WO2018223748A1 - 涵道风扇 - Google Patents

涵道风扇 Download PDF

Info

Publication number
WO2018223748A1
WO2018223748A1 PCT/CN2018/079749 CN2018079749W WO2018223748A1 WO 2018223748 A1 WO2018223748 A1 WO 2018223748A1 CN 2018079749 W CN2018079749 W CN 2018079749W WO 2018223748 A1 WO2018223748 A1 WO 2018223748A1
Authority
WO
WIPO (PCT)
Prior art keywords
duct
hub shaft
ducted fan
heat dissipation
fan according
Prior art date
Application number
PCT/CN2018/079749
Other languages
English (en)
French (fr)
Inventor
刘若鹏
栾琳
兰水泉
Original Assignee
深圳光启合众科技有限公司
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 深圳光启合众科技有限公司 filed Critical 深圳光启合众科技有限公司
Publication of WO2018223748A1 publication Critical patent/WO2018223748A1/zh

Links

Classifications

    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems
    • B64D33/10—Radiator arrangement
    • 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
    • B64D33/00—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for
    • B64D33/08—Arrangements in aircraft of power plant parts or auxiliaries not otherwise provided for of power plant cooling systems

Definitions

  • the present invention relates to the field of aircraft and, more particularly, to a ducted fan.
  • the problem of cooling and cooling has always been a problem in aircraft engines.
  • the quality of the engine cooling system directly affects the performance and service life of the engine.
  • the general engine cooling system is active cooling, that is, using a cooling fan to blow air through the surface of the heat sink at high speed, taking away the heat from the engine and cooling the engine.
  • the cooling fan is often omitted in order to reduce the weight of the aircraft. Without the high-speed airflow provided by the fan, the cooling efficiency is greatly reduced, which brings serious problems to the design of the aircraft.
  • the radiator of the engine is placed at the entrance of the duct, and it is desirable to carry away the heat by the airflow entering the duct.
  • the air flow rate at the entrance of the duct is limited, which is far from the speed of the airflow after the acceleration of the duct. Cooling with the airflow at the inlet is not very efficient, so it is necessary to increase the volume of the radiator to achieve the required heat dissipation, but this will increase the overall weight of the flight bag and also affect the aesthetics.
  • an object of the present invention is to provide a ducted fan, which is disposed in a ducted fan to dissipate heat by using a high-speed airflow in a ducted fan, thereby significantly improving the heat sink.
  • the ducted fan places the heat dissipation structure on the stationary vane, thereby saving packaging space.
  • the present invention provides a ducted fan comprising: a ducted duct having a central axis, an air inlet and an air outlet respectively located at upper and lower ends of the duct; and a hub shaft disposed at the duct a central axis; a plurality of moving blades disposed on the hub shaft and adjacent to the air inlet, and rotatable with the rotation of the hub shaft; the fixed sleeve, the hub shaft is mounted in the fixed sleeve; a blade, the opposite ends of the stationary blade are respectively connected with the inner wall of the fixing sleeve and the duct, each of the stationary blades is provided with a heat dissipation structure; and the power driving device is disposed in the fixing sleeve and located under the plurality of moving blades, wherein The power drive is coupled to the hub shaft to drive the hub shaft to rotate, and the power drive is coupled to the heat dissipation structure to dissipate heat through the heat dissipation structure.
  • the heat dissipation structure is a heat sink attached to an outer surface of each of the stationary blades, and a heat sink cooling duct is provided in the heat sink.
  • a power drive apparatus includes an engine having an engine cooling circuit therein, an output shaft of the engine coupled to the hub shaft to drive the hub shaft rotation, and an engine cooling line and a fin cooling line Fluidly connected to form a coolant circuit.
  • the heat sink comprises a water chamber and a water chamber communicating via a plurality of heat pipes, wherein the water chamber is in fluid communication with an outlet of the engine cooling line, and the inlet of the water chamber and the engine cooling line Fluid communication.
  • the plurality of heat dissipating tubes are disposed in parallel with each other, and a plurality of heat dissipating fins are further disposed between the adjacent heat dissipating tubes.
  • a water pump is provided at the inlet of the engine cooling circuit to return coolant cooled by the plurality of fins back into the engine cooling line.
  • a thermostat is provided at the outlet of the engine cooling circuit.
  • the plurality of moving blades are equally angularly distributed about the central axis, and the chord of each moving blade forms an angle with the rotating blade horizontal plane.
  • the plurality of stationary vanes are equally angularly distributed about the central axis, and each stationary vane is perpendicular to the cross section of the duct.
  • a fairing is provided at the top end of the hub shaft, and the fairing is located above the plurality of moving blades and rotates in accordance with the rotation of the moving blades.
  • the plurality of fins are fixed to the surfaces of the plurality of stationary vanes by welding, riveting or bolting.
  • the heat sink may be integrally formed with the corresponding stationary blade.
  • the heat dissipating structure is arranged on the static blade of the ducted fan or integrally forms the heat dissipating structure and the static vane, so that the static vane has a heat dissipating function and also has the function of balancing the anti-torque, and the high-speed airflow in the ducted fan passes significantly.
  • the heat dissipation effect on the engine ensures that the temperature of the engine is within the normal operating temperature range, improving the fuel efficiency of the engine and ensuring flight safety;
  • the ducted fan of the present invention places the engine radiator on the stationary vanes of the ducted fan, which significantly reduces the packaging space.
  • FIG. 1 is a schematic structural view of a ducted fan according to an embodiment of the present invention.
  • Figure 2 illustrates a cross-sectional view of the ducted fan of Figure 1 taken along the plane of the central axis;
  • Figure 3 illustrates the manner in which the engine and heat sink are connected in a ducted fan in accordance with one embodiment of the present invention.
  • the ducted fan in accordance with an exemplary embodiment of the present invention is illustrated.
  • the ducted fan includes a duct 1, a hub shaft, a plurality of moving blades 2, a fixed sleeve, a plurality of stator blades 3, and a power driving device 4.
  • the duct 1 is a cylindrical passage having a central axis, and an air inlet and an air outlet are respectively located at the upper end and the lower end of the duct 1, and the hub shaft is coaxially disposed with the duct 1 in the fixed sleeve,
  • the moving blades 2 are disposed on the hub shaft adjacent to the air inlets, wherein all the moving blades 2 are radially arranged around the hub axis and can rotate with the rotation of the hub shaft, and the opposite ends of each of the stationary blades 3 are respectively
  • the fixing sleeve is connected to the inner wall of the duct 1 and is provided with a heat dissipating structure on each of the stationary vanes 3, and the power driving device 4 is located in the fixing sleeve and disposed under the plurality of moving blades 2, wherein the power driving device 4 It is connected with the hub shaft to drive the hub shaft to rotate, thereby driving the plurality of moving blades 2 disposed on the hub shaft to rotate; in addition, the power driving device 4 is further connected
  • the ducted fan is disposed in the ducted fan by using the heat dissipation structure to dissipate heat by the high-speed airflow in the ducted fan, thereby significantly improving the cooling effect of the heat dissipation structure, thereby ensuring the temperature of the power driving device 4.
  • the heat radiating structure is disposed on the stationary blade 3, which can significantly save Package space.
  • the heat dissipation structure is implemented as a heat sink attached to the outer surface of each stationary blade 3, in each heat sink.
  • a heat sink cooling line is provided.
  • the power driving device 4 comprises an engine with an engine cooling line disposed therein, and an output shaft of the engine is coupled with the hub shaft to drive the hub shaft to rotate, thereby driving the connection A plurality of moving blades 2 on the hub shaft rotate.
  • the engine cooling circuit of the engine is in fluid communication with the fin cooling line of the fin to form a coolant circuit for engine cooling through the fins.
  • the ducted fan is disposed in the duct 1 by using the high-speed airflow in the duct 1 to significantly improve the cooling effect of the fin, thereby ensuring the temperature of the engine. Improve the fuel efficiency of the engine and ensure the safety of the flight within the normal operating temperature range.
  • the heat sink may be secured to the surface of the stationary vane 3 by welding, rivets or bolting, etc., which are common in the art; in addition, in other embodiments, the fin may also correspond to the corresponding vane 3 integrally formed, from another angle, the heat sink is made into the configuration of the static vane 3, which can be regarded as a heat sink and a static vane integrated structure, so that the heat radiating and the static vane 3 balance the counter torque, the embodiment
  • the structure in which the heat sink and the stator blade 3 are integrated is simpler in structure, and the overall structure is more compact, and the package space is remarkably reduced.
  • each fin includes an upper water chamber 6 and a lower water chamber 7 located above and below, respectively, wherein the upper water chamber 6 and the lower water chamber 7 are in fluid communication via a plurality of heat pipes 5.
  • the upper water chamber 6 is in fluid communication with the outlet of the engine cooling line to receive the cooling liquid to be cooled from the engine cooling line and feed it into the fin cooling line for cooling; the lower water chamber 7 and the engine cooling tube
  • the inlet of the road is in fluid communication to return the cooled coolant to the engine cooling line for cooling of the engine.
  • all the heat dissipation pipes 5 are oriented parallel to each other, and a plurality of heat dissipation fins are further disposed between the adjacent heat dissipation pipes 5 of all the heat dissipation pipes 5 to further enhance the heat dissipation effect. .
  • a water pump 8 is provided at the inlet of the engine cooling pipe, and the water pump 8 functions to return the coolant cooled by the fins to the engine cooling pipe.
  • the road is used for engine cooling.
  • a thermostat 9 is provided at the outlet of the engine cooling circuit, the function of the thermostat 9 is to control the engine cooling tube The flow of coolant in the road.
  • the thermostat 9 when the temperature of the coolant in the engine cooling line is lower than 80 degrees, the thermostat 9 is closed, the coolant flows directly back to the engine, does not flow to the heat sink, thereby ensuring that the engine is operating at a suitable temperature; when the engine cooling tube When the temperature of the coolant in the road is higher than 80 degrees, the thermostat 9 is opened, and the coolant flows through the duct to the fins and is cooled by the fins.
  • the ducted fan includes four moving blades 2 angularly distributed around the central axis of the duct 1, and each moving blade 2 The chord line forms an angle with the rotating blade horizontal plane; similarly, in each of the above embodiments or other embodiments of the invention, the ducted fan comprises six stator blades 3 angularly distributed around the central axis of the duct 1 Further, the stationary blade 3 has a flat plate shape, and the flat stator blade 3 is disposed perpendicular to the cross section of the duct 1.
  • a fairing 10 can be mounted at the top end of the hub axle, the fairing 10 being positioned above the plurality of moving blades 2 and with multiple movements The blade 2 rotates while rotating.
  • the fairing 10 is capable of rectifying the flow of air entering the air inlet of the duct 1 to make the ducted fan flow more uniform.
  • the engine drives the moving blade 2 to rotate through the transmission shaft, so that the air enters the duct 1 from the air inlet of the duct 1 and Acceleration, airflow through the moving blade 2 will generate torque and thrust, the thrust will take the aircraft to take off, the heat sink can generate reverse torque when the airflow passes, thereby counteracting the torque; at the same time, the coolant flows under the action of the water pump 8.
  • the coolant absorbs the heat of the engine through the water jacket, and then flows through the entire heat sink; wherein the heat sink can be made of aluminum alloy, and when the high-speed airflow blows through the heat sink, a large amount of heat is taken away by the air. , thereby reducing the coolant temperature.
  • the cooled coolant is returned to the engine by the engine cooling circuit, and the pump is continuously pushed to cool the engine to form a circulating high-speed airflow of fluid cooling through the heat sink, which also greatly promotes heat dissipation of the engine.
  • ducted fan of the present invention is mainly applied to a ducted aircraft using a gasoline powered engine, but is equally applicable to any other aircraft that uses a duct to provide lift.

Landscapes

  • Engineering & Computer Science (AREA)
  • Mechanical Engineering (AREA)
  • Chemical & Material Sciences (AREA)
  • Combustion & Propulsion (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

一种涵道风扇，包括：具有中心轴线的涵道（1），一进风口和一出风口分别位于涵道（1）的上端和下端；桨毂轴，设置在涵道（1）的中心轴线上；多个动叶片（2），设置在桨毂轴上并靠近进风口且可随桨毂轴转动；固定套筒，桨毂轴装设于固定套筒内；多个静叶片（3），其相对两端分别与固定套筒和涵道（1）的内壁连接，每个静叶片（3）上设置有散热结构；以及动力驱动装置（4），设置在固定套筒内且位于多个动叶片（2）下方，动力驱动装置（4）与桨毂轴连接以驱动桨毂轴转动且动力驱动装置（4）与散热结构连接以通过散热结构散热。将散热结构设置在涵道风扇的静叶片（3）上或将散热结构与静叶片（3）一体成型，使静叶片（3）具有散热功能同时也具有平衡反扭矩的作用，显著提高了散热效果，同时也节省了空间。

Description

涵道风扇 技术领域
本发明涉及飞行器领域，并且更具体地，涉及一种涵道风扇。
 背景技术
散热冷却问题一直是飞行器发动机的一个症结。发动机冷却系统的好坏直接影响发动机的性能和使用寿命。一般发动机的冷却系统都是主动冷却，即，使用冷却风扇使空气高速吹过散热片表面，带走发动机散出的热量, 使发动机冷却。但是在飞行器设计中，为了减轻飞行器重量常常省去冷却风扇。没有了风扇提供的高速气流，冷却效率会大大降低，给飞行器的设计带来了严重的问题。
 技术问题
现有技术中，将发动机的散热器放在了涵道的入口，希望通过进入涵道的气流带走热量。但是涵道入口的空气来流速度有限，跟经过涵道动叶片加速后的气流速度相差甚远。用入口处的气流冷却效率不大，因此需要通过增大散热器体积来达到要求的散热效果，但是这会增加飞行包的整体重量，而且也影响美观。
 技术解决方案
针对相关技术中存在的问题，本发明的目的在于提供一种涵道风扇，该涵道风扇将散热器布局在涵道风扇中，以利用涵道风扇中的高速气流散热，显著提高了散热器的冷却效果；此外，该涵道风扇将散热结构设置在静叶片上，从而节省封装空间。
为实现上述目的，本发明提供了一种涵道风扇，包括：涵道，涵道具有中心轴线，一进风口和一出风口分别位于涵道的上端和下端；桨毂轴，设置在涵道的中心轴线上；多个动叶片，设置在桨毂轴上并靠近进风口，且可随桨毂轴的转动而转动；固定套筒，桨毂轴装设于固定套筒内；多个静叶片，静叶片的相对两端分别与固定套筒和涵道的内壁连接，每个静叶片上设置有散热结构；以及动力驱动装置，设置在固定套筒内并且位于多个动叶片下方，其中，动力驱动装置与桨毂轴连接以驱动桨毂轴转动，并且动力驱动装置与散热结构连接以通过散热结构散热。
根据本发明的一个实施例，散热结构为贴附在每个静叶片的外表面上的散热片，在散热片中设有散热片冷却管路。
根据本发明的一个实施例，动力驱动装置包括发动机，发动机内设有发动机冷却管路，发动机的输出轴与桨毂轴连接以驱动桨毂轴转动，并且发动机冷却管路与散热片冷却管路流体连通以形成冷却液回路。
根据本发明的一个实施例，散热片包括经由多个散热管连通的上水室和下水室，其中，上水室与发动机冷却管路的出口流体连通，并且下水室与发动机冷却管路的入口流体连通。
根据本发明的一个实施例，多个散热管相互平行地设置，且在相邻的散热管之间还设有多个散热翅片。
根据本发明的一个实施例，在发动机冷却管路的入口处设置有水泵，以将经多个散热片冷却的冷却液送回发动机冷却管路中。
根据本发明的一个实施例，在发动机冷却管路的出口处设置有节温器。
根据本发明的一个实施例，多个动叶片绕中心轴线等角度分布，并且每个动叶片的弦线与动叶片旋转水平面形成夹角。
根据本发明的一个实施例，多个静叶片绕中心轴线等角度分布，并且每个静叶片垂直于涵道的横截面。
根据本发明的一个实施例，在桨毂轴顶端设置有整流罩，整流罩位于多个动叶片的上方且随动叶片的转动而转动。
根据本发明的一个实施例，多个散热片通过焊接、铆接或螺栓连接固定在多个静叶片的表面上。
根据本发明的一个实施例，散热片可与对应的静叶片一体成型。
 有益效果
本发明的有益技术效果在于：
本发明将散热结构设置在涵道风扇的静叶片上或将散热结构与静叶片一体成型，使静叶片具有散热功能同时也具有平衡反扭矩的作用，涵道风扇中的高速气流经过，显著提高了对发动机的散热效果，从而保证发动机的温度在正常工作温度范围内，提高发动机的燃油效率，保障飞行的安全性；
此外，本发明的涵道风扇将发动机散热器设置在涵道风扇的静叶片上，显著地减小了封装空间。
 附图说明
为了更清楚地说明本发明实施例或现有技术中的技术方案，下面将对实施例中所需要使用的附图作简单地介绍，显而易见地，下面描述中的附图仅仅是本发明的一些实施例，对于本领域普通技术人员来讲，在不付出创造性劳动的前提下，还可以根据这些附图获得其他的附图。
图1例示了根据本发明的一个实施例的涵道风扇的结构示意图；
图2例示了图1所示的涵道风扇沿中心轴线所在平面截取的截面图；以及
图3例示了根据本发明的一个实施例的涵道风扇中的发动机与散热片的连接方式。
 本发明的实施方式
以下将结合附图，对本发明的实施例进行具体描述。需要注意的是，以下各个实施例可以任意可能的方式相互组合或部分替换。
参照图1至图3，示出了根据本发明的一个示例性实施例的涵道风扇。在该实施例中，由图1可见，涵道风扇包括涵道1、桨毂轴、多个动叶片2、固定套筒、多个静叶片3以及动力驱动装置4。具体地，涵道1为具有中心轴线的圆柱形通道，一进风口和一出风口分别位于涵道1的上端和下端，桨毂轴与涵道1同轴地设置在固定套筒内，多个动叶片2邻近进风口设置在桨毂轴上，其中，所有动叶片2绕桨毂轴呈辐射状布置且可随桨毂轴的转动而转动，每个静叶片3的相对两端分别与固定套筒和涵道1的内壁连接，并且在每个静叶片3上设置有散热结构，动力驱动装置4位于固定套筒内且设置在多个动叶片2的下方，其中，动力驱动装置4与桨毂轴连接以驱动桨毂轴转动，从而带动设置在桨毂轴上的多个动叶片2转动；此外，动力驱动装置4还与散热结构连接，以通过散热结构进行散热。
有益地，在上述实施例中，涵道风扇通过将散热结构布局在涵道风扇中，利用涵道风扇中的高速气流散热，显著提高了散热结构的冷却效果，从而保证动力驱动装置4的温度在正常工作温度范围内，提高动力驱动装置4的能效，保障飞行的安全性；此外，在上述实施例所示的涵道风扇中，通过将散热结构设置在静叶片3上，能够显著地节省封装空间。
示例性地，在本发明的一个可能的实施例中，如图1至图3所示，散热结构实施为贴附在每个静叶片3的外表面上的散热片，在每个散热片中设有散热片冷却管路。进一步示例性地，根据发明的一个可能的实施例，动力驱动装置4包括发动机，发动机内设有发动机冷却管路，发动机的输出轴与桨毂轴连接以驱动桨毂轴转动，从而带动连接于桨毂轴上的多个动叶片2转动。此外，发动机的发动机冷却管路与散热片的散热片冷却管路流体连通以形成冷却液回路，从而通过散热片实现发动机冷却。
在上述示例性实施例中，有益的是，涵道风扇通过将散热片布局在涵道1中，利用涵道1中的高速气流散热，显著提高了散热片的冷却效果，从而保证发动机的温度在正常工作温度范围内，提高发动机的燃油效率，保障飞行的安全性。在一些实施例中，散热片可通过焊接、铆钉或螺栓连接等本领域常见的紧固方式固定在静叶片3的表面上；此外，在另一些实施例中，散热片还可与对应静叶片3一体成型，换个角度讲，即将散热片制作成静叶片3的构型，可以看做是散热片与静叶片为一体构造，因此同时具有散热和静叶片3平衡反扭矩的作用，本实施例中这种将散热片与静叶片3一体化的构造，结构更简单，也使整体结构更紧凑，显著地减小了封装空间。
继续参照图3，详细描述散热片的具体构造。如图所示，每个散热片包括分别位于上方和下方的上水室6和下水室7，其中，上水室6和下水室7经由多个散热管5流体连通。其中，上水室6与发动机冷却管路的出口流体连通，以接收来自发动机冷却管路的需冷却的冷却液并将其送入散热片冷却管路中进行冷却；下水室7与发动机冷却管路的入口流体连通，以将经冷却的冷却液送回发动机冷却管路中，用于发动机的冷却。
优选地，在本发明的一个可能的实施例中，所有散热管5相互平行定向，并且在所有散热管5的相邻散热管5之间还设有多个散热翅片，以进一步增强散热效果。
另外，在本发明的其他可能的实施例中，如图3所示，在发动机冷却管路的入口处设置有水泵8，水泵8的作用在于将经散热片冷却的冷却液送回发动机冷却管路中用于发动机冷却。附加地或替代地，在本发明的另一个可能的实施例中，如图3所示，在发动机冷却管路的出口处设置有节温器9，节温器9的作用是控制发动机冷却管路中的冷却液的流向。例如，当发动机冷却管路中的冷却液的温度低于80度时，节温器9闭合，冷却液直接流回发动机，不流向散热片，从而保证发动机工作在合适的温度；当发动机冷却管路中的冷却液的温度高于80度时，节温器9打开，冷却液通过导管流至散热片，通过散热片进行冷却。
优选地，在上述各个实施例或本发明的其他实施例中，如图1所示，涵道风扇包括绕涵道1的中心轴线等角度分布的四个动叶片2，并且每个动叶片2的弦线与动叶片旋转水平面形成夹角；类似地，在上述各个实施例或本发明的其他实施例中，涵道风扇包括绕涵道1的中心轴线等角度分布的六个静叶片3，并且静叶片3呈平板状，平板状的静叶片3垂直于涵道1的横截面而设置。
进一步优选地，在本发明的一些可能的实施例中，如图1所示，可在桨毂轴顶端安装整流罩10，整流罩10定位在多个动叶片2的上方并且随着多个动叶片2的转动而转动。有益地，整流罩10能够对进入涵道1的进风口的气流起到整流的作用，使涵道风扇入流更加均匀。
在散热片与静叶片3一体成型的实施例中，如图1所以，在涵道风扇工作时，发动机通过传动轴带动动叶片2转动，使空气从涵道1的进风口进入涵道1并且加速，气流流过动叶片2会产生扭矩和推力，推力带动飞行器起飞，散热片在气流经过时能够产生反向扭矩，从而起到抵消扭矩的作用；同时，冷却液在水泵8的作用下流经发动机的气缸的水套，冷却液经水套将发动机的热量吸收，然后流经整个散热片；其中，散热片可为铝合金材质，当高速气流吹过散热片后，大量热量被空气带走，从而降低了冷却液温度。冷却后的冷却液由发动机冷却管路再流回发动机，经过水泵的推动继续冷却发动机，形成一个流体散热的循环高速气流流过散热片，也极大地促进了发动机的散热。
应当注意的是，本发明的涵道风扇主要应用于采用汽油动发动机的涵道式飞行器，但也同样适用于其他任何利用涵道提供升力的飞行器。
以上所述仅为本发明的优选实施例而已，并不用于限制本发明，对于本领域的技术人员来说，本发明可以有各种更改和变化。凡在本发明的精神和原则之内，所作的任何修改、等同替换、改进等，均应包含在本发明的保护范围之内。

Claims (12)

  1. 一种涵道风扇，其特征在于，包括：
    涵道（1），所述涵道（1）具有中心轴线，一进风口和一出风口分别位于所述涵道（1）的上端和下端；
    桨毂轴，设置在所述涵道（1）的所述中心轴线上；
    多个动叶片（2），设置在所述桨毂轴上并靠近所述进风口，且可随所述桨毂轴的转动而转动；
    固定套筒，所述桨毂轴装设于所述固定套筒内；
    多个静叶片（3），每个所述静叶片（3）的相对两端分别与所述固定套筒和所述涵道（1）的内壁连接，每个所述静叶片（3）上设置有散热结构；以及
    动力驱动装置（4），设置在所述固定套筒内并且位于所述多个动叶片（2）下方，
    其中，所述动力驱动装置（4）与所述桨毂轴连接以驱动所述桨毂轴转动，并且所述动力驱动装置（4）与所述散热结构连接以通过所述散热结构散热。
  2. 根据权利要求1所述的涵道风扇，其特征在于，所述散热结构为贴附在每个所述静叶片（3）的外表面上的散热片，在所述散热片中设有散热片冷却管路。
  3. 根据权利要求2所述的涵道风扇，其特征在于，所述动力驱动装置（4）包括发动机，所述发动机内设有发动机冷却管路，所述发动机的输出轴与所述桨毂轴连接以驱动所述桨毂轴转动，并且所述发动机冷却管路与所述散热片冷却管路流体连通以形成冷却液回路。
  4. 根据权利要求3所述的涵道风扇，其特征在于，所述散热片包括经由多个散热管（5）连通的上水室（6）和下水室（7），其中，所述上水室（6）与所述发动机冷却管路的出口流体连通，并且所述下水室（7）与所述发动机冷却管路的入口流体连通。
  5. 根据权利要求4所述的涵道风扇，其特征在于，所述多个散热管（5）相互平行地设置，且在相邻的所述散热管（5）之间还设有多个散热翅片。
  6. 根据权利要求4所述的涵道风扇，其特征在于，在所述发动机冷却管路的所述入口处设置有水泵（8），以将经所述散热片冷却的冷却液送回所述发动机冷却管路中。
  7. 根据权利要求4所述的涵道风扇，其特征在于，在所述发动机冷却管路的出口处设置有节温器（9）。
  8. 根据权利要求1所述的涵道风扇，其特征在于，所述多个动叶片（2）绕所述中心轴线等角度分布，并且每个所述动叶片（2）的弦线与所述动叶片旋转水平面形成夹角。
  9. 根据权利要求1所述的涵道风扇，其特征在于，所述多个静叶片（3）绕所述中心轴线等角度分布，并且每个所述静叶片（3）垂直于所述涵道（1）的横截面。
  10. 根据权利要求3所述的涵道风扇，其特征在于，在所述桨毂轴顶端设置有整流罩（10），所述整流罩（10）位于所述多个动叶片（2）的上方且随所述多个动叶片（2）的转动而转动。
  11. 根据权利要求1所述的涵道风扇，其特征在于，所述散热片通过焊接、铆接或螺栓连接固定在每个所述静叶片（3）的表面上。
  12. 根据权利要求1所述的涵道风扇，其特征在于，所述散热片可与对应的所述静叶片（3）一体成型。
PCT/CN2018/079749 2017-06-07 2018-03-21 涵道风扇 WO2018223748A1 (zh)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201710422428.9A CN108995818A (zh) 2017-06-07 2017-06-07 涵道风扇
CN201710422428.9 2017-06-07

Publications (1)

Publication Number Publication Date
WO2018223748A1 true WO2018223748A1 (zh) 2018-12-13

Family

ID=64565723

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2018/079749 WO2018223748A1 (zh) 2017-06-07 2018-03-21 涵道风扇

Country Status (2)

Country Link
CN (1) CN108995818A (zh)
WO (1) WO2018223748A1 (zh)

Families Citing this family (2)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN111137082A (zh) * 2019-12-30 2020-05-12 长春理工大学 单涵道陆空跨域机器人及其控制方法
CN115750439B (zh) * 2022-11-16 2023-06-16 南昌航空大学 一种基于边界层摄入的风冷一体化涵道风扇

Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US20150292352A1 (en) * 2014-04-14 2015-10-15 Airbus Operations (S.A.S.) Aircraft propulsion assembly comprising an air flow valve with a variable flow rate
CN105408207A (zh) * 2013-06-14 2016-03-16 空客集团有限公司 用于飞行器的电力推进组件
CN205945353U (zh) * 2016-07-07 2017-02-08 杭州海康机器人技术有限公司 一种自散热电机和无人机
CN206141808U (zh) * 2016-09-14 2017-05-03 深圳市大疆创新科技有限公司 一种飞行器的机臂组件以及飞行器
CN106741978A (zh) * 2016-12-30 2017-05-31 中航维拓（天津）科技有限公司 一种直升机用一体化复合式冷却系统
CN206939096U (zh) * 2017-06-07 2018-01-30 深圳光启合众科技有限公司 涵道风扇

Family Cites Families (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US8387362B2 (en) * 2006-10-19 2013-03-05 Michael Ralph Storage Method and apparatus for operating gas turbine engine heat exchangers
CN101050727A (zh) * 2007-05-09 2007-10-10 韩培洲 中冷等压回热燃气轮机
JP5636774B2 (ja) * 2010-07-09 2014-12-10 株式会社Ihi タービン翼及びエンジン部品
EP2971670B1 (en) * 2013-02-20 2020-07-15 United Technologies Corporation Integrated heat exchangers for low fan pressure ratio geared turbofan
US9422063B2 (en) * 2013-05-31 2016-08-23 General Electric Company Cooled cooling air system for a gas turbine
US9777963B2 (en) * 2014-06-30 2017-10-03 General Electric Company Method and system for radial tubular heat exchangers

Patent Citations (6)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN105408207A (zh) * 2013-06-14 2016-03-16 空客集团有限公司 用于飞行器的电力推进组件
US20150292352A1 (en) * 2014-04-14 2015-10-15 Airbus Operations (S.A.S.) Aircraft propulsion assembly comprising an air flow valve with a variable flow rate
CN205945353U (zh) * 2016-07-07 2017-02-08 杭州海康机器人技术有限公司 一种自散热电机和无人机
CN206141808U (zh) * 2016-09-14 2017-05-03 深圳市大疆创新科技有限公司 一种飞行器的机臂组件以及飞行器
CN106741978A (zh) * 2016-12-30 2017-05-31 中航维拓（天津）科技有限公司 一种直升机用一体化复合式冷却系统
CN206939096U (zh) * 2017-06-07 2018-01-30 深圳光启合众科技有限公司 涵道风扇

Also Published As

Publication number Publication date
CN108995818A (zh) 2018-12-14

Similar Documents

Publication Publication Date Title
CN106249827B (zh) Cpu水泵散热器
EP3505449B1 (en) Heat dissipation system for electric aircraft engine
EP2802774B1 (en) Cooling system of a wind turbine
TW202100927A (zh) 液冷式散熱裝置及車輛
CN102478365A (zh) 散热器和冷却装置
WO2018223748A1 (zh) 涵道风扇
CN206939096U (zh) 涵道风扇
CN110667864A (zh) 混合动力多旋翼无人机水冷却系统及其应用方法
CN206753860U (zh) 压缩机散热风机
KR20160137292A (ko) 회전팬 블레이드부 자체의 표면냉각효과를 이용한 냉각팬
CN205248989U (zh) 一种油内循环冷却电机
CN210239860U (zh) 燃气涡轮发电装置及飞行器
CN114194403B (zh) 驱动装置的散热结构及飞行器
CN212286905U (zh) 一种能够快速散热的数控加工中心主轴
WO2018201812A1 (zh) 涵道风扇
CN108952936A (zh) 一种利用行进过程产风的汽车散热器
CN104747260A (zh) 一种新型直升机水冷发动机散热系统
CN205657965U (zh) 液冷式散热系统及其泵
EP3699423A1 (en) High-pressure pump
CN209730964U (zh) 一种数控机床高速电机主轴散热装置
CN114024394A (zh) 一种新能源汽车低热改良的动力装置
WO2024139470A1 (zh) 双风冷散热通道的动力装置及包含其的飞行器
CN213094013U (zh) 一种应急变频调速电机用冷却装置
CN218913447U (zh) 一种风力电机定子主轴
CN219678246U (zh) 一种散热性好的发电机

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: 18812921

Country of ref document: EP

Kind code of ref document: A1

NENP Non-entry into the national phase

Ref country code: DE

32PN Ep: public notification in the ep bulletin as address of the adressee cannot be established

Free format text: NOTING OF LOSS OF RIGHTS PURSUANT TO RULE 112(1) EPC (EPO FORM 1205A DATED 10.06.2020)

122 Ep: pct application non-entry in european phase

Ref document number: 18812921

Country of ref document: EP

Kind code of ref document: A1