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51. 发明公开

KR1020110121226A 엔진 냉각용 덕트 구조 无效
标题翻译：用于冷却发动机的导管结构
公开(公告)号：KR1020110121226A
公开(公告)日：2011-11-07
申请号：KR1020100040726
申请日：2010-04-30
申请人： 한국항공우주산업 주식회사
发明人： 이태호 , 김진성 , 김재혁
IPC分类号： B64D33/08 , F01P1/00 , B64D33/10
CPC分类号： B64D33/08 , B64D13/006 , F01P1/06 , F01P5/06 , F01P2050/20
摘要： PURPOSE: A duct structure for engine cooling is provided to directly supply external air in an engine cooling fin and remove air flow in a region far from the cooling fin, thereby improving engine cooling performance by inducing optimized air flow. CONSTITUTION: A duct structure for engine cooling comprises a front duct(100), a rear duct(200), and a coupling device(300). The front duct is installed in the front side of an engine cooling fin(400) in order to induce external air into the engine cooling fin. The rear duct is installed in the rear side of the cooling fin and discharges air passed the cooling fin to the rear side. The coupling device arranges an air path surrounding the cooling fin by connecting the front duct with the rear duct.
摘要翻译：目的：提供用于发动机冷却的管道结构，以直接供应发动机冷却翅片中的外部空气，并且去除远离冷却翅片的区域中的空气流动，从而通过诱导优化的气流来改善发动机冷却性能。构成：用于发动机冷却的管道结构包括前管道（100），后管道（200）和联接装置（300）。前管道安装在发动机冷却翅片（400）的前侧，以便将外部空气引入发动机冷却翅片。后管安装在冷却翅片的后侧，将通过冷却翅片的空气排放到后侧。联接装置通过将前管道与后管道连接来布置围绕冷却翅片的空气路径。

52. 发明公开

KR1020110059889A 인터쿨러 및 애프터쿨러의 냉간 연료 냉각 无效
标题翻译：冷却器和冷却器的冷却冷却
公开(公告)号：KR1020110059889A
公开(公告)日：2011-06-07
申请号：KR1020117009156
申请日：2009-09-23
申请人： 에어로바이론먼트 인크
发明人： 브룩스알렉산더넬슨 , 데일리제임스갤러거 , 힙스바트딘
IPC分类号： F02M31/20 , B60H1/00
CPC分类号： F02B43/00 , F01P2050/20 , F01P2060/02 , F01P2060/10 , F02B29/0412 , F02B29/0493 , F02C6/12 , F02C7/143 , F02C7/16 , F02C7/224 , F02M31/02 , F02M31/16 , F02M31/20 , F05D2260/205 , Y02T10/126 , Y02T10/146 , Y02T50/675
摘要： 높은 고도의 항공기 파워플랜트는 엔진, 인터쿨러 및 애프터쿨러를 갖는 2단 터보차저, 극저온 수소 연료 공급원, 및 수소 열교환기를 포함하는 냉각 시스템을 포함한다. 냉각제를 인접한 주변 온도로 냉각시키는 램에어 냉각기에 의해, 열교환기는 냉각제를 이용하여 수소를 가열하고, 높은 고도의 비행 중에 주변 온도 미만의 온도로 냉각제를 냉각시키도록 구성된다. 인터쿨러 및 애프터쿨러는 별개의 센서와 마찬가지로 주변 온도 미만의 냉각제를 이용한다. 램에어 냉각기는 전방 부분 및 후방 부분을 포함한다. 냉각 시스템은 램에어 냉각기의 전방부분 만을, 후방 부분 만을, 그리고 두 부분 모두를 각각 포함하는 3개의 냉각 후프를 포함한다.

53. 发明公开

KR1020110052370A 무인헬리콥터용 공냉식엔진 냉각장치 有权
标题翻译：空中冷却发动机冷却装置的无人直升机
公开(公告)号：KR1020110052370A
公开(公告)日：2011-05-18
申请号：KR1020090109367
申请日：2009-11-12
申请人： (주)한성티앤아이
发明人： 황인성
IPC分类号： B64D33/08 , B64D33/10 , B64C27/04
CPC分类号： B64D33/08 , B64C27/12 , F01P2001/026 , F01P2003/025 , F01P2050/20
摘要： PURPOSE: An air-cooling engine cooking device for an automatic helicopter is provided to cool heat from the engine since a cooling fin for cooling heat in operation of the engine and a cooling-water circulating pipe are formed on the outer side of the cylinder head of the air-cooling engine for the automatic helicopter. CONSTITUTION: An air-cooling engine cooking device for an automatic helicopter comprises a cooling fin(12), a pipe(20), an inlet(22) and an outlet(23). The cooling fin is formed on the outer wall of the cylinder head on both sides of the body(11) of the air-cooling engine(10). The pipe comprises a cooling-water circulating path. The inlet and the outlet are formed integrally with the pipe. Cooling water flows in through the inlet and is discharged through the outlet. The inlet is formed on one side of the upper part of the pipe and the outlet is formed on the other side of the lower part of the pipe in a diagonal direction.
摘要翻译：目的：提供一种用于自动直升机的空气冷却发动机烹饪装置，用于冷却发动机的热量，因为在发动机运转时用于散热的冷却翅片和冷却水循环管形成在气缸盖的外侧的自动直升机的空气冷却发动机。构成：用于自动直升机的空气冷却发动机烹调装置包括冷却翅片（12），管道（20），入口（22）和出口（23）。冷却翅片在空气冷却发动机（10）的主体（11）的两侧形成在气缸盖的外壁上。管道包括冷却水循环路径。入口和出口与管道一体形成。冷却水通过入口流入，并通过出口排出。入口形成在管的上部的一侧上，并且出口在对角线方向上形成在管的下部的另一侧。

54. 发明授权

KR101453325B1 키트형 헬리콥터 엔진실 냉각시스템 有权
标题翻译：发动机冷却系统用于工具包型直升机
公开(公告)号：KR101453325B1
公开(公告)日：2014-10-21
申请号：KR1020140103171
申请日：2014-08-11
申请人： 경남과학기술대학교 산학협력단 , (주) 피트게러지 인터그레이션
发明人： 이치우 , 김종호
IPC分类号： B64D33/08 , F01P1/00
CPC分类号： F01P1/00 , B60K11/06 , B64D33/08 , F01P5/02 , F01P2005/025 , F01P2050/20
摘要： The present invention relates to a system for cooling an engine room of a kit-type helicopter, which makes cold air fed to the engine room flow in the traveling direction of the helicopter at the driving of a cooling fan when the helicopter flies, and accelerates the flow of the cold air and prevents the cold air from flowing backward around the cooling fan to improve the cooling performance. The system includes a radiator installed in an engine room with an air inlet port and an air outlet port; a main cooling fan which is installed to be able to rotate at the rear of the radiator and radiates the cold air passing through the engine and the radiator to the outside of the engine room; a shroud which encloses the main cooling fan to guide the cold air to smoothly flow in or out; and an auxiliary fan fixed to a joint hub, to which the main cooling fan is mounted, to increase rotation of the sucked air generated in rear of the main cooling fan and thus increase the volume of the air passing through the air outlet port.
摘要翻译：本发明涉及一种用于冷却套件式直升机的发动机室的系统，当直升机飞行时，使冷空气供给到发动机室的空气在直升机的行进方向上流动，在冷却风扇的驱动下加速冷空气的流动并防止冷空气围绕冷却风扇回流，以提高冷却性能。该系统包括安装在具有进气口和空气出口的发动机室中的散热器; 主冷却风扇，其安装成能够在散热器的后部旋转并且将通过发动机和散热器的冷空气辐射到发动机室的外部; 封闭主冷却风扇以引导冷空气平稳流入或流出的护罩; 以及辅助风扇，其固定到主冷却风扇安装到的接头毂上，以增加主冷却风扇后部产生的吸入空气的旋转，从而增加通过空气出口的空气的体积。

55. 发明公开

KR1020140118367A 항공기용 엔진 냉각 시스템 有权
标题翻译：发动机冷却系统
公开(公告)号：KR1020140118367A
公开(公告)日：2014-10-08
申请号：KR1020130034117
申请日：2013-03-29
申请人： 한국항공우주산업 주식회사
发明人： 박성환 , 강성수 , 정광채 , 김상선 , 이성구 , 정년수 , 박선욱
IPC分类号： B64D33/08 , F01P7/02 , B64D33/04 , B64D29/00
CPC分类号： B64D33/08 , B64D13/006 , B64D29/06 , F01P1/06 , F01P2050/20
摘要： The present invention relates to an engine cooling system for an airplane. The engine cooling system for an airplane according to one embodiment of the present invention includes a cowl which surrounds an aerial engine and a baffle which divides the inner part of the cowl into an upper part and a lower part. According to one embodiment of the present invention, an air inlet is formed in one side of the cowl. An air outlet is formed in the other side of the cowl. According to one embodiment of the present invention, the baffle is formed in the inner part of the baffle. More particularly, in an aspect of the present invention, the engine cooling system for an airplane can include other embodiments.
摘要翻译：本发明涉及一种用于飞机的发动机冷却系统。根据本发明的一个实施例的用于飞机的发动机冷却系统包括围绕空中发动机的整流罩和将整流罩的内部分成上部和下部的挡板。根据本发明的一个实施例，在整流罩的一侧形成空气入口。在整流罩的另一侧形成出气口。根据本发明的一个实施例，挡板形成在挡板的内部。更具体地，在本发明的一个方面，用于飞机的发动机冷却系统可以包括其他实施例。

56. 发明公开

KR1020100109717A 무인헬기의 엔진 냉각 시스템 失效
标题翻译：用于无人驾驶直升机的发动机冷却系统
公开(公告)号：KR1020100109717A
公开(公告)日：2010-10-11
申请号：KR1020090028125
申请日：2009-04-01
申请人： 원신 스카이텍 주식회사
发明人： 한재섭 , 여홍태 , 양재익 , 정명호 , 윤성용
IPC分类号： B64D33/10 , B64C27/04 , B64D33/08 , B64C27/12
CPC分类号： B64D33/10 , B64C27/12 , B64C2201/024 , F01P5/10 , F01P2025/50 , F01P2050/20
摘要： PURPOSE: An engine cooling system for an unmanned helicopter is provided to prevent the overheating of a rotary engine implementing high-speed rotation of a rotor. CONSTITUTION: An engine cooling system for an unmanned helicopter comprises a rotary engine(110), a generator(130), a cooling fan(140), a water pump(150), and radiators(161,162). The generator comprises a generator rotary shaft which is coaxially connected to the output shaft of the rotary engine. The cooling fan comprises a cooling fan rotary shaft which is coaxially connected to the generator rotary shaft. The water pump comprises a water pump driving shaft which is coaxially connected to the cooling fan rotary shaft. The radiators are connected between the water jacket of the rotary engine and the water pump. Cooling water circulates with the drive of the water pump successively through the water pump, the radiators, and the water jacket of the rotary engine. Exterior air is drawn in through the radiators with the drive of the cooling fan and cools the engine cover of the rotary engine.
摘要翻译：目的：提供用于无人直升机的发动机冷却系统，以防止实现转子高速旋转的旋转发动机的过热。构成：用于无人直升机的发动机冷却系统包括旋转发动机（110），发电机（130），冷却风扇（140），水泵（150）和散热器（161,162）。发电机包括同轴连接到旋转发动机的输出轴的发电机旋转轴。冷却风扇包括与发电机旋转轴同轴连接的冷却风扇旋转轴。水泵包括与冷却风扇旋转轴同轴连接的水泵驱动轴。散热器连接在旋转发动机的水套和水泵之间。冷却水随着水泵的驱动顺序循环通过水泵，散热器和旋转发动机的水套。外部空气通过散热器与冷却风扇的驱动器一起吸入，并冷却旋转发动机的发动机盖。

57. 发明公开

KR1020080042267A 엔진 배기가스를 이용한 엔진 냉각장치 有权
标题翻译：使用发动机排气的发动机冷却系统，用于冷却空气流
公开(公告)号：KR1020080042267A
公开(公告)日：2008-05-15
申请号：KR1020060110448
申请日：2006-11-09
申请人： 주식회사 썬에어로시스 , 한국항공우주연구원
发明人： 박선태 , 김승주 , 김중욱
IPC分类号： B64D33/08 , B64D33/04
CPC分类号： B64D33/08 , B64C27/04 , B64C29/02 , B64C2201/024 , B64C2201/108 , B64C2201/165 , B64D2033/022 , F01P1/00 , F01P11/12 , F01P2050/20
摘要： An engine cooling system using engine exhaust gas is provided to maintain a temperature of an engine at a predetermined level by rapidly sucking and exhausting air in case of vertical takeoff and landing of UAV(Unmanned Aerial Vehicle) or an R/C(Remote Control) model aerial vehicle. An engine cooling system using engine exhaust gas includes a front air inlet(10), an air passage(20), an air outlet(30), an engine(40), and an exhaust pipe(50). The front air inlet is installed at one side of an aerial vehicle body. One end of the air passage is connected to the front air inlet and has a predetermined rear length along the aerial vehicle body. The air outlet is connected to the other end of the air passage and passes through an outer wall of a rear side of the aerial vehicle body. The engine is installed in the air passage. The exhaust pipe is installed at the engine and has a predetermined rear length along the air passage. The engine cooling system is mounted at a UAV(Unmanned Aerial Vehicle) or an R/C(Remote Control) model aerial vehicle.
摘要翻译：提供使用发动机废气的发动机冷却系统，以在UAV（无人机）或R / C（遥控））的垂直起飞和着陆的情况下，通过快速吸入和排出空气来将发动机的温度维持在预定水平，模型飞行器。使用发动机排气的发动机冷却系统包括前空气入口（10），空气通道（20），空气出口（30），发动机（40）和排气管（50）。前进气口安装在飞行器体的一侧。空气通道的一端连接到前空气入口，并沿着飞行器体具有预定的后长度。空气出口连接到空气通道的另一端并通过飞行器体的后侧的外壁。发动机安装在空气通道中。排气管安装在发动机上，沿着空气通道具有预定的后长度。发动机冷却系统安装在无人机（无人机）或R / C（遥控）模型飞行器上。

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