board brake cooling fan driven by a high-speed motor on the main landing gear axle and main wheel of the aircraft.
  • Typical examples are Airbus A320 and A350.
  • the on-board brake cooling fan cools the brakes.
  • the on-board brake cooling fan can also be turned on to cool the brakes.
  • the advantage of this method is that it makes full use of the time during the taxiing phase, and can achieve rapid brake cooling without ground auxiliary cooling equipment.
  • variable frequency power supply of the fan motor may also need to add an additional frequency modulation step-down controller, which will also increase the weight of the aircraft;
  • control of the brake fan also requires additional corresponding control boxes and signal leads, which increases the brake control system.
  • Complexity third, the fan motor occupies the space in the axle of the landing gear, which increases the difficulty for the arrangement of the wheel speed sensor and the tire pressure sensor.
  • ground auxiliary equipment to cool down, such as an air-conditioning vehicle.
  • the ground maintenance personnel When the aircraft lands and taxis to the apron and stops, the ground maintenance personnel tow the air-conditioning vehicle to the position of the main wheel of the aircraft, and align the air outlet of the air-conditioning vehicle with the wheel. The rim is cooled.
  • the benefit of this approach is that there is no need to increase the complexity of the braking system.
  • the main disadvantages are as follows: First, the ground auxiliary equipment can be used to cool down only when the aircraft is stable and stationary. The ground auxiliary equipment cannot be used to cool down during the taxiing phase, and the cooling efficiency is not as good as that of the airborne brake cooling fan; Second, it increases the operating cost of the airport. , because the airport needs to prepare a large number of air-conditioned vehicles, the storage, maintenance and scheduling of air-conditioned vehicles will cost a lot.
  • the purpose of the present invention is to solve the above-mentioned technical problems.
  • the invention provides a brake cooling fan device, which brakes a wheel of an aircraft landing gear.
  • the brake cooling fan device includes a mechanical power device and a cooling fan assembly.
  • the cooling fan assembly includes a fan rotating shaft and a cooling fan fixedly mounted on the fan rotating shaft.
  • the mechanical power device drives the cooling fan assembly to run, so that the cooling fan rotates with the fan shaft.
  • the mechanical power device includes the wheel of the aircraft and the variable speed transmission assembly, the variable speed transmission assembly is connected between the wheel and the cooling fan assembly, the input end of the variable speed transmission assembly is drivably connected to the wheel, and the output end of the variable speed transmission assembly can It is drivingly connected to the cooling fan assembly to transmit the rotational power of the wheel to the cooling fan assembly through the variable speed transmission assembly.
  • the output rotational speed of the variable-speed transmission assembly is greater than the input rotational speed of the variable-speed transmission assembly.
  • variable speed transmission assembly is a gear set variable speed transmission assembly
  • gear set variable speed transmission assembly includes:
  • the output gear at the output end is driveably connected to the input gear, and the input gear transmits its rotational power to the output gear through a speed increase, so that the rotational speed of the output gear is greater than the rotational speed of the input gear.
  • the gear set variable speed transmission assembly is a planetary gear set variable speed transmission assembly
  • the input gear is a ring gear
  • the output gear is a sun gear
  • the planetary gear set variable speed transmission assembly further includes: Multiple planetary gears.
  • the ring gear includes ring gear teeth on its inner circumference
  • the sun gear includes sun gear teeth on its outer edge
  • the planet gear includes planet gear teeth on its outer edge.
  • the planetary gear set transmission assembly also includes:
  • the sun gear shaft at the center of the sun gear, the sun gear is fixedly mounted on the sun gear shaft;
  • the planetary gear fixed shaft at the center of each planetary gear is rotatably mounted on the planetary gear fixed shaft.
  • the sun gear is coaxially located on the rotation axis of the ring gear
  • the planet gear is meshed between the ring gear and the sun gear
  • the ring gear teeth, the planet gear teeth and the sun gear teeth are configured so that the rotation speed of the sun gear is greater than the rotation speed of the ring gear.
  • the wheel is rotatably installed on the wheel shaft which is fixedly installed relative to the landing gear of the aircraft.
  • the ring gear is coaxially fixed to the wheel
  • the rotating shaft of the sun gear is rotatably fixed relative to the wheel shaft
  • the fixed shaft of the planetary gear is fixed relative to the wheel shaft.
  • the planetary gear set variable speed transmission assembly further includes:
  • the planet carrier is fixedly connected to the wheel shaft, and one end of the fixed shaft of the planet wheel is fixedly connected to the planet carrier;
  • the bearing is fixedly installed in the axle
  • the rotating shaft of the sun gear includes a shaft output end and a shaft mounting end opposite to the shaft output end
  • the shaft mounting end of the sun gear rotating shaft is supported on the bearing, so that the rotating shaft of the sun gear can rotate relative to the axle
  • the sun gear The shaft output end of the rotating shaft is connected to the fan rotating shaft, so that the sun gear drives the cooling fan to rotate.
  • the ring gear is connected to the wheel through a key.
  • the planet carrier is fixed to the end face of the axle by means of fasteners.
  • the fastener includes a plurality of bolts.
  • the contact surface between the ring gear and the wheel is coated with thermally conductive silicone grease.
  • the ring gear is connected to the bead seat of the wheel.
  • the output rotational speed of the variable-speed transmission assembly is at least 10 times the input rotational speed of the variable-speed transmission assembly.
  • the brake cooling fan device further comprises a fan cover covering the cooling fan, and the cooling fan is an axial cooling fan.
  • the fan cover is an air collecting cover and is connected to the ring gear through a plurality of screws, and a rubber pad is filled between the air collecting cover and the ring gear.
  • the technical effect of the present invention is to provide a passive cooling device for rapidly cooling the wheel brakes of the aircraft during the taxiing phase on the ground, which is used for the aircraft to quickly pass the station during the operation phase and improve the dispatching efficiency of the aircraft.
  • the brake cooling fan device of the present invention can amplify the rotational speed of the wheel when the aircraft decelerates and taxis at a low speed by a certain multiple, and then drives the axial cooling fan to rotate at a high speed to generate strong wind, thereby realizing the rapid cooling of the wheel brake.
  • FIG. 1 is a schematic perspective view of a brake cooling fan device according to the present invention.
  • Fig. 2 is a perspective view of the air collecting hood in the brake cooling fan device according to the present invention
  • FIG 3 is a schematic perspective view of a cooling fan assembly in the brake cooling fan device according to the present invention.
  • Planetary gear set variable speed transmission assembly (variable transmission assembly, gear set variable speed transmission assembly), including:
  • 16-Sun gear shaft including shaft output end and shaft installation end;
  • 2- Cooling fan assembly including:
  • FIG. 1 shows a brake cooling fan device according to a preferred embodiment of the present invention, wherein the brake is used for the wheel (not shown in the figure) of the aircraft landing gear, and the wheel can rotate It is mounted on the axle (not shown in the figure) fixedly mounted relative to the landing gear of the aircraft.
  • the conventional on-board brake cooling fan device includes a mechanical power device and a cooling fan assembly 2.
  • the cooling fan assembly 2 includes a fan shaft 22 and a cooling fan 21 fixedly mounted on the fan shaft 22.
  • the mechanical power device drives the cooling fan assembly 2 to operate, so that the The cooling fan 21 rotates with the fan shaft 22 to cool the brake.
  • the power of the mechanical power unit is the power supply of the aircraft. According to the present invention, the power of the mechanical power device is passive power.
  • the passive mechanical power device includes a wheel of the aircraft and a variable-speed transmission assembly, the variable-speed transmission assembly is connected between the wheel and the cooling fan assembly 2, and the input end of the variable-speed transmission assembly is connected to the wheel to rotate the wheel. It is transmitted to the input end of the variable speed transmission assembly, and the output end of the variable speed transmission assembly is connected to the cooling fan assembly 2, so as to input the rotational power of the wheel into the variable speed transmission assembly through the input end, and the variable speed transmission assembly increases the rotation of the input by increasing the speed.
  • the motion is transmitted to the output end and thus to the cooling fan assembly 2, whereby the output speed of the variable speed transmission assembly is greater than the input speed of the variable speed transmission assembly, that is, the rotation speed of the cooling fan 21 of the cooling fan assembly 2 is made greater than the rotation of the wheels speed.
  • the speed change transmission assembly adopts a gear set speed change transmission assembly
  • the gear set speed change transmission assembly includes an input gear at the input end and an output gear at the output end.
  • the input gear is driveably connected to the wheel, so that the wheel rotates synchronously with the input gear, the input gear is driveably connected to the output gear through the speed increase, and the input gear transmits its rotational power to the output gear through the speed increase, so that the output gear is greater than the speed of the input gear.
  • the gear set variable speed transmission assembly is the planetary gear set variable speed transmission assembly 1, that is, the gear set adopts a planetary gear set, and through the planetary gear set, the rotational speed of the input gear is transmitted to the output gear after the speed increase.
  • the planetary gear set transmission assembly 1 includes a ring gear 11 constituting an input gear, a sun gear 13 constituting an output gear, and a plurality of planetary gears 12 for increasing speed.
  • the ring gear 11 is an internal ring gear, that is, it has ring gear teeth on the inner circumference of the ring gear 11
  • the sun gear 13 is an external gear, that is, it has sun gear teeth on the outer circumference of the sun gear 13
  • the planetary gear 12 There are a plurality of them, three in the embodiment shown in FIG. 1 , and the planetary gears 12 are also external gears, that is, the planetary gears 12 have planetary gear teeth on the outer circumference.
  • the planetary gear set transmission assembly 1 also includes a rotation axis at the center of the ring gear 11 , a sun gear rotating shaft 16 at the center of the sun gear 13 , and a planetary gear fixed shaft 15 at the center of each planetary gear 12 .
  • the ring gear 11 rotates around the rotation axis;
  • the sun gear 13 is fixedly mounted on the sun gear shaft 16, so that the sun gear 13 rotates together with the sun gear shaft 16;
  • the planetary gear 12 is rotatably mounted on the planetary gear fixed shaft 15, so that the planetary gear
  • the wheel 12 rotates around the fixed axis 15 of the planetary wheel.
  • the sun gear 13 and the ring gear 11 are coaxially installed, the planetary gear 12 is meshed between the ring gear 11 and the sun gear 13, the ring gear teeth and the planetary gear teeth mesh and roll with each other, the planetary gear teeth and the sun gear teeth mesh and roll with each other, whereby, the teeth of the ring gear, the planet gears and the sun gear are configured such that the rotational speed of the sun gear 13 is greater than the rotational speed of the ring gear 11 , in particular, the teeth of the ring gear, the planet gears and the sun gear teeth are configured such that the sun gear 13
  • the rotational speed of the ring gear is at least 10 times the rotational speed of the ring gear 11 .
  • the ring gear 11 is coaxially fixed to the wheel, so that the ring gear 11 and the wheel rotate synchronously and coaxially.
  • the ring gear 11 is connected to the wheel through a key; in one embodiment, the ring gear 11 is connected to the bead seat of the wheel, and thermally conductive silicone grease is applied to the contact surface between the ring gear 11 and the bead seat.
  • the sun gear rotating shaft 16 is rotatably installed relative to the wheel shaft, so that the sun gear rotating shaft 16 rotates together with the sun gear 13 , and the rotational power of the sun gear 13 is output through the sun gear rotating shaft 16 .
  • the planetary gear set transmission assembly 1 further includes a bearing 17, the bearing 17 is fixedly installed in the axle, the sun gear rotating shaft 16 includes a shaft output end and a shaft mounting end opposite to the shaft output end, the sun gear rotating shaft 16 The shaft mounting end of the shaft is installed in the bearing 17, so that the sun gear shaft 16 can rotate relative to the wheel shaft. The rotational power of the sun gear 13 is output through the shaft output end.
  • the planetary gear fixed shaft 15 is fixedly installed relative to the wheel shaft.
  • the planetary gear set transmission assembly 1 further includes a planetary carrier 14, the planetary carrier 14 is fixedly connected to the wheel shaft, one end of the planetary gear fixed shaft 15 is fixedly connected to the planetary carrier 14, and the planetary gear 12 is rotatably mounted on the planetary gear fixed shaft. 15 , so that the planetary wheel 12 can rotate relative to the fixed axis 15 of the planetary wheel.
  • the rotational power of the wheel is input to the planetary gear set speed change transmission assembly 1 through the ring gear 11, and is transmitted from the sun gear of the planetary gear set speed change transmission assembly 1 through the meshing of the ring gear 11, the planetary gear 12 and the sun gear 13 with each other.
  • the rotation shaft 16 outputs, and the rotation speed of the rotation shaft 16 of the sun gear is greater than the rotation speed of the ring gear 11 through a set of planetary gears 12 meshed between the ring gear 11 and the sun gear 13 .
  • the planet carrier 14 is fixed to the end face of the axle by means of fasteners. In one embodiment, the planet carrier 14 is fixed to the end face of the axle of the landing gear through a plurality of bolts.
  • the brake cooling fan device further includes a fan cover 3 covering the cooling fan 21 .
  • the fan cover 3 is a wind collecting cover 31 to gather wind.
  • the wind collecting cover 31 is connected to the ring gear 11 through a plurality of screws, and a rubber gasket is filled between the wind collecting cover 31 and the ring gear 11 for buffering and sealing.
  • the planetary gear set transmission assembly 1 is mainly composed of a ring gear 11, a planetary gear 12, a sun gear 13 and a planetary carrier 14.
  • the planet carrier 14 is fixedly connected to the end face of the aircraft landing gear axle through bolts, and is a fixed part in the planetary gear set speed change transmission assembly 1.
  • the ring gear 11 is connected with the wheel through a key, and the contact surface between the ring gear 11 and the wheel is coated with thermally conductive silicone grease.
  • One end of the sun gear 13 is connected to the bearing 17 in the axle of the landing gear through the fixed sun gear rotating shaft 16, and the bearing 17 is fixed in the axle.
  • the wind collecting hood 31 is connected with the gear ring 11 by screws, and the air collecting hood 31 and the gear ring 11 are buffered and sealed by a rubber gasket.
  • the axial cooling fan assembly 2 is mainly composed of a cooling fan 21 and a fan shaft 22.
  • the fan shaft 22 is fixedly connected to the center of the sun gear 13, that is, fixedly connected to the sun gear shaft 16, and the sun gear 13 drives the fan shaft 22 to rotate.
  • the main engine wheel speed is generally 2000-3000RPM when the aircraft is landing and rolling, and the wheel speed is generally 300RPM when the aircraft is taxiing at low speed. If the cooling fan 21 is directly driven by the wheel to cool the wheel brake, the fan speed is too low to have a cooling effect.
  • the brake cooling fan 21 needs to have a rotational speed of more than 3000 RPM to have a cooling effect.
  • the wheel speed is amplified several times and transmitted to the axial flow cooling fan 21, so that the cooling fan 21 rotates at a high speed, generating high-speed, high-pressure and strong axial wind, so as to achieve the effect of forced convection cooling by wheel braking.
  • the ring gear 11 of the planetary gear set speed change transmission assembly 1 is fixedly connected to the wheel, and acts as a driving element to drive the planetary wheel 12 to rotate. Since the planetary carrier 14 is fixed to the axle of the landing gear, the planetary carrier 14 is a fixed part, and the planetary wheel 12 rotates on a fixed axis at this time, and drives the sun gear 13 to rotate.
  • One end of the sun gear shaft 16 is supported on the bearing 17 for free rotation, and the other end is fixed to the fan shaft 22 of the axial cooling fan 21 .
  • the sun gear shaft 16 drives the cooling fan 21 to rotate at high speed.
  • the planetary gear set variable speed transmission assembly 1 can achieve a certain multiple of rotation speed amplification, which can reach more than 10 times, so that the rotation speed of the brake cooling fan 21 can reach more than 14,000 RPM when the aircraft is rolling, and the fan speed can also reach more than 3,000 RPM when the aircraft is taxiing at a low speed. Fan speed requirements.
  • the present invention is equivalent to an active fan of the current motor-driven brake cooling fan 21 structure, cancels the fan motor and the control and power distribution system to form a passive fan, and can achieve a single-wheel weight reduction of about 5kg;
  • the planetary gear mechanism is used to amplify the rotational speed of the wheel to drive the cooling fan 21 to achieve a cooling effect similar to that of an active fan;
  • the passive fan of the present invention does not require the aircraft to provide a power supply and a fan control system, which reduces the risks of electromagnetic compatibility, high-intensity radiation and lightning strikes. Difficulty of operation;
  • the ring gear of the brake cooling fan device is in direct contact with the wheel, which can conduct heat through the metal to conduct the heat at the bead seat, which increases the heat dissipation area of the wheel in disguised form.
  • the present invention can amplify the rotational speed of the wheel several times, and then drive the axial cooling fan 21 to rotate at a high speed to generate strong axial wind to achieve the effect of forced convection cooling by the wheel brake.
  • the brake cooling fan device of the present invention does not need to be additionally equipped with a high-speed motor-driven fan, so there is no problem of heat generated by the motor itself, and the aircraft does not need to provide power and fan control. system.
  • the planetary gear set can quickly transmit the heat of the bead seat of the machine and help dissipate heat.

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  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Transportation (AREA)
  • General Details Of Gearings (AREA)
  • Braking Arrangements (AREA)
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Abstract

一种刹车冷却风扇装置，刹车用于飞机起落架的机轮，刹车冷却风扇装置包括机械动力装置和冷却风扇组件(2)，冷却风扇组件(2)包括风扇转轴(22)和固定地安装到风扇转轴(22)上的冷却风扇(21)，机械动力装置驱动冷却风扇组件(2)运行，使冷却风扇(21)随风扇转轴(22)旋转。其中，机械动力装置包括飞机的机轮和变速传动组件(1)，变速传动组件(1)连接在机轮与冷却风扇组件(2)之间，变速传动组件(1)的输入端可传动地连接于机轮，变速传动组件(1)的输出端可传动地连接于冷却风扇组件(2)，以将机轮的旋转动力通过变速传动组件(1)传递到冷却风扇组件(2)。其中，变速传动组件(1)的输出转速大于变速传动组件(1)的输入转速。该刹车冷却风扇装置使得飞机在运营阶段快速过站，能够提高飞机派遣效率。

Description

刹车冷却风扇装置 技术领域
本发明涉及一种用于飞机在地面滑行阶段给机轮刹车快速降温的冷却装置，用于飞机在运营阶段快速派遣过站，属于飞机机载刹车冷却风扇装置的领域。
背景技术
随着民航市场的发展，客流量日益增大，航空公司对于飞机过站派遣效率提出了越来越高的要求，而机轮刹车温度是限制飞机过站时间的一个重要因素。提高机轮刹车的降温效率，能极大缩短飞机在停机坪等待降温时间，从而提高飞机派遣效率。
目前，民用飞机或大型运输机实现快速过站的方法主要分为两种：
一种方法是在飞机主起落架轮轴和主机轮上加装由高速电机驱动的机载刹车冷却风扇，典型的例子是空客的A320、A350，飞机着陆后，在滑行阶段飞行员就可以手动开启机载刹车冷却风扇给刹车降温，在停机等待过站的阶段，只要飞机通电，也可以开启机载刹车冷却风扇给刹车降温。这种方法的好处是充分利用了滑行阶段的时间，并且无需地面辅助降温设备即可实现刹车快速降温，缺点主要有：一是给飞机额外增加了不小的重量和电源负载，有些飞机提供给风扇电机的变频电源可能还需要增加额外的调频降压控制器，这也会增加飞机的重量；二是刹车风扇的控制还需要额外增加相应的控制盒和信号引线，这增加了刹车控制系统的复杂性；三是风扇电机占据了起落架轮轴内的空间，对于机轮轮速传感器和胎压传感器的布置增加了难度。
另一种方法是使用地面辅助设备降温，比如空调车等，当飞机着陆滑行至停机坪并刹停后，地面维护人员将空调车拖至飞机主机轮位置，将空调车吹风口对准机轮轮辋实施降温。这种方法的好处是不必增加刹车系统的复杂性。缺点主要有：一是只有当飞机挺稳静止后才可以使用地面辅助设备实施降温，滑行阶段不能就使用地面辅助设备进行降温，降温效率不如机载刹车冷却风扇；二是增加了机场的运营成本，因为机场需要准备大量的空调车，空调车的储存、 维护和调度都会花费很大成本。
发明内容
为此，本发明的目的是解决上述的技术问题。
本发明提供一种刹车冷却风扇装置，刹车用于飞机起落架的机轮，刹车冷却风扇装置包括机械动力装置和冷却风扇组件，冷却风扇组件包括风扇转轴和固定地安装到风扇转轴上的冷却风扇，机械动力装置驱动冷却风扇组件运行，使冷却风扇随风扇转轴旋转。其中，机械动力装置包括飞机的机轮和变速传动组件，变速传动组件连接在机轮与冷却风扇组件之间，变速传动组件的输入端可传动地连接于机轮，变速传动组件的输出端可传动地连接于冷却风扇组件，以将机轮的旋转动力通过变速传动组件传递到冷却风扇组件。其中，变速传动组件的输出转速大于变速传动组件的输入转速。
较佳地，在刹车冷却风扇装置的上述技术方案的基础上，变速传动组件为齿轮组变速传动组件，齿轮组变速传动组件包括：
在输入端的输入齿轮，输入齿轮可传动地连接于机轮，使得机轮驱动输入齿轮同步地旋转；以及
在输出端的输出齿轮，输出齿轮可传动地连接于输入齿轮，输入齿轮将其旋转动力通过增速传递到输出齿轮，使得输出齿轮的转速大于输入齿轮的转速。
较佳地，在刹车冷却风扇装置的上述技术方案的基础上，齿轮组变速传动组件为行星齿轮组变速传动组件，输入齿轮是齿圈，输出齿轮是太阳轮，行星齿轮组变速传动组件还包括多个行星轮。其中，齿圈包括在其内周的齿圈齿，太阳轮包括在其外缘的太阳轮齿，行星轮包括在其外缘的行星轮齿。行星齿轮组变速传动组件还包括：
在齿圈的中心的旋转轴线；
在太阳轮的中心的太阳轮转轴，太阳轮固定地安装在太阳轮转轴上；
在各行星轮的中心的行星轮固定轴，行星轮可旋转地安装在行星轮固定轴上。
其中，太阳轮同轴地位于齿圈的旋转轴线，行星轮啮合在齿圈与太阳轮 之间，齿圈齿、行星轮齿和太阳轮齿构造成使得太阳轮的转速大于齿圈的转速。
在刹车冷却风扇装置的上述技术方案的基础上，机轮可旋转地安装在相对飞机起落架固定安装的轮轴上。其中，齿圈同轴地固定于机轮，太阳轮转轴相对轮轴可旋转地固定，行星轮固定轴相对轮轴固定。
较佳地，在刹车冷却风扇装置的上述技术方案的基础上，行星齿轮组变速传动组件还包括：
行星架，行星架固定地连接于轮轴，行星轮固定轴的一端固定地连接于行星架；
轴承，轴承固定地安装在轮轴内，太阳轮转轴包括轴输出端和与轴输出端相对的轴安装端，太阳轮转轴的轴安装端支承于轴承，使得太阳轮转轴能够相对轮轴旋转，太阳轮转轴的轴输出端连接于风扇转轴，使太阳轮驱动冷却风扇旋转。
较佳地，在刹车冷却风扇装置的上述技术方案的基础上，齿圈通过键与机轮连接。行星架通过紧固件固定于轮轴的端面。优选地，紧固件包括多个螺栓。
较佳地，在刹车冷却风扇装置的上述技术方案的基础上，齿圈与机轮之间的接触面涂敷导热硅脂胶。
较佳地，在刹车冷却风扇装置的上述技术方案的基础上，齿圈连接于机轮的胎圈座。
针对本发明的刹车冷却风扇装置，变速传动组件的输出转速至少是变速传动组件的输入转速的10倍。
针对本发明的刹车冷却风扇装置，刹车冷却风扇装置还包括覆盖冷却风扇的风扇罩，冷却风扇为轴流冷却风扇。
优选地，针对本发明的刹车冷却风扇装置，风扇罩为聚风罩，并通过多个螺钉连接于齿圈，聚风罩与齿圈之间填充橡胶垫。
由此，本发明的技术效果是：提供一种用于飞机在地面滑行阶段给机轮刹车快速降温的无源降温装置，用于飞机在运营阶段快速过站，提高飞机派遣效率。通过本发明的刹车冷却风扇装置，可以将飞机减速滑跑和低速滑行时机轮转动的转速放大一定倍数，然后驱动轴流冷却风扇高速旋转，产生强风， 从而实现给机轮刹车快速降温。
附图说明
图1是根据本发明的刹车冷却风扇装置的立体示意图；
图2是根据本发明的刹车冷却风扇装置中的聚风罩的立体示意图；
图3是根据本发明的刹车冷却风扇装置中的冷却风扇组件的立体示意图。
图中的附图标记在技术方案和实施例中的列表：
1-行星齿轮组变速传动组件(变速传动组件，齿轮组变速传动组件)，包括：
11-齿圈，包括齿圈齿；
12-行星轮，包括行星轮齿；
13-太阳轮，包括太阳轮齿；
14-行星架，
15-行星轮固定轴；
16-太阳轮转轴，包括轴输出端和轴安装端；
17-轴承；
2-冷却风扇组件，包括：
21-冷却风扇；
22-风扇转轴；
3-风扇罩，包括；
31-聚风罩。
具体实施方式
下面结合附图和实施例来进一步描述本发明，从而更清楚地连接本发明的发明原理和有益的技术效果。
如图1所示，其示出了根据本发明的一个较佳实施例，一种刹车冷却风扇装置，其中的刹车用于飞机起落架的机轮(图中未示出)，机轮可旋转地安装在相对飞机起落架固定安装的轮轴(图中未示出)上。传统机载刹车冷却风 扇装置包括机械动力装置和冷却风扇组件2，冷却风扇组件2包括风扇转轴22和固定地安装到风扇转轴22上的冷却风扇21，机械动力装置驱动冷却风扇组件2运行，使冷却风扇21随风扇转轴22旋转，从而给刹车降温。机械动力装置的动力为飞机的电源。而根据本发明，机械动力装置的动力为无源动力。该无源的机械动力装置包括飞机的机轮和变速传动组件，变速传动组件连接在机轮与冷却风扇组件2之间，变速传动组件的输入端连接于机轮，以将机轮的旋转运动传递到变速传动组件的输入端，变速传动组件的输出端连接于冷却风扇组件2，以将机轮的旋转动力通过输入端输入到变速传动组件内，变速传动组件通过增速将该输入的旋转运动传递到输出端，从而传递到冷却风扇组件2，由此，变速传动组件的输出转速大于变速传动组件的输入转速，即，使得冷却风扇组件2的冷却风扇21的旋转速度大于机轮的旋转速度。
在本发明中，变速传动组件采用齿轮组变速传动组件，齿轮组变速传动组件包括在输入端的输入齿轮和在输出端的输出齿轮。输入齿轮可传动地连接于机轮，使得机轮与输入齿轮同步地旋转，输入齿轮通过增速可传动地连接于输出齿轮，输入齿轮将其旋转动力通过增速传递到输出齿轮，使得输出齿轮的转速大于输入齿轮的转速。在图1所示的实施例中，齿轮组变速传动组件为行星齿轮组变速传动组件1，即齿轮组采用行星齿轮组，通过行星齿轮组，使得输入齿轮的转速通过增速后传递到输出齿轮。行星齿轮组变速传动组件1包括构成输入齿轮的齿圈11、构成输出齿轮的太阳轮13以及用来增速的多个行星轮12。
如图1所示，齿圈11是内齿圈，即在齿圈11的内周具有齿圈齿，太阳轮13为外齿轮，即在太阳轮13的外周上具有太阳轮齿，行星轮12有多个，在图1所示的实施例中为三个，行星轮12也是外齿轮，即在行星轮12的外周上具有行星轮齿。除了齿轮，行星齿轮组变速传动组件1还包括在齿圈11的中心的旋转轴线、在太阳轮13的中心的太阳轮转轴16和在各行星轮12的中心的行星轮固定轴15。齿圈11绕旋转轴线旋转；太阳轮13固定地安装在太阳轮转轴16上，使太阳轮13与太阳轮转轴16一起旋转；行星轮12可旋转地安装在行星轮固定轴15上，使得行星轮12绕行星轮固定轴15旋转。其中，太阳轮13与齿圈11同轴安装，行星轮12啮合在齿圈11与太阳轮13之间， 齿圈齿与行星轮齿彼此啮合滚动，行星轮齿与太阳轮齿彼此啮合滚动，由此，齿圈齿、行星轮齿和太阳轮齿构造成使得太阳轮13的转速大于齿圈11的转速，尤其是，齿圈齿、行星轮齿和太阳轮齿的齿数构造使得太阳轮13的转速至少是齿圈11的转速的10倍。
齿圈11同轴地固定于机轮，使得齿圈11与机轮同步同轴旋转。齿圈11通过键与机轮连接；在一实施例中，齿圈11连接于机轮的胎圈座，并在齿圈11与胎圈座之间的接触面涂敷导热硅脂胶。
太阳轮转轴16相对轮轴可旋转地安装，使得太阳轮转轴16与太阳轮13一起旋转，太阳轮13的旋转动力通过太阳轮转轴16输出。在一实施例中，行星齿轮组变速传动组件1还包括轴承17，轴承17固定地安装在轮轴内，太阳轮转轴16包括轴输出端和与轴输出端相对的轴安装端，太阳轮转轴16的轴安装端安装在轴承17内，使得太阳轮转轴16能够相对轮轴旋转。而太阳轮13的旋转动力通过轴输出端输出。
行星轮固定轴15相对轮轴固定安装。行星齿轮组变速传动组件1还包括行星架14，行星架14固定地连接于轮轴，行星轮固定轴15的一端固定地连接于行星架14，而行星轮12可旋转地安装在行星轮固定轴15上，使得行星轮12能够相对行星轮固定轴15旋转。由此，机轮的旋转动力通过齿圈11输入到行星齿轮组变速传动组件1，并通过齿圈11、行星轮12和太阳轮13彼此间的啮合而从行星齿轮组变速传动组件1的太阳轮转轴16输出，而且，通过啮合在齿圈11与太阳轮13之间的一组行星轮12，使得太阳轮转轴16的转速大于齿圈11的转速。行星架14通过紧固件固定于轮轴的端面。在一实施例中，行星架14通过多个螺栓固定于起落架轮轴的端面。
如图1－3所示，刹车冷却风扇装置还包括覆盖冷却风扇21的风扇罩3。在一实施例中，该风扇罩3是一聚风罩31，以起到聚拢风的作用。聚风罩31通过多个螺钉连接于齿圈11，聚风罩31与齿圈11之间填充橡胶垫，以进行缓冲和密封。
具体的应用的示例
行星齿轮组变速传动组件1主要由齿圈11、行星轮12、太阳轮13和行 星架14组成。行星架14通过螺栓与飞机起落架轮轴端面固接，在行星齿轮组变速传动组件1中为固定部分，行星轮12绕行星架14上的行星轮固定轴15作定轴转动。齿圈11通过键与机轮连接，齿圈11和机轮接触面涂敷导热硅脂胶，齿圈11在行星齿轮组变速传动组件1中为主动部分，跟随机轮转动。太阳轮13一端通过固接的太阳轮转轴16与起落架轮轴内的轴承17连接，轴承17固定于轮轴内。聚风罩31通过螺钉与齿圈11连接，聚风罩31与齿圈11之间通过橡胶垫而缓冲和密封。轴流冷却风扇组件2主要由冷却风扇21和风扇转轴22组成，风扇转轴22固接于太阳轮13中心位置，即固定地连接于太阳轮转轴16，由太阳轮13带动风扇转轴22旋转。
飞机在着陆滑跑时主机轮转速一般为2000～3000RPM，低速滑行时机轮转速一般为300RPM。若直接由机轮驱动冷却风扇21对机轮刹车进行降温，风扇转速太低，无法起到降温效果。刹车冷却风扇21需要转速达到3000RPM以上才能起到降温效果。
上述示例通过设计行星齿轮转速放大组件，将机轮转速放大数倍传递给轴流冷却风扇21，使得冷却风扇21高速旋转，产生轴向的高速高压强风，实现机轮刹车强制对流降温的效果。
行星齿轮组变速传动组件1的齿圈11与机轮固接，作为主动件，带动行星轮12转动。由于行星架14固定于起落架轮轴，因此行星架14为固定件，行星轮12此时作定轴转动，并带动太阳轮13转动。太阳轮转轴16通过其一端支承于轴承17作自由转动，另一端固结轴流冷却风扇21的风扇转轴22，太阳轮转轴16带动冷却风扇21高速旋转。
行星齿轮组变速传动组件1能实现转速放大一定倍数，能达到10倍以上，使得飞机在着陆滑跑时刹车冷却风扇21的转速高达14000RPM以上，低速滑行时风扇转速也可以到达3000RPM以上，满足刹车风扇的转速要求。
本发明的设计要点：
1、本发明相当于对当前的电机驱动刹车冷却风扇21结构的有源风扇，取消风扇电机及控制和配电系统而形成无源风扇，可实现单轮减重约5kg；
2、利用行星齿轮机构，放大机轮转速用于驱动冷却风扇21，达到与有源 风扇相似的降温效果；
3、相较于有源风扇，本发明的无源风扇无需飞机提供电源和风扇控制系统，减少了电磁兼容、高强度辐射和雷击等风险；驾驶舱无需另外布置风扇控制开关，减小了飞行员操作难易度；
4、刹车冷却风扇装置的齿圈与机轮直接接触，可以通过金属导热，传导出胎圈座处的热量，变相的加大了机轮的散热面积。
本发明通过设计行星齿轮组变速传动组件1，可以将机轮转速放大若干倍，然后驱动轴流冷却风扇21高速旋转，产生轴向的强风，实现机轮刹车强制对流降温的效果。与常见的机载刹车风扇如A320、A350飞机的刹车风扇显著不同，本发明的刹车冷却风扇装置无需额外配备高速电机驱动风扇，因此没有电机本身产生热量的问题，也无需飞机提供电源和风扇控制系统。
由于行星齿轮组变速传动组件1中齿圈11直接与胎圈座下部相连，连接部位涂抹导热硅脂，行星齿轮组可以快速传导机轮胎圈座热量并帮助散热。
以上内容描述了本发明的具体实施方式，但是本领域的技术人员应当理解，这些仅是举例说明，本发明的保护范围是由所附权利要求书限定。本领域的技术人员在不背离本发明的原理和实质的前提下，可以对这些实施方式作出多种变更或修改，这些变更和修改均落入本发明的保护范围。
以上实施例中的各个特征还可以根据本发明原理在合理范围内作任意组合，这种组合也落入本发明的保护范围内。

Claims (12)

  1. 一种刹车冷却风扇装置，所述刹车用于飞机起落架的机轮，所述刹车冷却风扇装置包括机械动力装置和冷却风扇组件(2)，所述冷却风扇组件(2)包括风扇转轴(22)和固定地安装到所述风扇转轴(22)上的冷却风扇(21)，所述机械动力装置驱动冷却风扇组件(2)运行，使所述冷却风扇(21)随所述风扇转轴(22)旋转，其特征在于，
    所述机械动力装置包括飞机的机轮和变速传动组件，所述变速传动组件连接在所述机轮与所述冷却风扇组件(2)之间，所述变速传动组件的输入端可传动地连接于所述机轮，所述变速传动组件的输出端可传动地连接于所述冷却风扇组件(2)，以将所述机轮的旋转动力通过所述变速传动组件传递到所述冷却风扇组件(2)，其中，所述变速传动组件的输出转速大于所述变速传动组件的输入转速。
  2. 如权利要求1所述的刹车冷却风扇装置，其特征在于，
    所述变速传动组件为齿轮组变速传动组件，所述齿轮组变速传动组件包括：
    在所述输入端的输入齿轮，所述输入齿轮可传动地连接于所述机轮，使得所述机轮驱动所述输入齿轮同步地旋转；以及
    在所述输出端的输出齿轮，所述输出齿轮可传动地连接于所述输入齿轮，所述输入齿轮将其旋转动力通过增速传递到所述输出齿轮，使得所述输出齿轮的转速大于所述输入齿轮的转速。
  3. 如权利要求2所述的刹车冷却风扇装置，其特征在于，
    所述齿轮组变速传动组件为行星齿轮组变速传动组件(1)，所述输入齿轮是齿圈(11)，所述输出齿轮是太阳轮(13)，所述行星齿轮组变速传动组件(1)还包括多个行星轮(12)；
    其中，所述齿圈(11)包括在其内周的齿圈齿，所述太阳轮(13)包括在其外缘的太阳轮齿，所述行星轮(12)包括在其外缘的行星轮齿；
    所述行星齿轮组变速传动组件(1)还包括：
    在所述齿圈(11)的中心的旋转轴线；
    在所述太阳轮(13)的中心的太阳轮转轴(16)，所述太阳轮(13)固定地安装在所述太阳轮转轴(16)上；
    在各所述行星轮(12)的中心的行星轮固定轴(15)，所述行星轮(12)可旋转地安装在所述行星轮固定轴(15)上；
    其中，所述太阳轮(13)同轴地位于所述齿圈(11)的所述旋转轴线，所述行星轮(12)啮合在所述齿圈(11)与所述太阳轮(13)之间，所述齿圈齿、所述行星轮齿和所述太阳轮齿构造成使得所述太阳轮(13)的转速大于所述齿圈(11)的转速。
  4. 如权利要求3所述的刹车冷却风扇装置，所述机轮可旋转地安装在相对所述飞机起落架固定安装的轮轴上，其特征在于，
    所述齿圈(11)同轴地固定于所述机轮；
    所述太阳轮转轴(16)相对所述轮轴可旋转地固定；
    所述行星轮固定轴(15)相对所述轮轴固定。
  5. 如权利要求4所述的刹车冷却风扇装置，其特征在于，
    所述行星齿轮组变速传动组件(1)还包括：
    行星架(14)，所述行星架(14)固定地连接于所述轮轴，所述行星轮固定轴(15)的一端固定地连接于所述行星架(14)；
    轴承(17)，所述轴承(17)固定地安装在所述轮轴内，所述太阳轮转轴(16)包括轴输出端和与所述轴输出端相对的轴安装端，所述太阳轮转轴(16)的所述轴安装端支承于所述轴承(17)，使得所述太阳轮转轴(16)能够相对所述轮轴旋转，所述太阳轮转轴(16)的所述轴输出端连接于风扇转轴(22)，使太阳轮(13)驱动冷却风扇(21)旋转。
  6. 如权利要求5所述的刹车冷却风扇装置，其特征在于，
    所述齿圈(11)通过键与机轮连接；
    所述行星架(14)通过紧固件固定于所述轮轴的端面。
  7. 如权利要求6所述的刹车冷却风扇装置，其特征在于，
    所述齿圈(11)与所述机轮之间的接触面涂敷导热硅脂胶。
  8. 如权利要求7所述的刹车冷却风扇装置，其特征在于，
    所述齿圈(11)连接于所述机轮的胎圈座。
  9. 如权利要求6所述的刹车冷却风扇装置，其特征在于，
    所述紧固件包括多个螺栓。
  10. 如权利要求1-9中的任何一项所述的刹车冷却风扇装置，其特征在于，
    所述变速传动组件的输出转速至少是所述变速传动组件的输入转速的10倍。
  11. 如权利要求1-9中的任何一项所述的刹车冷却风扇装置，其特征在于，
    所述刹车冷却风扇装置还包括覆盖所述冷却风扇(21)的风扇罩(3)，所述冷却风扇(21)为轴流冷却风扇。
  12. 如权利要求10所述的刹车冷却风扇装置，其特征在于，
    所述风扇罩(3)为聚风罩(31)，并通过多个螺钉连接于齿圈(11)，所述聚风罩(31)与所述齿圈(11)之间填充橡胶垫。
PCT/CN2020/140636 2020-08-17 2020-12-29 刹车冷却风扇装置 WO2022036985A1 (zh)

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