-
公开(公告)号：WO2013095033A1
公开(公告)日：2013-06-27
申请号：PCT/KR2012/011248
申请日：2012-12-21
Applicant: 한국항공우주연구원
CPC classification number: F03D15/00 , F03D13/20 , F03D15/10 , F03D80/00 , F05B2240/14 , F05B2260/97 , Y02E10/72
Abstract: 본 발명은 풍력에 의해 전기에너지를 생산하는 풍력 발전기에 관한 것으로, 더욱 상세하게는 수평축 풍력발전기의 나셀에 펜스 구조물을 설치하며 공기역학적 성능을 향상시키는 나셀 펜스를 갖는 풍력발전기에 관한 것이다. 본 발명의 나셀 펜스를 갖는 풍력발전기는 회전하는 블레이드 하류단에서 발생하는 와류를 감소시켜, 블레이드의 공기역학적인 성능을 향상시키며 나아가 풍력발전기의 발전 효율을 증가시키는 효과가 있다.
Abstract translation: 本发明涉及一种用于产生电能的风力涡轮机，更具体地，涉及一种具有用于通过将篱笆结构安装在水平轴风力涡轮机的机舱上来提高空气动力学性能的机舱的风力涡轮机。 根据本发明的具有机舱围栏的风力涡轮机减小了在旋转叶片的下端处产生的涡流，以便提高叶片的空气动力学性能，并且提高了风力涡轮机的发电效率。
-
公开(公告)号：WO2012081926A3
公开(公告)日：2012-06-21
申请号：PCT/KR2011/009695
申请日：2011-12-16
Inventor： 김철완
Abstract: 본 발명은 장기 체공 풍력 비행기에 관한 것으로, 본 발명의 목적은 풍력 에너지를 동력원으로 사용하는 장기 체공 풍력 비행기를 제공함에 있다. 본 발명의 장기 체공 풍력 비행기는, 장기 체공을 목적으로 한 소형 무인 비행기에 있어서, 비행기 형상으로 형성되는 본체(110); 상기 본체(110)에 구비되며, 모터(121) 및 프로펠러(122)를 포함하여 구성되어 추력을 발생시키는 추력 발생부(120); 상기 본체(110)에 구비되며, 풍력을 이용하여 전력을 생산하여 상기 추력 발생부(120)로 전달하는 풍력 터빈(130); 를 포함하여 이루어지는 것을 특징으로 한다.
-
公开(公告)号：KR1020160080735A
公开(公告)日：2016-07-08
申请号：KR1020140193604
申请日：2014-12-30
Applicant: 한국항공우주연구원
Inventor： 김철완
IPC: B60L5/24
CPC classification number: B60L5/24
Abstract: 본발명은공력에의한소음을저감하기위한구조에관한것으로, 더욱상세하게는십만단위이상의고 레이놀즈수영역에서운용되는물체의공력소음을저감시킬수 있는, 고레이놀즈수영역에서의공력소음저감구조에관한것이다.
Abstract translation: 本发明涉及一种通过空气动力减小噪声的结构。 更具体地，本发明涉及具有高雷诺数的区域中的气动噪声降低结构，其可以减少在雷诺数高于或等于十万单位的区域中操作的物体的空气动力噪声。 具有高雷诺数的区域中的空气动力降噪结构在具有圆形，椭圆形或矩形横截面的物体的外表面中具有不平坦部分或多个突起。
-
公开(公告)号：KR101179277B1
公开(公告)日：2012-09-03
申请号：KR1020110140703
申请日：2011-12-23
Applicant: 한국항공우주연구원
CPC classification number: F03D15/00 , F03D13/20 , F03D15/10 , F03D80/00 , F05B2240/14 , F05B2260/97 , Y02E10/72 , Y02E10/722 , Y02E10/726
Abstract: PURPOSE: A wind turbine having a nacelle fence is provided to minimize the vortex in a lower end of a blade by installing a fence in a nacelle along a flow direction of air. CONSTITUTION: A wind turbine comprises one or more nacelle fences(50). The nacelle fences are separately installed at constant intervals in a downstream direction of a rotor blade(30), and formed on an upper part of a tower. The nacelle fences are extended from a surface of a nacelle(20) along a flow direction of air. A cross section of the nacelle fence is inclined at a predetermined angle to a rotary shaft. The cross section of the nacelle fence is oppositely inclined to the rotary direction of the blade.
Abstract translation: 目的：提供一种具有机舱围栏的风力涡轮机，以通过沿着空气的流动方向在机舱中安装围栏来最小化叶片下端的涡流。 构成：风力涡轮机包括一个或多个机舱围栏（50）。 机舱围栏在转子叶片（30）的下游方向上以恒定间隔分开安装，并形成在塔的上部。 机舱围栏沿着空气的流动方向从机舱（20）的表面延伸。 机舱围栏的横截面以与旋转轴成预定角度倾斜。 机舱围栏的横截面相对于叶片的旋转方向倾斜。
-
公开(公告)号：KR1020160072522A
公开(公告)日：2016-06-23
申请号：KR1020140180245
申请日：2014-12-15
Applicant: 한국항공우주연구원
IPC: B64C27/28
CPC classification number: B64C27/28
Abstract: 본발명은틸트로터항공기용날개(10)에관한것으로, 더욱상세하게설명하면, 틸트로터항공기의이착륙또는정지비행시 날개(10) 하단에발생되는와류를분산또는상쇄시켜, 이착륙또는정지비행에필요한에너지를줄일수 있는틸트로터항공기용날개(10)에관한것이다. 본발명의구성은상기날개(10)의외측에구비되는회전로터(100); 상기날개(10)의후단에상하방향으로회전가능하도록구비되는후단플랩(200); 및상기날개(10)의전단에상하방향으로회전가능하도록구비되고, 상기날개(10)의하단에밀착되는전단플랩(300);을포함하여이루어진다.
Abstract translation: 本发明涉及一种用于倾斜转子飞机的叶片（10），更具体地涉及一种用于倾斜转子飞机的叶片（10），其能够通过分散或抵消涡流来降低起飞和着陆或悬停飞行所需的能量 当倾斜转子飞机起飞着陆或悬停时，在叶片（10）的下端产生。 叶片（10）包括：转子（100），安装在叶片（10）的外侧上; 安装在所述叶片（10）的后端以垂直旋转的后端翼片（200） 以及安装在所述叶片（10）的前端处以垂直旋转并附接到所述叶片（10）的下端的前端翼片（300）。
-
Patent Agency Ranking
公开(公告)号：KR1020140098600A
公开(公告)日：2014-08-08
申请号：KR1020130011461
申请日：2013-01-31
Applicant: 한국항공우주연구원
IPC: B64C3/14
Abstract: In relation to an airfoil used for an ultralight airplane which cruises at low speed, the present invention relates to an airfoil for a ultralight airplane, which keeps aerodynamic performance of a main airfoil made of myler or plastic material by minimizing change in pressure which the main airfoil experiences through reducing curvature of a curved surface from a leading edge to the lower surface, and enhances convenience in manufacturing and structural strength by increasing thickness of a trailing edge.
Abstract translation: 关于用于以低速航行的超轻型飞机的翼型，本发明涉及一种用于超轻型飞机的翼型，其通过最小化压力变化来保持由迈勒或塑料材料制成的主翼型的空气动力学性能，主翼 机翼通过从前缘到下表面的弯曲表面的曲率减小而经历，并且通过增加后缘的厚度来提高制造和结构强度的便利性。
-
公开(公告)号：KR1020130072035A
公开(公告)日：2013-07-01
申请号：KR1020110139579
申请日：2011-12-21
Applicant: 한국항공우주연구원
IPC: F03D11/00
CPC classification number: F03D1/0641 , F05B2240/221 , F05B2240/301 , Y02E10/72
Abstract: PURPOSE: A blade airfoil for an aerogenerator is provided to improve an output performance of a blade by a high lift-drag ratio while a structural rigidity is maintained by forming a maximum thickness ratio as 18% in a cross section airfoil used in a tip vicinity of a blade. CONSTITUTION: A blade airfoil for an aerogenerator comprises an airfoil used in a tip vicinity of a blade. A maximum thickness ratio (t/c) which is a rate of a maximum thickness (t) to a lower side from an upper side and a code length (c) of a code which is a straight line which continues a leading edge and a trailing edge is 18% in the airfoil. A reynold's number (Re# = air density * speed of wind * code length / air viscosity coefficient) which the airfoil is operated is 2,000,000 to 3,000,000.
Abstract translation: 目的：提供一种用于风力发电机的叶片翼型，以通过在尖端附近使用的横截面翼型中形成最大厚度比为18％来保持结构刚度而通过高提升阻力比提高叶片的输出性能 的刀片。 构成：用于风力发电机的叶片翼型件包括用于叶片附近尖端的翼型件。 作为上侧的下侧的最大厚度（t）的比率和作为向前方延续的直线的代码的代码长度（c）的最大厚度比（t / c） 翼型的后缘为18％。 机翼运行的雷诺数（Re＃=空气密度*风速*码长/空气粘度系数）为2,000,000至3,000,000。
-
公开(公告)号：KR1020110078430A
公开(公告)日：2011-07-07
申请号：KR1020090135243
申请日：2009-12-31
Applicant: 한국항공우주연구원
CPC classification number: Y02E10/74 , F03D3/005 , F03D3/06 , F03D17/00 , F05B2240/20 , F05B2240/211 , F05B2260/80
Abstract: PURPOSE: A wind power turbine testing apparatus is provided to promote the effective wind power turbine development by grasping the aerodynamic performance of a vertical shaft wind power turbine blade using a measurement sensor to a blade of a vertical shaft wind power turbine. CONSTITUTION: A wind power turbine testing apparatus comprises a support(10), a rotary shaft(20) coupled to the support, a rotary motor(30) coupled to the bottom of the rotary shaft to rotate the rotary shaft, a rotary bottom plate(40) and a rotary top plate(50) coupled to the rotary shaft to fix blades, plural non-measurement blades(61) coupled between the rotary bottom plate and the rotary top plate, a measurement blade(62) coupled to the rotary top plate, and a measurement sensor(70) provided to the measurement blade to measure the power and moment acting on the measurement blade.
Abstract translation: 目的：提供一种风力发电涡轮机测试装置，通过使用测量传感器将垂直轴风力发电机叶片的空气动力学性能掌握到垂直轴风力涡轮机的叶片来促进有效的风力涡轮机开发。 构成：风力涡轮机测试装置包括支撑件（10），联接到支撑件的旋转轴（20），联接到旋转轴的底部以旋转旋转轴的旋转马达（30），旋转底板 （40）和联接到所述旋转轴以固定叶片的旋转顶板（50），耦合在所述旋转底板和所述旋转顶板之间的多个非测量叶片（61），耦合到所述旋转底板 顶板和设置到测量刀片的测量传感器（70），以测量作用在测量叶片上的功率和力矩。
-
公开(公告)号：KR1020100072622A
公开(公告)日：2010-07-01
申请号：KR1020080131078
申请日：2008-12-22
Applicant: 한국항공우주연구원
Inventor： 김철완
Abstract: PURPOSE: A low-noise airfoil using a dimple is provided to remarkably reduce noise and drag by stabilizing wake occurred in the rear part of the airfoil. CONSTITUTION: A low-noise airfoil using a dimple comprises a blade(1) and multiple dimples(2). The dimples are formed on the front end surface(S) of the blade. The angle of attack of the front end surface is in a 0° to 90° range. The air foil remarkably stabilizes wake occurred in the rear part of the blade and reduces noise occurred in the blade.
Abstract translation: 目的：提供使用凹坑的低噪声翼型，以通过稳定翼型后部发生的尾迹来显着降低噪音和阻力。 构成：使用凹坑的低噪声翼型包括叶片（1）和多个凹坑（2）。 凹坑形成在叶片的前端表面（S）上。 前端面的攻角为0°〜90°。 风叶在叶片的后部显着地稳定了尾迹，并降低了叶片中的噪音。
-
公开(公告)号：KR1020130072022A
公开(公告)日：2013-07-01
申请号：KR1020110139563
申请日：2011-12-21
Applicant: 한국항공우주연구원
CPC classification number: Y02E10/721 , F03D1/0633 , F05B2240/221 , F05B2240/301 , Y02E10/72
Abstract: PURPOSE: A blade airfoil for an aerogenerator is provided to have a high lift-drag ratio, and to maintain a structural rigidity by forming a maximum thickness rate as 30% at a cross section airfoil used in a root vicinity of a blade. CONSTITUTION: A blade airfoil for an aerogenerator comprises an airfoil used in a root vicinity of a blade. A maximum thickness ratio (t/c) which is a rate of a maximum thickness (t) to a lower side from an upper side and a code length (c) of a code which is a straight line which continues a leading edge and a trailing edge is 30% in the airfoil. A reynold's number (Re# = air density * speed of wind * code length / air viscosity coefficient) in which the airfoil is operated is 2,000,000 to 3,000,000.
Abstract translation: 目的：提供用于风力发电机的叶片翼型具有高的提升阻力比，并且通过在用于叶片根部附近的横截面翼型上形成最大厚度率为30％来保持结构刚度。 构成：用于风力发电机的叶片翼型件包括用于叶片根部附近的翼型件。 作为上侧的下侧的最大厚度（t）的比率和作为向前方延续的直线的代码的代码长度（c）的最大厚度比（t / c） 后翼在翼型中为30％。 机翼运行的雷诺数（Re＃=空气密度*风速*码长/空气粘度系数）为2,000,000至3,000,000。
-
-
-
-
-
-
-
-
-
Search Results
18
records
(took 0.02 seconds)
