WO2023124378A1 - Hélice et aéronef - Google Patents

Hélice et aéronef Download PDF

Info

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
Authority
WO
WIPO (PCT)
Prior art keywords
spoiler
blade
propeller
side wall
aircraft
Prior art date
Application number
PCT/CN2022/124711
Other languages
English (en)
Chinese (zh)
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/fr

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
    • 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.

Landscapes

  • 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

L'invention concerne une hélice et un aéronef. L'hélice comprend une pale d'hélice (1) et une partie déporteur (2). Au moins une partie de la partie déporteur (2) fait saillie par rapport à une surface d'aspiration de la pale d'hélice (1), et la partie déporteur (2) s'étend dans une direction d'envergure de la pale d'hélice (1).
PCT/CN2022/124711 2021-12-29 2022-10-11 Hélice et aéronef WO2023124378A1 (fr)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN202111633174.8 2021-12-29
CN202111633174.8A CN116409458A (zh) 2021-12-29 2021-12-29 一种螺旋桨和飞行器

Publications (1)

Publication Number Publication Date
WO2023124378A1 true WO2023124378A1 (fr) 2023-07-06

Family

ID=86997479

Family Applications (1)

Application Number Title Priority Date Filing Date
PCT/CN2022/124711 WO2023124378A1 (fr) 2021-12-29 2022-10-11 Hélice et aéronef

Country Status (2)

Country Link
CN (1) CN116409458A (fr)
WO (1) WO2023124378A1 (fr)

Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB372378A (en) * 1930-11-07 1932-05-09 Stone J & Co Ltd Improvements in and connected with screw propellers
CN107074344A (zh) * 2017-01-13 2017-08-18 深圳市大疆创新科技有限公司 飞行器的螺旋桨、动力套装及无人机
CN107089327A (zh) * 2017-04-26 2017-08-25 朱晓义 一种产生更大升力的飞行器
DE102017205912A1 (de) * 2017-04-06 2018-10-11 Lufthansa Technik Ag Selbstklebende Kunststofffolie
CN209080146U (zh) * 2018-11-20 2019-07-09 辽宁壮龙无人机科技有限公司 桨叶、螺旋桨及无人飞行器
CN209192204U (zh) * 2018-11-20 2019-08-02 辽宁壮龙无人机科技有限公司 螺旋桨和无人机
CN110466751A (zh) * 2019-09-03 2019-11-19 中国科学院合肥物质科学研究院 一种低噪声的高效便携式无人机旋翼结构及其设计方法
CN217227900U (zh) * 2021-12-29 2022-08-19 北京三快在线科技有限公司 一种螺旋桨和飞行器

Patent Citations (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
GB372378A (en) * 1930-11-07 1932-05-09 Stone J & Co Ltd Improvements in and connected with screw propellers
CN107074344A (zh) * 2017-01-13 2017-08-18 深圳市大疆创新科技有限公司 飞行器的螺旋桨、动力套装及无人机
DE102017205912A1 (de) * 2017-04-06 2018-10-11 Lufthansa Technik Ag Selbstklebende Kunststofffolie
CN107089327A (zh) * 2017-04-26 2017-08-25 朱晓义 一种产生更大升力的飞行器
CN209080146U (zh) * 2018-11-20 2019-07-09 辽宁壮龙无人机科技有限公司 桨叶、螺旋桨及无人飞行器
CN209192204U (zh) * 2018-11-20 2019-08-02 辽宁壮龙无人机科技有限公司 螺旋桨和无人机
CN110466751A (zh) * 2019-09-03 2019-11-19 中国科学院合肥物质科学研究院 一种低噪声的高效便携式无人机旋翼结构及其设计方法
CN217227900U (zh) * 2021-12-29 2022-08-19 北京三快在线科技有限公司 一种螺旋桨和飞行器

Also Published As

Publication number Publication date
CN116409458A (zh) 2023-07-11

Similar Documents

Publication Publication Date Title
CN107757879B (zh) 用于飞行器的机翼的翼尖装置、飞行器及用途
CN105556114B (zh) 用于风力涡轮机的涡流发生器
US20150217851A1 (en) Wing configuration
US6431498B1 (en) Scalloped wing leading edge
US20110006165A1 (en) Application of conformal sub boundary layer vortex generators to a foil or aero/ hydrodynamic surface
US20060006290A1 (en) Vorticity cancellation at trailing edge for induced drag elimination
US20010030264A1 (en) Method and apparatus for reducing trailing vortices in the wake of an aircraft
US20170138339A1 (en) Vortex generator, wind turbine blade, and wind turbine power generating apparatus
WO2009098442A2 (fr) Dispositifs de commande d’aile
US8827201B2 (en) Rotorcraft structural element for reducing aerodynamic drag
US9475578B2 (en) Rotary wing aircraft with a tail shroud
JP2016070089A (ja) ファン
WO2011098807A1 (fr) Appareil et procédé permettant une réduction de la traînée aérodynamique
US6899525B2 (en) Blade and wing configuration
WO2023124378A1 (fr) Hélice et aéronef
CN217227900U (zh) 一种螺旋桨和飞行器
CN219172657U (zh) 一种旋翼以及旋翼飞行器
US4795308A (en) Obstacle in front of a propeller
JP4676633B2 (ja) 回転翼航空機の回転翼羽根
Gong et al. On the aerodynamic loads and flow statistics of airfoil with deformable vortex generators
KR20110012448A (ko) 2메가와트급 풍력 발전기용 블레이드의 팁 에어포일
WO2011149440A2 (fr) Procédé d'amélioration de la réduction de traînée d'écoulement et de la production d'élévation à l'aide d'un dé-turbulateur
WO2024139168A1 (fr) Rotor et giravion
CN111043081A (zh) 一种轴流风扇及其在远程射雾器上的应用
JP2002166891A (ja) ブレード用高性能翼型

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: 22913642

Country of ref document: EP

Kind code of ref document: A1