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WO2023124378A1 - 螺旋桨和飞行器 - Google Patents

螺旋桨和飞行器 Download PDF

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Publication number
WO2023124378A1
WO2023124378A1 PCT/CN2022/124711 CN2022124711W WO2023124378A1 WO 2023124378 A1 WO2023124378 A1 WO 2023124378A1 CN 2022124711 W CN2022124711 W CN 2022124711W WO 2023124378 A1 WO2023124378 A1 WO 2023124378A1
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WO
WIPO (PCT)
Prior art keywords
spoiler
blade
propeller
side wall
aircraft
Prior art date
Application number
PCT/CN2022/124711
Other languages
English (en)
French (fr)
Inventor
赵龙智
郜奥林
刘璐
陆宏伟
续立军
邱一可
吴振凯
李桂华
刘金来
马聪
刘宝俊
高焓
Original Assignee
北京三快在线科技有限公司
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 北京三快在线科技有限公司 filed Critical 北京三快在线科技有限公司
Publication of WO2023124378A1 publication Critical patent/WO2023124378A1/zh

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    • 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
    • B64C11/16—Blades
    • B64C11/18—Aerodynamic features
    • 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
    • B64C11/16—Blades
    • B64C11/20—Constructional features

Definitions

  • the present application relates to the technical field of aircraft, in particular to a propeller and an aircraft.
  • the aircraft is equipped with a propeller, and the flight of the aircraft is realized through the disturbance of the airflow by the propeller. Since the aircraft has functions such as shooting and transporting materials, it is widely used in many industries such as surveying and mapping, logistics, and distribution.
  • the application provides a propeller and an aircraft, and the technical scheme is as follows.
  • the first aspect of the present application provides a propeller, which includes: a blade and a spoiler, at least part of which protrudes from the suction surface of the blade; wherein the spoiler extends along the span direction of the blade.
  • the spoiler extending along the spanwise direction of the blade is provided so that the airflow in the laminar flow region changes to turbulent flow in advance, that is, when the flow velocity of the airflow is relatively high, the laminar flow is transformed into turbulent flow, so that the flow velocity of turbulent flow increases, thereby making The airflow in the turbulent area can leave the surface of the blade faster, thereby reducing the collision area between the airflow in the turbulent area and the surface of the blade, so as to reduce noise.
  • the blade along the chord direction of the blade, the blade also includes a leading edge and a trailing edge oppositely arranged, the vertical distance between the leading edge and the trailing edge is the chord length c of the blade, and the spoiler
  • the distance L1 between the centerline and the leading edge satisfies: 0.05c ⁇ L1 ⁇ 0.6c.
  • the blade along the direction of the chord length of the blade, the blade also includes a leading edge and a trailing edge oppositely arranged, the vertical distance between the leading edge and the trailing edge is the chord length c of the blade, and the operating environment of the propeller
  • the Reynolds number is Re
  • the blade along the chord direction of the blade, the blade also includes a leading edge and a trailing edge oppositely arranged, the vertical distance between the leading edge and the trailing edge is the chord length c of the blade, and the spoiler
  • the width L2 satisfies: 0.05c ⁇ L2 ⁇ 0.5c.
  • the spoiler along the chord direction of the blade, includes a first side wall and a second side wall oppositely arranged, at least part of the first side wall is sawtooth-shaped, and/or, the second At least a portion of the sidewall is serrated.
  • the spoiler includes a first side and a second side, and a plurality of first sides and a plurality of second sides are arranged at intervals and connected with each other to form a zigzag first side wall and/or a second side wall.
  • the blade along the thickness direction of the blade, the blade includes a top surface and a bottom surface oppositely arranged, both the top surface and the bottom surface are suction surfaces, and the spoiler is arranged on the top surface, or the spoiler is arranged on the top surface face and bottom.
  • the spoiler runs through the blade, or the spoiler covers a part of the blade.
  • the spoiler is integrally formed or fixedly connected to the paddle.
  • the second aspect of the present application provides an aircraft, the aircraft includes a body and a propeller installed on the body, and the propeller is the propeller described in any one of the above.
  • the propeller is provided with a spoiler extending along the span of the blade to increase the turbulent flow velocity, so that the area where the noise is generated on the surface of the blade is reduced, thereby reducing the noise generated during the working process of the propeller, thereby improving the use of the aircraft Performance, at the same time, can improve the concealment of the aircraft, thereby improving the application scenarios of the aircraft.
  • Fig. 1 is a partial structural schematic diagram of a propeller provided by the present application
  • Fig. 2 is a structural schematic diagram of a spoiler provided by the present application.
  • Fig. 3 is a schematic structural diagram of a spoiler provided by the present application.
  • FIG. 4 is a schematic diagram of a partial structure of a spoiler provided by the present application after the blade is installed.
  • the aircraft is provided with a propeller, and when the propeller rotates, the propeller disturbs the air flow, so that the flight of the aircraft can be realized.
  • the propeller disturbs the airflow, it will cause collision between the airflow and the airflow and the propeller to generate noise, thereby reducing the performance of the aircraft.
  • the noise generated above belongs to aerodynamic noise, and aerodynamic noise is mainly divided into broadband noise and harmonic noise. Based on the different designs of propellers and different working conditions where propellers are required to be used, the relative proportions of these two kinds of noise may also be different.
  • When reducing noise for propellers it is often chosen to change the thickness distribution, chord length distribution, and torsional distribution of the blades to reduce harmonic noise.
  • the embodiment of the present application provides a propeller, as shown in Figure 1, the propeller includes: a blade 1; a spoiler 2, at least part of the spoiler 2 protrudes from the suction surface of the blade 1; wherein, the spoiler 2 extends along the length direction of the blade 1.
  • the length direction of the blade 1 is the span direction of the blade 1
  • the span direction is the direction indicated by r or R in FIG. 1 .
  • the spoiler 2 extends along the span direction of the blade 1, which may refer to: the projected length of the spoiler 2 in the span direction is greater than that of the spoiler 2 in the The projected length in the direction of the chord length, the direction of the chord length is the direction shown in c in Figure 1.
  • the airflow will be stirred during the operation of the propeller, so that the laminar flow changes into a turbulent flow. Due to the chaotic direction of the airflow in the turbulent flow area, the collision between the airflow and the airflow will occur, and part of the airflow will collide with the airflow. The surface of the paddle 1 collides, thereby generating a large noise. The energy of the airflow decreases due to the collision of the airflow, so that the flow velocity of the airflow decreases, that is, along the chord direction of the blade 1 , the flow velocity of the airflow at the front end of the blade 1 is greater than the flow velocity of the airflow at the rear end of the blade 1 .
  • the spoiler 2 extending along the span direction of the blade 1 is provided.
  • the spoiler 2 will further disturb the airflow in addition to the blade 1 stirring the airflow.
  • the spoiler 2 is equivalent to a forward step, which can intervene in the generation and development of the above-mentioned laminar flow separation bubbles, so that the airflow in the laminar flow area changes to turbulent flow in advance, that is, the laminar flow is transformed into turbulent flow when the airflow velocity is relatively high, In other words, the spoiler 2 can transform laminar flow into turbulent flow.
  • the flow velocity of the turbulent flow is increased, and the turbulent kinetic energy is improved, so that the airflow in the turbulent flow area can leave the surface of the blade 1 faster, and the thickness of the turbulent boundary layer is reduced, thereby reducing the air flow in the turbulent flow area and the blade 1.
  • Surface collision area to reduce noise.
  • the propeller provided by the embodiment of the present application can at least reduce bandwidth noise, and can also reduce bandwidth noise and harmonic noise, thereby reducing aerodynamic noise.
  • the propeller provided by the embodiment of the present application can reduce noise by about 2dBA (decibels adjusted, adjusted decibels).
  • This noise reduction method is simple, has high feasibility, and is suitable for various engineering applications. Moreover, this noise reduction method has little impact on the aerodynamic characteristics of the blade 1 and will not affect the normal use of the propeller.
  • the blade 1 along the chord direction of the blade 1, the blade 1 also includes a leading edge 11 and a trailing edge 12 oppositely arranged, and the vertical distance between the leading edge 11 and the trailing edge 12 is is the chord length c of the blade 1 , and the distance L1 between the center line of the spoiler 2 and the leading edge 11 satisfies: 0.05c ⁇ L1 ⁇ 0.6c.
  • the distance L1 satisfies 0.1c ⁇ L1 ⁇ 0.5c.
  • L1 is too small, such as less than 0.05c, the impact of the air flow on the spoiler 2 during the operation of the blade 1 is too large, and damage to the spoiler 2 is likely to occur; if L1 is too large, If it is greater than 0.6c, the spoiler 2 is located in the turbulent area or behind the turbulent area, and the noise reduction effect of the spoiler 2 is low or even ineffective. Therefore, 0.05c ⁇ L1 ⁇ 0.6c can prolong the service life of the spoiler 2 and improve the noise reduction effect of the spoiler 2 at the same time.
  • the front end of the blade 1 is a leading edge 11
  • the rear end of the blade 1 is a trailing edge 12 .
  • the chord length c of the blade 1 on the unit length is a constant value
  • the shape variation rules of the leading edge 11 and the trailing edge 12 of the blade 1 are different,
  • the chord length c of the blade 1 per unit length is constantly changing, therefore, the distance L1 between the center line of the spoiler 2 and the leading edge 11 can be a constant value, or can be constantly changing.
  • the Reynolds number of the propeller operating environment is Re
  • the proportional coefficient k satisfies: 0.01 ⁇ k ⁇ 0.2.
  • the chord length c per unit length is a constant value, if the leading edge 11 and the trailing edge 12 of the blade 1
  • the chord length c per unit length is constantly changing. Therefore, the height h of the protruding top surface of the spoiler 2 per unit length can be a constant value, or it can be constantly changing.
  • the width L2 of the spoiler 2 satisfies: 0.05c ⁇ L2 ⁇ 0.5c.
  • the width of the spoiler 2 is too small, resulting in poor strength of the spoiler 2.
  • the spoiler 2 is easily deformed under the action of the airflow.
  • the spoiler 2 is ineffective or even damaged; if L2>0.5c, the width of the spoiler 2 is too large to exceed the turbulent flow region of the air flow, disturbing the air flow in the laminar flow region and generating greater noise. Therefore, if 0.05c ⁇ L2 ⁇ 0.5c, the use strength of the spoiler 2 can be improved, the service life of the spoiler 2 can be extended, and at the same time, the noise reduction effect of the spoiler 2 can be improved to ensure the normal operation of the spoiler 2 .
  • the chord length c per unit length is a constant value, if the shape of the leading edge 11 and the trailing edge 12 of the blade 1 changes If the rules are different, the chord length c per unit length is constantly changing. Therefore, the width L2 of the spoiler 2 can be a constant value, or it can be constantly changing.
  • the spoiler 2 includes a first side wall 21 and a second side wall 22 oppositely arranged, and at least part of the first side wall 21 is zigzag, and/or, at least part of the second side wall 22 is zigzag.
  • At least part of the first side wall 21 is zigzag, and/or, at least part of the second side wall 22 is zigzag, and the zigzag first side wall 21 and/or the second side can be added.
  • the contact area between the wall 22 and the airflow improves the noise reduction effect of the spoiler 2 , thereby improving the performance of the propeller.
  • At least part of the first side wall 21 is straight, and/or at least part of the second side wall 22 is straight.
  • the saw-tooth shape and the straight shape are examples, and are not used to limit the shape of the side wall of the spoiler 2.
  • any suitable shape can be used as the shape of the side wall of the spoiler 2 .
  • the spoiler 2 includes a first side 23 and a second side 24, and a plurality of first sides 23 and a plurality of second sides 24 are arranged at intervals and connected to each other to form a zigzag first side.
  • the angle ⁇ between the side wall 21 and/or the second side wall 22 ; the first side 23 and the second side 24 satisfies: 10° ⁇ 120°.
  • first side 23 and the second side 24 are spaced apart and connected end to end to form a zigzag first side wall 21 and/or second side wall 22 . If the angle ⁇ between the first side 23 and the second side 24 is too large or too small, that is, the distance S between the adjacent tooth tips is too large or too small, the first side 23 and the second side 24 will be separated from the airflow. If the contact area is too small, the noise reduction effect of the spoiler 2 will be reduced. Therefore, 10° ⁇ 120° can increase the contact area between the zigzag-shaped first side wall 21 and/or the second side wall 22 and the airflow, thereby improving the noise reduction effect of the spoiler 2 and further improving the use of the propeller. performance.
  • the blade 1 along the thickness direction of the blade 1, the blade 1 includes a top surface and a bottom surface oppositely arranged, both the top surface and the bottom surface are suction surfaces, and the spoiler 2 is arranged on the top surface, or the spoiler 2 Set on top and bottom.
  • the spoiler 2 is set on the top surface of the blade 1, which can improve The noise reduction effect of the spoiler 2, the spoiler 2 is arranged on the top surface and the bottom surface, so that the noise above and below the propeller is reduced, thereby further improving the noise reduction effect of the spoiler 2 .
  • the spoiler 2 can also be provided only on the bottom surface of the blade 1, so that the noise below the propeller is reduced, and the sum of the noise above and below the propeller will also be reduced, thereby reducing the noise. noise effect.
  • the spoiler 2 runs through the blade 1 , or the spoiler 2 covers a part of the blade 1 .
  • the spoiler 2 runs through the blade 1, that is, the spoiler 2 covers the entire blade 1 in the span direction, or in other words, the projected length of the spoiler 2 in the span direction is equal to that of the blade 1 in the span direction. Projection length.
  • the spoiler 2 may pass through the blade 1 , or may only cover a part of the blade 1 , thereby increasing the flexibility of disposing the spoiler 2 .
  • the spoiler 2 runs through the blade 1 along the span direction of the blade 1, which can increase the range of action of the spoiler 2, thereby improving the working performance of the spoiler 2, and reducing the noise generated when the propeller is in operation to a greater extent.
  • the spoiler 2 covers a part of the blade 1, while meeting the noise reduction requirements of the propeller, the size of the spoiler 2 is reduced, thereby reducing the production cost of the spoiler 2, and at the same time reducing the weight of the spoiler 2 , thereby reducing the weight of the propeller and increasing the performance of the propeller.
  • the number of the spoiler 2 is one or more; a plurality of spoilers 2 are arranged at intervals or continuously.
  • the embodiment of the present application does not limit the number and arrangement of the spoiler 2 .
  • the shape of the side walls of the one spoiler 2 may be the same or different.
  • all the sidewall shapes of the spoiler 2 are zigzag, or all sidewall shapes are straight, or half of the sidewall shapes are zigzag and the other half of the sidewall shapes are straight, here Not limited.
  • the side wall shapes of different spoiler parts 2 include but are not limited to: the side walls of every two spoiler parts 2 have the same shape, or the sides of every two spoiler parts 2 The shapes of the walls are all different, or a part of the spoiler 2 has the same side wall shape and another part of the spoiler 2 has a different side wall shape, which will not be repeated here.
  • the number of spoilers 2 is one or more; multiple spoilers 2 are arranged at intervals or continuously, which increases the flexibility of disposing the spoilers 2 on the blade 1 .
  • a plurality of turbulent parts 2 are arranged at intervals, while ensuring the noise reduction performance of the turbulent parts 2, the material of the turbulent parts 2 is reduced, thereby reducing the production cost.
  • all the spoilers 2 may be arranged at intervals, or all the spoilers 2 may be arranged continuously, or some spoilers 2 may be arranged at intervals and the other part may be arranged at intervals.
  • the spoiler 2 is arranged continuously, and the setting method is relatively flexible, and an appropriate setting method can be selected according to experience or actual needs.
  • the spoiler 2 is integrally formed or fixedly connected to the paddle 1 .
  • the fixed connection includes: obtaining a separate spoiler 2 and a separate paddle 1 , and then assembling the spoiler 2 to the paddle 1 so that the spoiler 2 is fixedly connected to the paddle 1 .
  • the spoiler 2 is integrally formed with the blade 1, which increases the stability of the connection between the spoiler 2 and the blade 1, and prevents the spoiler 2 from being separated from the blade 1 during the operation of the propeller. Safety issues, thereby improving the stability of the propeller and the safety of use.
  • the spoiler 2 is fixedly connected to the paddle 1 , which can facilitate the processing of the spoiler 2 and the paddle 1 , thereby reducing the processing cost of the spoiler 2 and the paddle 1 .
  • the spoiler 2 is integrally formed or fixedly connected with the blade 1 , which increases the connection mode between the spoiler 2 and the blade 1 , thereby increasing the flexibility of connecting the spoiler 2 and the blade 1 .
  • all spoiler parts 2 may be integrally formed with the blade 1, or all spoiler parts 2 may be integrated with the The paddle 1 is fixedly connected, or a part of the spoiler 2 is integrally formed with the paddle 1 and another part of the spoiler 2 is fixedly connected with the paddle 1 .
  • the embodiment of the present application also provides an aircraft, the aircraft includes a body and a propeller, the propeller is the propeller described in any of the above embodiments; the propeller is installed on the body.
  • a spoiler 2 extending along the chord direction of the blade 1 is provided on the propeller to increase the turbulent flow velocity, so that the area where noise is generated on the surface of the blade 1 is reduced, thereby reducing the noise generated during the working process of the propeller.
  • the performance of the aircraft can be improved, and at the same time, the concealment of the aircraft can be improved, thereby improving the application scenarios of the aircraft. That is, improving the versatility of the aircraft makes the aircraft applicable to more scenarios and expands the scope of application of the aircraft.
  • the aircraft includes, but is not limited to: a multi-rotor type aircraft, a vertical take-off and landing type aircraft, and the like.
  • the multi-rotor type aircraft includes multiple rotor shafts, and the above-mentioned body and propeller can be connected through the rotor shafts.
  • the embodiment of the present application does not limit the type of the aircraft, as long as the aircraft can use propellers.

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  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)
  • Hooks, Suction Cups, And Attachment By Adhesive Means (AREA)

Abstract

一种螺旋桨和飞行器。螺旋桨包括：桨叶（1）和扰流部（2），扰流部（2）的至少部分凸出桨叶（1）的吸力面；其中，扰流部（2）沿桨叶（1）的展向延伸。

Description

螺旋桨和飞行器
本申请要求于2021年12月29日提交的申请号为202111633174.8、申请名称为“一种螺旋桨和飞行器”的中国专利申请的优先权，其全部内容通过引用结合在本申请中。
技术领域
本申请涉及飞行器技术领域，尤其涉及一种螺旋桨和飞行器。
背景技术
飞行器上设置有螺旋桨，通过螺旋桨对气流的扰动实现飞行器的飞行，由于飞行器具有拍摄、运输物资等功能，因此被广泛应用于测绘、物流、配送等多个行业。
发明内容
本申请提供了一种螺旋桨和飞行器，技术方案如下。
本申请第一方面提供一种螺旋桨，该螺旋桨包括：桨叶和扰流部，扰流部的至少部分凸出桨叶的吸力面；其中，扰流部沿桨叶的展向延伸。
在本申请中，设置沿桨叶展向延伸的扰流部，使得层流区域的气流提前变化为湍流，即在气流流速较大时将层流转变为湍流，使得湍流的流速增加，从而使得湍流区域的气流能够更快的离开桨叶表面，进而减小了湍流区域的气流与桨叶表面的碰撞区域，以降低噪音。
在一种可能的设计中，沿桨叶的弦长方向，桨叶还包括相对设置的前缘和后缘，前缘和后缘之间的垂直距离为桨叶的弦长c，扰流部的中心线与前缘之间的距离L1满足：0.05c≤L1≤0.6c。
在一种可能的设计中，沿桨叶的弦长方向，桨叶还包括相对设置的前缘和后缘，前缘和后缘之间的垂直距离为桨叶的弦长c，螺旋桨使用环境的雷诺数为Re，扰流部凸出吸力面的高度为h满足：h＝kc/Re 0.2；其中，比例系数k满足：0.01≤k≤0.2。
在一种可能的设计中，沿桨叶的弦长方向，桨叶还包括相对设置的前缘和后缘，前缘和后缘之间的垂直距离为桨叶的弦长c，扰流部的宽度L2满足：0.05c≤L2≤0.5c。
在一种可能的设计中，沿桨叶的弦长方向，扰流部包括相对设置的第一侧壁和第二侧壁，第一侧壁的至少部分为锯齿形，和/或，第二侧壁的至少部分为锯齿形。
在一种可能的设计中，扰流部包括第一侧面和第二侧面，多个第一侧面和多个第二侧面间隔设置且相互连接，以形成锯齿形的第一侧壁和/或第二侧壁；第一侧面与第二侧面之间的夹角α满足：10°＜α＜120°。
在一种可能的设计中，沿桨叶厚度方向，桨叶包括相对设置的顶面和底面，顶面和底面均为吸力面，扰流部设置于顶面，或者，扰流部设置于顶面和底面。
在一种可能的设计中，沿桨叶的展向，扰流部贯穿桨叶，或者，扰流部覆盖桨叶的一部分。
在一种可能的设计中，扰流部的数量为一个或多个；多个扰流部间隔设置或连续设置。
在一种可能的设计中，扰流部与桨叶一体成型或固定连接。
本申请第二方面提供一种飞行器，该飞行器包括本体和安装于本体的螺旋桨，螺旋桨为以上任一项中所述的螺旋桨。
在本申请中，在螺旋桨上设置沿桨叶展向延伸的扰流部来增加湍流流速，使得桨叶表面产生噪声的区域减小，从而降低螺旋桨工作过程所产生的噪音，进而提升飞行器的使用性能，同时，能够提升飞行器的隐蔽性，进而提升飞行器的适用场景。
应当理解的是，以上的一般描述和后文的细节描述仅是示例性的，并不能限制本申请。
附图说明
图1为本申请提供的一种螺旋桨的局部结构示意图；
图2为本申请提供的一种扰流部的结构示意图；
图3为本申请提供的一种扰流部的结构示意图；
图4为本申请提供的一种扰流部与桨叶安装后的局部结构示意图。
附图标记：
1-桨叶；
11-前缘；12-后缘；
2-扰流部；
21-第一侧壁；22-第二侧壁；23-第一侧面；24-第二侧面。
此处的附图被并入说明书中并构成本说明书的一部分，示出了符合本申请的实施例，并与说明书一起用于解释本申请的原理。
具体实施方式
为了更好的理解本申请的技术方案，下面结合附图对本申请实施例进行详细描述。
应当明确，所描述的实施例仅仅是本申请一部分实施例，而不是全部的实施例。基于本申请中的实施例，本领域普通技术人员在没有作出创造性劳动前提下所获得的所有其它实施例，都属于本申请保护的范围。
在本申请实施例中使用的术语是仅仅出于描述特定实施例的目的，而非旨在限制本申请。在本申请实施例和所附权利要求书中所使用的单数形式的“一种”、“所述”和“该”也旨在包括多数形式，除非上下文清楚地表示其他含义。
应当理解，本文中使用的术语“和/或”仅仅是一种描述关联对象的关联关系，表示可以存在三种关系，例如，A和/或B，可以表示：单独存在A，同时存在A和B，单独存在B这三种情况。另外，本文中字符“/”，一般表示前后关联对象是一种“或”的关系。
需要注意的是，本申请实施例所描述的“上”、“下”、“左”、“右”等方位词是以附图所示的角度来进行描述的，不应理解为对本申请实施例的限定。此外，在上下文中，还需要理解的是，当提到一个元件连接在另一个元件“上”或者“下”时，其不仅能够直接连接在另一个元件“上”或者“下”，也可以通过中间元件间接连接在另一个元件“上”或者“下”。
随着飞行器技术的不断发展，飞行器在各个行业的应用也越来越广泛。其中，飞行器上设置有螺旋桨，当螺旋桨发生转动时，螺旋桨对气流造成扰动，从而可以实现飞行器的飞行。在飞行器飞行过程中，由于螺旋桨扰动气流，因而会导致气流与气流之间、气流与螺旋桨之间发生碰撞而产生噪声，从而降低了飞行器的使用性能。
其中，上述产生的噪声属于气动噪声，气动噪声主要分为宽带噪声和谐波噪 声。基于对螺旋桨的设计不同、需要应用螺旋桨的工况不同，这两种噪声的相对比例也可能不同。在针对螺旋桨进行降噪时，往往会选择改变桨叶的厚度分布、弦长分布和扭转分布等等，以降低谐波噪声，而对于宽带噪声则缺乏可以广泛应用的降噪方法。
本申请实施例提供了一种螺旋桨，如图1所示，该螺旋桨包括：桨叶1；扰流部2，扰流部2的至少部分凸出桨叶1的吸力面；其中，扰流部2沿桨叶1的长度方向延伸。
其中，桨叶1的长度方向即为桨叶1的展向，展向为图1中r或R所示的方向。示例性地，对于一个扰流部2而言，该扰流部2沿桨叶1的展向延伸，可以是指：该扰流部2在展向上的投影长度，大于该扰流部2在弦长方向上的投影长度，弦长方向为图1中c所示的方向。
如果桨叶1不包括扰流部2，在螺旋桨工作过程中会搅动气流，使得层流变化为湍流，由于湍流区域内的气流运动方向杂乱，导致气流与气流之间发生碰撞，且部分气流与桨叶1的表面碰撞，从而产生较大的噪音。由于气流发生碰撞导致气流能量降低，从而使得气流的流速减小，即，沿桨叶1的弦长方向，桨叶1前端气流的流速大于桨叶1后端的气流的流速。正因为桨叶1前端气流的流速大于桨叶1后端气流的流速，因而会在桨叶1上形成逆压梯度，该逆压梯度会导致桨叶1前端产生和发展层流分离泡，从而导致产生较大的噪音。
而在本申请实施例中，设置沿桨叶1展向延伸的扰流部2，在桨叶1运行过程中，除了桨叶1搅动气流之外，该扰流部2也会进一步扰动气流。该扰流部2相当于一个前向台阶，能够干预上述的层流分离泡的产生和发展，使得层流区域的气流提前变化为湍流，即在气流流速较大时将层流转变为湍流，或者说，该扰流部2可以将层流转捩为湍流。
因此，使得湍流的流速增加，提高了湍流动能，从而使得湍流区域的气流能够更快的离开桨叶1表面，并降低了湍流边界层的厚度，进而减小了湍流区域的气流与桨叶1表面的碰撞区域，以降低噪音。
本申请实施例提供的螺旋桨，至少可以降低带宽噪声，还可以降低带宽噪声和谐波噪声，从而使得气动噪声降低。示例性地，经测试，本申请实施例提供的螺旋桨可以降低约2dBA(decibels adjusted，调整分贝)的噪声。此种降噪方式简单易行，具有较高的可行性，适用于各种工程应用，并且，此种降噪方式对桨叶1的气动特性影响较小，不会影响螺旋桨的正常使用。
示例性地，如图1和图4所示，沿桨叶1的弦长方向，桨叶1还包括相对设置的前缘11和后缘12，前缘11和后缘12之间的垂直距离为桨叶1的弦长c，扰流部2的中心线与前缘11之间的距离L1满足：0.05c≤L1≤0.6c。比如，该距离L1满足0.1c≤L1≤0.5c。
在本实施例中，若L1过小，如小于0.05c，则在桨叶1工作过程中扰流部2受到的气流的冲击过大，易发生扰流部2的损坏；若L1过大，如大于0.6c，则扰流部2位于湍流区域内或扰流部2位于湍流区域的后方，则扰流部2降噪效果低甚至失去作用。因此，0.05c≤L1≤0.6c，能够延长扰流部2的使用寿命，同时，提升扰流部2的降噪效果。
沿桨叶1运行方向，即图1中位于桨叶1左侧的箭头指示的方向，桨叶1的前端为前缘11，桨叶1的后端为后缘12。若桨叶1的前缘11和后缘12是平行的，则桨叶1在单位长度上的弦长c是定值，若桨叶1的前缘11和后缘12的形状变化规律不同，则桨叶1在单位长度上的弦长c是不断变化的，因此，扰流部2的中心线与前缘11之间的距离L1可以是定值，也可以是不断变化的。
示例性地，如图2和图3所示，沿桨叶1的弦长方向，螺旋桨使用环境的雷诺数为Re，扰流部2凸出顶面的高度为h满足：h＝kc/Re 0.2；其中，比例系数k满足：0.01≤k≤0.2。其中，顶面属于吸力面，则扰流部2凸出顶面的高度，可以认为是扰流部2凸出吸力面的高度，扰流部2凸出吸力面的高度在图3中表示为h，在图2中表示为H，即H满足：H＝kc/Re 0.2。
在本实施例中，若h过小，如小于0.01，则扰流部2能够干扰的湍流区域的气流量过小，导致扰流部2的降噪效果低；若h过大，如大于0.2，则扰流部2高出湍流区域而干扰层流区域的气流并产生较大的噪音。因此，h＝kc/Re 0.2且0.01≤k≤0.2，在确保扰流部2正常工作的同时，提升扰流部2的工作效果。
其中，若桨叶1的前缘11和后缘12是平行的，则沿桨叶1的展向，单位长度上的弦长c是定值，若桨叶1的前缘11和后缘12的形状变化规律不同，则单位长度上的弦长c是不断变化的，因此，扰流部2在单位长度上的凸出顶面的高度为h可以是定值，也可以是不断变化的。
示例性地，如图2～图4所示，扰流部2的宽度L2满足：0.05c≤L2≤0.5c。
在本实施例中，若L2＜0.05c，则扰流部2的宽度过小，导致扰流部2的强度差，在螺旋桨工作过程中，扰流部2在气流的作用下易发生变形，使得扰流部2失去作用甚至损坏；若L2＞0.5c，则扰流部2的宽度过大超过气流的湍流区域 而干扰层流区域的气流并产生较大的噪音。因此，0.05c≤L2≤0.5c，能够提高扰流部2的使用强度，延长扰流部2的使用寿命，同时，能够提升扰流部2的降噪效果，确保扰流部2的正常工作。
若桨叶1的前缘11和后缘12是平行的，则桨叶1的展向，单位长度上的弦长c是定值，若桨叶1的前缘11和后缘12的形状变化规律不同，则单位长度上的弦长c是不断变化的，因此，扰流部2的宽度L2可以是定值，也可以是不断变化的。
示例性地，如图2和图3所示，沿桨叶1的弦长方向，扰流部2包括相对设置的第一侧壁21和第二侧壁22，第一侧壁21的至少部分为锯齿形，和/或，第二侧壁22的至少部分为锯齿形。
在本实施例中，第一侧壁21的至少部分为锯齿形，和/或，第二侧壁22的至少部分为锯齿形，能够增加锯齿形的第一侧壁21和/或第二侧壁22与气流的接触面积，从而提升扰流部2的降噪效果，进而提升螺旋桨的使用性能。
示例性地，如图2所示，第一侧壁21的至少部分为平直形，和/或，第二侧壁22的至少部分为平直形。应理解的是，此处的锯齿形和平直形均为举例，不用于对扰流部2的侧壁形状造成限定，本申请实施例可以在保证扰流部2能够扰动气流的前提下，选择任意合适的形状作为扰流部2的侧壁形状。
示例性地，如图3所示，扰流部2包括第一侧面23和第二侧面24，多个第一侧面23和多个第二侧面24间隔设置且相互连接，以形成锯齿形的第一侧壁21和/或第二侧壁22；第一侧面23与第二侧面24之间的夹角α满足：10°＜α＜120°。
在本实施例中，第一侧面23和第二侧面24间隔设置且首尾相连，以形成锯齿形的第一侧壁21和/或第二侧壁22。若第一侧面23与第二侧面24之间的夹角α过大或过小，即相邻齿尖的距离S过大或过小，则导致第一侧面23和第二侧面24与气流的接触面积过小，从而降低扰流部2的降噪效果。因此，10°＜α＜120°，能够增加锯齿形的第一侧壁21和/或第二侧壁22与气流的接触面积，从而提升扰流部2的降噪效果，进而提升螺旋桨的使用性能。
以上任一实施例中，沿桨叶1厚度方向，桨叶1包括相对设置的顶面和底面，顶面和底面均为吸力面，扰流部2设置于顶面，或者，扰流部2设置于顶面和底面。
在本实施例中，螺旋桨工作过程中，沿桨叶1厚度方向，螺旋桨的上方所产 生的噪音大于螺旋桨下方所产生的噪音，因此，在桨叶1的顶面设置扰流部2，能够提高扰流部2的降噪效果，将扰流部2设置于顶面和底面，使得螺旋桨上方和下方的噪音均减小，从而进一步提高扰流部2的降噪效果。当然，示例性地，也可以仅在桨叶1的底面设置扰流部2，从而使得螺旋桨下方的噪音减小，则螺旋桨上方和下方的噪音之和也会减小，从而能够起到的降噪效果。
以上任一实施例中，沿桨叶1的展向，扰流部2贯穿桨叶1，或者，扰流部2覆盖桨叶1的一部分。其中，扰流部2贯穿桨叶1，也即是扰流部2在展向上覆盖桨叶1的全部，或者说，扰流部2在展向上的投影长度，等于桨叶1在展向上的投影长度。
在本实施例中，沿桨叶1的展向，扰流部2可以贯穿桨叶1，也可以仅覆盖桨叶1的一部分，从而增加扰流部2设置的灵活性。扰流部2沿桨叶1的展向贯穿桨叶1，能够增加扰流部2的作用范围，从而提升扰流部2的工作性能，更大程度的降低螺旋桨工作时所产生的噪声。扰流部2覆盖桨叶1的一部分，在满足螺旋桨的降噪需求的同时，减小扰流部2的尺寸，从而降低扰流部2的生产成本，同时，减小扰流部2的重量，进而减小螺旋桨的重量，增加螺旋桨的使用性能。
示例性地，扰流部2的数量为一个或多个；多个扰流部2间隔设置或连续设置。本申请实施例不限定扰流部2的数量和设置方式。当扰流部2的数量为一个时，该一个扰流部2的各处侧壁形状可以相同，也可以不同。比如，该一个扰流部2的所有侧壁形状均为锯齿形，或所有侧壁形状均为平直形，或一半侧壁形状为锯齿形且另一半侧壁形状为平直形，在此不作限定。当扰流部2的数量为多个时，不同扰流部2的侧壁形状包括但不限于：每两个扰流部2的侧壁形状均相同，或每两个扰流部2的侧壁形状均不同，或一部分扰流部2的侧壁形状相同且另一部分扰流部2的侧壁形状不同，此处不再举例赘述。
在本实施例中，扰流部2的数量为一个或多个；多个扰流部2间隔设置或连续设置，增加了桨叶1上设置扰流部2的灵活性。多个扰流部2间隔设置，在保证扰流部2降噪性能的同时，减小了扰流部2的材料，从而降低生产成本。
示例性地，当扰流部2的数量为多个时，可以是全部的扰流部2均间隔设置，或者全部的扰流部2均连续设置，或者一部分扰流部2间隔设置而另一部分扰流部2连续设置，设置方式较为灵活，可以根据经验或者实际需求选择合适的设置方式。
以上任一实施例中，扰流部2与桨叶1一体成型或固定连接。示例性地，固定连接包括：获取单独的扰流部2，以及单独的桨叶1，再将扰流部2拼装于桨叶1，使得扰流部2与桨叶1固定连接。
在本实施例中，扰流部2与桨叶1一体成型，增加了扰流部2与桨叶1的连接的稳固性，避免在螺旋桨工作过程中扰流部2与桨叶1脱离而引发安全问题，从而提升螺旋桨工作的稳定性和使用安全性。扰流部2与桨叶1固定连接，能够便于扰流部2和桨叶1的加工，从而降低扰流部2和桨叶1的加工成本。扰流部2与桨叶1一体成型或固定连接，增加了扰流部2和桨叶1的连接方式，从而增加了扰流部2与桨叶1连接的灵活性。
示例性地，如果有多个扰流部2，当扰流部2的数量为多个时，可以是全部的扰流部2均与桨叶1一体成型，或者全部的扰流部2均与桨叶1固定连接，或者一部分扰流部2与桨叶1一体成型而另一部分扰流部2与桨叶1固定连接。
本申请实施例还提供了一种飞行器，该飞行器包括本体和螺旋桨，螺旋桨为以上任一实施例中所述的螺旋桨；螺旋桨安装于本体。
在本实施例中，在螺旋桨上设置沿桨叶1弦长方向延伸的扰流部2来增加湍流流速，使得桨叶1表面产生噪声的区域减小，从而降低螺旋桨工作过程所产生的噪音，进而提升飞行器的使用性能，同时，能够提升飞行器的隐蔽性，进而提升飞行器的适用场景。也即是，提升飞行器的泛用性，使得飞行器能够适用于更多的场景，扩大了飞行器的适用范围。
示例性地，该飞行器包括但不限于：多旋翼类型的飞行器、垂直起降类型的飞行器，等等。其中，多旋翼类型的飞行器包括多个旋翼轴，上述的本体和螺旋桨可以通过旋翼轴连接。当然，本申请实施例不限定该飞行器的类型，只要该飞行器可以使用螺旋桨即可。
以上所述仅为本申请的实施例而已，并不用于限制本申请，对于本领域的技术人员来说，本申请可以有各种更改和变化。凡在本申请的原则之内，所作的任何修改、等同替换、改进等，均应包含在本申请的保护范围之内。

Claims (11)

  1. 一种螺旋桨，其中，所述螺旋桨包括：
    桨叶(1)；
    扰流部(2)，所述扰流部(2)的至少部分凸出所述桨叶(1)的吸力面；
    其中，所述扰流部(2)沿所述桨叶(1)的展向延伸。
  2. 根据权利要求1所述的螺旋桨，其中，沿所述桨叶(1)的弦长方向，所述桨叶(1)还包括相对设置的前缘(11)和后缘(12)，所述前缘(11)和所述后缘(12)之间的垂直距离为所述桨叶(1)的弦长c，所述扰流部(2)的中心线与所述前缘(11)之间的距离L1满足：0.05c≤L1≤0.6c。
  3. 根据权利要求1所述的螺旋桨，其中，沿所述桨叶(1)的弦长方向，所述桨叶(1)还包括相对设置的前缘(11)和后缘(12)，所述前缘(11)和所述后缘(12)之间的垂直距离为所述桨叶(1)的弦长c，所述螺旋桨使用环境的雷诺数为Re，所述扰流部(2)凸出所述吸力面的高度为h满足：h＝kc/Re 0.2；
    其中，比例系数k满足：0.01≤k≤0.2。
  4. 根据权利要求1所述的螺旋桨，其中，沿所述桨叶(1)的弦长方向，所述桨叶(1)还包括相对设置的前缘(11)和后缘(12)，所述前缘(11)和所述后缘(12)之间的垂直距离为所述桨叶(1)的弦长c，所述扰流部(2)的宽度L2满足：0.05c≤L2≤0.5c。
  5. 根据权利要求1所述的螺旋桨，其中，沿所述桨叶(1)的弦长方向，所述扰流部(2)包括相对设置的第一侧壁(21)和第二侧壁(22)，所述第一侧壁(21)的至少部分为锯齿形，和/或，所述第二侧壁(22)的至少部分为锯齿形。
  6. 根据权利要求5所述的螺旋桨，其中，扰流部(2)包括第一侧面(23)和第二侧面(24)，多个所述第一侧面(23)和多个所述第二侧面(24)间隔设置且相互连接，以形成锯齿形的所述第一侧壁(21)和/或所述第二侧壁(22)；
    所述第一侧面(23)与所述第二侧面(24)之间的夹角α满足：10°＜α＜ 120°。
  7. 根据权利要求1～6中任一项所述的螺旋桨，其中，沿所述桨叶(1)厚度方向，所述桨叶(1)包括相对设置的顶面和底面，所述顶面和所述底面均为所述吸力面，所述扰流部(2)设置于所述顶面，或者，所述扰流部(2)设置于所述顶面和所述底面。
  8. 根据权利要求1～6中任一项所述的螺旋桨，其中，沿所述桨叶(1)的展向，所述扰流部(2)贯穿所述桨叶(1)，或者，所述扰流部(2)覆盖所述桨叶(1)的一部分。
  9. 根据权利要求8所述的螺旋桨，其中，所述扰流部(2)的数量为一个或多个；
    多个所述扰流部(2)间隔设置或连续设置。
  10. 根据权利要求1～6中任一项所述的螺旋桨，其中，所述扰流部(2)与所述桨叶(1)一体成型或固定连接。
  11. 一种飞行器，其中，所述飞行器包括本体和权利要求1～10中任一项所述的螺旋桨；
    所述螺旋桨安装于所述本体。
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