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1. 发明公开

KR1020130114862A 항공기용 공랭식 피스톤 엔진 냉각용 시스템 有权
标题翻译：空气冷却活塞式发动机冷却系统
公开(公告)号：KR1020130114862A
公开(公告)日：2013-10-21
申请号：KR1020120037233
申请日：2012-04-10
申请人： 한국항공우주산업 주식회사
发明人： 정인면 , 최원 , 최재승 , 이일우
IPC分类号： F01P1/02 , F01P11/00 , F01P5/02
CPC分类号： F01P1/04 , B64D13/08 , F01P5/02 , F01P2001/005 , F01P2050/20
摘要： PURPOSE: A cooling system of an air cooling piston engine for an aircraft is provided to minimize drag by inhaling cooling air, which is generated by the rotation of a propeller, through an inlet of a cowl which is located behind the propeller. CONSTITUTION: A cooling system of an air cooling piston engine for an aircraft includes a cowl, a baffle (40), and an engine cylinder (50). The cowl forms an outer shape of a cooling system, and is equipped with an inlet (10) on one side and with an outlet (20) on the other side. The baffle is formed inside the cooling system, and divides the cowl into the upper and the lower part. The engine cylinder is formed multiply on the middle part of the baffle. The inlet of the cowl is located behind the propeller of the aircraft, and inhales cooling air which is generated by the rotation of the propeller.
摘要翻译：目的：提供一种用于飞行器的空气冷却活塞发动机的冷却系统，以通过吸入由螺旋桨的旋转产生的冷却空气通过位于螺旋桨后面的整流罩的入口来最小化阻力。构成：用于飞行器的空气冷却活塞发动机的冷却系统包括整流罩，挡板（40）和发动机气缸（50）。整流罩形成冷却系统的外形，并且在一侧配备有入口（10）并且在另一侧上具有出口（20）。挡板形成在冷却系统的内部，并将整流罩分成上部和下部。发动机气缸形成在挡板的中间部分上。整流罩的入口位于飞机的螺旋桨后面，并吸入由螺旋桨旋转产生的冷却空气。

2. 发明公开

KR1020160051733A 내부 연소 엔진의 냉각 审中-实审
标题翻译：内燃机冷却
公开(公告)号：KR1020160051733A
公开(公告)日：2016-05-11
申请号：KR1020167003047
申请日：2014-06-03
申请人： 유에이브이 엔진스 엘티디.
发明人： 비둘프크리스토퍼존
IPC分类号： F01P3/18 , F28D1/053 , F28D1/02
CPC分类号： F01P3/18 , B64D33/10 , F01P2050/20 , F02B61/04 , F28D1/05366 , F28D2001/028
摘要： 프로펠러로-구동되는항공기를위한엔진조립체(10)가개시되고, 이조립체는엔진(11)과, 엔진(11)에의해구동되는구동샤프트(13)와, 그리고구동샤프트(13)를수용하기위한개구(24)를포함하는라디에이터(20)를포함하며, 개구(24)는라디에이터(20)가구동샤프트(13)를실질적으로원주방향으로둘러싸도록위치된다. 개구(24)는라디에이터(20)의내부에있는구멍또는라디에이터(20)내에형성된블라인드슬릿과같은, 다양한형태를가진다.

3. 发明授权

KR101538626B1 수분무식 과열 저감 장치 및 방법 有权
标题翻译：水喷雾式除臭器的装置及其方法
公开(公告)号：KR101538626B1
公开(公告)日：2015-07-23
申请号：KR1020140036860
申请日：2014-03-28
申请人： 두산중공업 주식회사
发明人： 권우철 , 정동관 , 이재달 , 김용성 , 임중현
IPC分类号： F01D25/12 , F01P3/00
CPC分类号： F01P9/02 , F01D25/12 , F01P3/12 , F01P2003/001 , F01P2050/20
摘要： 본발명의일 실시예에따른과열저감장치는, 과열증기가이동하며상기증기와분사된물이내부에서혼합작용을일으키는과열저감튜브; 및상기튜브내로물의유입을위하여상기과열저감튜브일측상부로부터하방으로수직으로삽입되는스프레이튜브;를포함하고, 상기과열저감튜브는스프레이튜브전방의증기속도가속화를위한벤투리부를포함하며, 상기스프레이튜브는상기과열저감튜브내에삽입된부분에상기과열저감튜브내부로물을분사하는분무수단을포함하고, 상기분무수단은다수의분무구를갖는적어도하나이상의다공성오리피스로이루어진것을특징으로한다.
摘要翻译：根据本发明的实施例的过热降温器包括：过热蒸汽移动并且蒸汽和喷射水在内部混合的过热加热管; 以及从过热管的一侧的顶部到底部垂直插入以允许水流入管中的喷射管。减温管包括：用于增加喷射管前面的蒸汽速度的文丘里单元。喷射管包括：在插入减温管中的部件上的喷射装置，用于将水喷射到过热管中。喷射装置包括：具有多个喷射孔的至少一个多孔孔。

4. 发明授权

KR101453329B1 키트형 헬리콥터의 냉각수 순환시스템 有权
标题翻译：套筒式直升机冷凝器循环系统
公开(公告)号：KR101453329B1
公开(公告)日：2014-10-22
申请号：KR1020140101106
申请日：2014-08-06
申请人： (주) 피트게러지 인터그레이션 , 경남과학기술대학교 산학협력단
发明人： 이치우 , 김종호
IPC分类号： B64D33/08 , F01P3/20
CPC分类号： F01P3/20 , B64D33/08 , F01P11/0209 , F01P11/14 , F01P2050/20
摘要： The present invention relates to a coolant circulation system for a kit-type helicopter, in which a coolant tank storing a coolant for cooling an engine is provided with an auxiliary tank for storing extra coolant which is not circulated in the engine, thereby easily filling the coolant when the amount of coolant in the coolant tank is not enough, and preventing an operator or worker from being burned on a hot cap; in which the coolant tank is directly connected to a radiator via a separate coolant line, thereby solving a problem in that the cooling efficiency is decreased by generation of bubbles when the coolant exceeds a boiling point under a condition where much output is used at a time at taking-off or landing of the helicopter; and in which the auxiliary tank is provided with the a hopper to easily perform the filling of the coolant and to prevent the coolant from flowing in an engine room.
摘要翻译：本发明涉及一种用于套件式直升机的冷却剂循环系统，其中存储用于冷却发动机的冷却剂的冷却剂罐设置有用于存储不在发动机中循环的额外冷却剂的辅助箱，从而容易地填充当冷却剂箱中的冷却剂量不足时，冷却剂，并且防止操作者或工人在热盖上燃烧; 其中冷却剂罐通过单独的冷却剂管线直接连接到散热器，从而解决了当在一次使用大量输出的条件下当冷却剂超过沸点时通过产生气泡来降低冷却效率的问题直升机起飞或着陆时; 并且其中辅助箱设置有料斗以容易地执行冷却剂的填充并且防止冷却剂在发动机室中流动。

5. 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。

6. 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.

7. 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。

8. 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。

9. 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。

10. 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。

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