EA201500723A1 - METHOD OF DESIGNING A THREE-DIMENSIONAL CURVED AERODYNAMIC PROFILE - Google Patents

METHOD OF DESIGNING A THREE-DIMENSIONAL CURVED AERODYNAMIC PROFILE

Info

Publication number
EA201500723A1
EA201500723A1 EA201500723A EA201500723A EA201500723A1 EA 201500723 A1 EA201500723 A1 EA 201500723A1 EA 201500723 A EA201500723 A EA 201500723A EA 201500723 A EA201500723 A EA 201500723A EA 201500723 A1 EA201500723 A1 EA 201500723A1
Authority
EA
Eurasian Patent Office
Prior art keywords
aerodynamic profile
section
dimensional
profile
cross
Prior art date
Application number
EA201500723A
Other languages
Russian (ru)
Other versions
EA029645B1 (en
Inventor
Юйци Чэнь
Original Assignee
Синьцзянь Шаньфу Нью Энерджи Текнолоджи Ко., Лтд.
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 Синьцзянь Шаньфу Нью Энерджи Текнолоджи Ко., Лтд. filed Critical Синьцзянь Шаньфу Нью Энерджи Текнолоджи Ко., Лтд.
Publication of EA201500723A1 publication Critical patent/EA201500723A1/en
Publication of EA029645B1 publication Critical patent/EA029645B1/en

Links

Classifications

    • B—PERFORMING OPERATIONS; TRANSPORTING
    • B64—AIRCRAFT; AVIATION; COSMONAUTICS
    • B64C—AEROPLANES; HELICOPTERS
    • B64C3/00—Wings
    • B64C3/10—Shape of wings
    • B64C3/14—Aerofoil profile
    • 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
    • B64C27/00—Rotorcraft; Rotors peculiar thereto
    • B64C27/32—Rotors
    • B64C27/46—Blades
    • B64C27/467—Aerodynamic features
    • Y—GENERAL TAGGING OF NEW TECHNOLOGICAL DEVELOPMENTS; GENERAL TAGGING OF CROSS-SECTIONAL TECHNOLOGIES SPANNING OVER SEVERAL SECTIONS OF THE IPC; TECHNICAL SUBJECTS COVERED BY FORMER USPC CROSS-REFERENCE ART COLLECTIONS [XRACs] AND DIGESTS
    • Y02—TECHNOLOGIES OR APPLICATIONS FOR MITIGATION OR ADAPTATION AGAINST CLIMATE CHANGE
    • Y02T—CLIMATE CHANGE MITIGATION TECHNOLOGIES RELATED TO TRANSPORTATION
    • Y02T50/00—Aeronautics or air transport
    • Y02T50/10—Drag reduction

Landscapes

  • Engineering & Computer Science (AREA)
  • Aviation & Aerospace Engineering (AREA)
  • Mechanical Engineering (AREA)
  • Physics & Mathematics (AREA)
  • Fluid Mechanics (AREA)
  • Wind Motors (AREA)
  • Turbine Rotor Nozzle Sealing (AREA)
  • Structures Of Non-Positive Displacement Pumps (AREA)

Abstract

Способ проектирования сечения трёхмерного изогнутого профиля аэродинамической поверхности. Данный способ включает в себя следующие шаги: сбор данных координат дуги сечения стандартного двухмерного аэродинамического профиля, таких как (x, у) и (х, у); в соответствии с данными координат сечения стандартного аэродинамического профиля, вычисление приращения между точками координат по оси х хорды; определение радиуса вращения R сечения аэродинамического профиля согласно проекту; создание координат дуги (х, y, z) сечения трёхмерного аэродинамического профиля, где у- значение координаты по толщине двухмерного профиля; и по аналогии - вычисление группы координат (х, у, z) дуги сечения трёхмерного аэродинамического профиля и т.д. Данный способ улучшает аэродинамический профиль лопасти путем оптимизации сечения трёхмерного изогнутого аэродинамического профиля, и соответствующего увеличения эффективности аэродинамической силы лопасти несущего винта, изготовленной из тех же материалов и имеющей те же структурные характеристики.A method for designing a cross section of a three-dimensional curved profile of an aerodynamic surface. This method includes the following steps: collecting coordinate data of the arc section of a standard two-dimensional aerodynamic profile, such as (x, y) and (x, y); in accordance with the coordinate data of the section of the standard aerodynamic profile, calculating the increment between the coordinate points along the x axis of the chord; determination of the radius of rotation R of the cross section of the aerodynamic profile according to the project; creation of the coordinates of the arc (x, y, z) of the cross section of the three-dimensional aerodynamic profile, where y is the coordinate value along the thickness of the two-dimensional profile; and by analogy - the calculation of the group of coordinates (x, y, z) of the cross-sectional arc of a three-dimensional aerodynamic profile, etc. This method improves the aerodynamic profile of the blade by optimizing the cross-section of a three-dimensional curved aerodynamic profile, and a corresponding increase in the efficiency of the aerodynamic force of the rotor blade made of the same materials and having the same structural characteristics.

EA201500723A 2013-02-05 2013-04-10 Design method for three-dimensional curved airfoil section EA029645B1 (en)

Applications Claiming Priority (2)

Application Number Priority Date Filing Date Title
CN201310053925.8A CN103967718B (en) 2013-02-05 2013-02-05 The method for designing of three-dimension curved surface aerofoil profile
PCT/CN2013/074018 WO2014121554A1 (en) 2013-02-05 2013-04-10 Design method for three-dimensional curved airfoil section

Publications (2)

Publication Number Publication Date
EA201500723A1 true EA201500723A1 (en) 2015-12-30
EA029645B1 EA029645B1 (en) 2018-04-30

Family

ID=51237627

Family Applications (1)

Application Number Title Priority Date Filing Date
EA201500723A EA029645B1 (en) 2013-02-05 2013-04-10 Design method for three-dimensional curved airfoil section

Country Status (3)

Country Link
CN (1) CN103967718B (en)
EA (1) EA029645B1 (en)
WO (1) WO2014121554A1 (en)

Families Citing this family (8)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
CN104881510B (en) * 2015-02-13 2018-06-05 南京航空航天大学 A kind of lifting airscrew/tail-rotor aerodynamic interference numerical value emulation method
CN108100195B (en) * 2016-11-25 2019-09-17 成都天府新区光启未来技术研究院 Method and apparatus for Design of Propeller
CN109229417B (en) * 2018-08-06 2020-08-21 浙江工业大学 Bionic combined wing section design method based on wing carving
CN109185009B (en) * 2018-09-07 2020-05-08 杭州江河水电科技有限公司 Passive self-adaptive reciprocating bidirectional water flow impeller device
RU2769545C1 (en) * 2021-05-14 2022-04-04 Акционерное общество "Национальный центр вертолетостроения им. М.Л. Миля и Н.И. Камова" (АО "НЦВ Миль и Камов") Aerodynamic profile of the lifting element of the aircraft
CN113970311A (en) * 2021-10-12 2022-01-25 中国航空工业集团公司北京长城计量测试技术研究所 Aero-engine blade vector approximation iterative measurement method
CN115544667B (en) * 2022-10-31 2024-05-10 南京航空航天大学 Equivalent disk method based on phyllanthus momentum source coupling CFD
CN117313235A (en) * 2023-09-23 2023-12-29 哈尔滨工业大学 Special unmanned aerial vehicle optimized wing blade design method based on machine learning

Family Cites Families (5)

* Cited by examiner, † Cited by third party
Publication number Priority date Publication date Assignee Title
US3625459A (en) * 1970-05-18 1971-12-07 Walter C Brown Airfoil design
US7941300B1 (en) * 2008-02-29 2011-05-10 Florida Turbine Technologies, Inc. Process for the design of an airfoil
CN101968821B (en) * 2009-07-28 2013-05-01 联合船舶设计发展中心 Airfoil profile design method and structure applicable for multi-speed domain
CN101923584B (en) * 2009-10-30 2012-08-15 重庆大学 Method for designing special wind turbine airfoil profile and special wind turbine airfoil profile
CN102235325B (en) * 2011-07-01 2012-10-31 重庆大学 Method for designing airfoil section of blade tip of wind machine based on airfoil section integration and mixed trailing edge modification

Also Published As

Publication number Publication date
EA029645B1 (en) 2018-04-30
WO2014121554A1 (en) 2014-08-14
CN103967718A (en) 2014-08-06
CN103967718B (en) 2016-10-05

Similar Documents

Publication Publication Date Title
EA201500723A1 (en) METHOD OF DESIGNING A THREE-DIMENSIONAL CURVED AERODYNAMIC PROFILE
MX2015007582A (en) Turbomachine blade, corresponding turbomachine and method of manufacturing a turbine blade.
EP2557503A3 (en) Application performance measurement and reporting
RU2013127596A (en) THE READY PRODUCT HAVING AERODYNAMIC PART WITH THE SIDE OF THE REDUCED PRESSURE OF THE SET PROFILE, AND THE COMPRESSOR
RU2016118151A (en) NON-AXISYMMETRIC SURFACE GAS-TURBINE ENGINE DETAIL
RU2014110074A (en) DEVICE FOR DESIGNING PLANES, PROGRAM FOR DESIGNING PLANES AND METHOD OF DESIGNING PLANES
CN104239599A (en) Dynamics simulated analysis method on basis of multipoint positioning flexibility tool system
EP2955243A3 (en) Methods of manufacturing a shroud abradable coating
WO2014197136A3 (en) Systems and methods for feedback while designing an architectural structure
CN104008257A (en) Reversal design method for component with complex curved surface
CN104166752A (en) Hydraulic torque converter full-flow-channel transient numerical simulation calculation method
CN105426565A (en) Probability density technology based geometrical tolerance distribution method for large high-speed rotary equipment
JP2014139430A5 (en)
CN105351248B (en) A kind of fan high-performance aerofoil profile
CN104598685A (en) Centrifugal pump impeller hydraulic power diagram generating method based on three-dimensional digital model
Oggiano CFD simulations on the NTNU wind turbine rotor and comparison with experiments
FR2982518B1 (en) DESIGN OF A PIECE OF 3D COMPOSITE MATERIAL
EP2618312A3 (en) System and method for snapping normals to create fair 3D surfaces from edge curves
CN103256251A (en) Variable-curvature arc equal-thickness plate wing section for fan group
WO2014006467A3 (en) Tip fabrication for rotor blade or stator vane airfoil
CN103016398B (en) Centrifugal impeller flow passage design method for controlling curvature distribution
CN104978485A (en) Method for calculating wing bending rigidity of high-aspect-ratio aircraft
AR095316A1 (en) SYSTEMS AND METHODS TO ANALYZE THE TEXTURE OF A COVERED SURFACE, THROUGH THE USE OF MULTIDIMENSIONAL GEOMETRIES
Fruth Reduction of Aerodynamic Forcing in Transonic Turbomachinery
BR112016004261A8 (en) manufacturing methods for fabricating a reinforcing edge of a turbine engine blade and a turbine engine blade