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公开(公告)号：KR101206287B1
公开(公告)日：2012-11-29
申请号：KR1020110080842
申请日：2011-08-12
Applicant: 국방과학연구소
Abstract: PURPOSE: A cooling device for a micro turbine and the micro turbine with the same is provided to minimize the decrease of the performance of a gas turbine as components are cooled without additional devices. CONSTITUTION: A cooling device for a micro turbine comprises a supply valve(21), a cooling pipe(150), and an ejection port(151). The supply valve supplies the air with pre-set temperature and pressure to a combustor(20) from a compressor(10). The cooling pipe branches from one end of the supply valve. One or more ejection ports are branch from the cooling pipe, and closely placed to the predetermined portion of a rotary shaft. The ejection port cools the portion adjacent to the rotary shaft by discharging the air.
Abstract translation: 目的：提供一种用于微型涡轮机的冷却装置和具有该冷却装置的微型涡轮机，以使组件在没有附加装置的情况下冷却时，降低燃气轮机的性能。 构成：微型涡轮机的冷却装置包括供给阀（21），冷却管（150）和排出口（151）。 供应阀向压缩机（10）的燃烧器（20）供应预定的温度和压力的空气。 冷却管从供给阀的一端分支。 一个或多个喷射口从冷却管分支，并且紧密地放置在旋转轴的预定部分。 喷出口通过排出空气来冷却与旋转轴相邻的部分。
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公开(公告)号：KR101116031B1
公开(公告)日：2012-02-22
申请号：KR1020100011200
申请日：2010-02-05
Applicant: 국방과학연구소
Abstract: 본 발명은 흡입덕트로 흡입된 공기를 압축시키는 압축기와, 압축 공기를 이용하여 연료를 연소시키는 연소기와, 및 상기 연소기에서 배출된 연소가스를 이용하여 상기 압축기에 동력을 제공하는 터빈, 및 상기 연소기의 연소가스가 배출되는 배기덕트를 포함하는 터보제트엔진에 있어서, 상기 흡입덕트와 배기덕트에 회전 가능하게 연결되며 상기 압축기와 터빈을 연결하는 샤프트와, 상기 흡입덕트의 내부에 장착되며 상기 샤프트의 전단을 회전 가능하게 지지하는 전방 베어링과, 상기 흡입덕트에 구비되며 상기 전방 베어링에 윤활용 연료를 공급하기 위한 제1전방유로, 및 상기 압축기 내부의 공기를 추출하여 상기 전방 베어링에 공급할 수 있도록 상기 흡입덕트와 압축기에 구비되는 제2전방유로를 포함하는 것을 특징으로 하는 터보제트엔진을 개시한다.
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公开(公告)号：KR1020130092277A
公开(公告)日：2013-08-20
申请号：KR1020120013914
申请日：2012-02-10
Applicant: 국방과학연구소
Abstract: PURPOSE: A rotor and a gas turbine thereof are provided to facilitate a rotor assembly, part management, and implement of an assembly procedure by integrating a compressor runner, a turbine runner, and a rotary shaft as an integral type. CONSTITUTION: A rotor and a gas turbine thereof includes a compressor runner (120), a turbine runner (130), and a rotary shaft (120). The rotary shaft has the compressor runner and the turbine runner which are arranged on at least one end. The compressor runner, the rotary shaft, the turbine runner, and the rotary shaft are integrally formed without any seam.
Abstract translation: 目的：提供一种转子及其燃气轮机，以便通过将压缩机转轮，涡轮机转轮和旋转轴整合为一体来促进组装过程的转子组件，部件管理和实施。 构成：转子及其燃气轮机包括压缩机流道（120），涡轮转轮（130）和旋转轴（120）。 旋转轴具有设置在至少一端的压缩机转轮和涡轮转轮。 压缩机流道，旋转轴，涡轮机转轮和旋转轴一体形成，没有任何接缝。
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公开(公告)号：KR101141145B1
公开(公告)日：2012-05-02
申请号：KR1020110123475
申请日：2011-11-24
Applicant: 국방과학연구소
Abstract: PURPOSE: A two-way power generation type of a micro turbine-generator is provided to improve the electricity generation by increasing a magnetic field and magnetic flux density through the high-speed rotation of a permanent magnet of a turbine blade. CONSTITUTION: A two-way power generation type of a micro turbine-generator comprises a turbine blade(11), two permanent magnets(12), a pair of induction coils(13), a multi-layered housing(20), and a supporting unit(14). The two permanent magnets are connected to the top and bottom surfaces of the turbine blade. The induction coil generates induced current according to the rotation of the turbine blade. The turbine blade and the permanent magnet are installed inside the housing. The housing is formed with the induction coil into one body. The housing comprises first and second passages(21a,21b). The compressed air is provided to the turbine blade through the first passage. The second passage is formed along the lateral direction of the turbine blade. The air is exhausted from the turbine blade through the second passage. The supporting unit supports the turbine blade rotatably.
Abstract translation: 目的：提供一种双向发电型的微型涡轮发电机，用于通过涡轮叶片的永磁体的高速旋转增加磁场和磁通密度来改善发电。 构成：双向发电型的微型涡轮发电机包括涡轮叶片（11），两个永磁体（12），一对感应线圈（13），多层壳体（20）和 支撑单元（14）。 两个永磁体连接到涡轮叶片的顶表面和底表面。 感应线圈根据涡轮叶片的旋转产生感应电流。 涡轮叶片和永磁体安装在壳体内。 壳体由感应线圈形成一体。 壳体包括第一和第二通道（21a，21b）。 压缩空气通过第一通道被提供给涡轮叶片。 第二通道沿涡轮叶片的横向方向形成。 空气从涡轮叶片通过第二通道排出。 支撑单元可旋转地支撑涡轮叶片。
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公开(公告)号：KR101122062B1
公开(公告)日：2012-03-14
申请号：KR1020100041654
申请日：2010-05-04
Applicant: 국방과학연구소
Abstract: 본 발명은 가스터빈용 회전연료노즐에 관한 것으로서, 더욱 상세하게는 회전연료노즐을 이루는 회전축의 반경면을 계단형으로 형성하고, 각 계단면에 연료 분사구인 오리피스를 형성하여 연소실로 연료를 분사할 수 있는 가스터빈용 회전연료노즐을 제공하는 것을 목적으로 한다.
상기 목적을 달성하기 위해, 연료 분사공이 형성된 폐쇄형 드럼구조를 갖는 회전축을 포함하는 가스터빈용 회전연료노즐로서, 상기 연료 분사공은 상기 회전축의 외측(外側)에 위치하는 연소실과 관통되도록 형성된 복수 개의 오리피스인 것을 특징으로 한다.-
Patent Agency Ranking
公开(公告)号：KR100781151B1
公开(公告)日：2007-11-30
申请号：KR1020010088289
申请日：2001-12-29
Applicant: 한화테크윈 주식회사 , 국방과학연구소
IPC: F01M11/02
Abstract: 본 발명은 가스 터빈 엔진에 있어, 윤활 오일을 냉각시키기 위한 냉각기를 외부에 별도로 설치할 필요없이 오일탱크 자체에서 오일의 냉각이 이루어질 수 있도록 하여, 무게를 감소시키고, 설치공간을 보다 유리하게 확보할 수 있도록 하기 위한 것으로, 본 발명은 윤활 오일이 저장되는 주 탱크부와, 상기 주 탱크부로 오일이 유입되는 유입관과, 상기 주 탱크부로부터 오일이 유출되는 유출관과, 상기 주 탱크부 내부를 지나도록 배설되는 적어도 하나 이상의 연료 흐름관을 포함하여 이루어진 것을 특징으로 하는 가스 터빈 엔진의 오일탱크 및 이를 구비한 가스 터빈 엔진의 윤활시스템에 관한 것이다.
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公开(公告)号：KR1020030059428A
公开(公告)日：2003-07-10
申请号：KR1020010088289
申请日：2001-12-29
Applicant: 한화테크윈 주식회사 , 국방과학연구소
IPC: F01M11/02
Abstract: PURPOSE: An oil tank and a lubricating system having the same are provided to reduce weight of the engine and prevents restriction of installation by eliminating the necessity of using an additional cooler. CONSTITUTION: A lubricating system comprises an oil tank(100) for storage of lubricating oil, and which is arranged to have a fuel flow pipe(120) penetrating through the interior of the oil tank; an oil pump(200) for supplying oil from the oil tank to mechanical components(510,520,530) of a gas turbine engine; an oil filter(300); and an oil circulation unit(400) for recovering the oil from the mechanical components and transferring the oil to the oil tank. The oil tank includes a main tank for storage of lubricating oil; an inlet pipe for receiving oil from the main tank; an outlet pipe for discharging oil from the main tank; and the fuel flow pipe penetrating through the interior of the main tank.
Abstract translation: 目的：提供一种油箱及其润滑系统，以减轻发动机的重量，并通过消除使用附加冷却器的必要性来防止安装的限制。 构成：润滑系统包括用于储存润滑油的油箱（100），并且其布置成具有穿过油箱内部的燃料流管（120）; 用于将油从油箱供给到燃气涡轮发动机的机械部件（510,520,530）的油泵（200） 油过滤器（300）; 以及用于从机械部件回收油并将油转移到油箱的油循环单元（400）。 油箱包括用于储存润滑油的主油箱; 用于从主罐接收油的入口管; 用于从主油箱排出油的出口管; 并且燃料流管穿过主罐的内部。
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公开(公告)号：KR101232055B1
公开(公告)日：2013-02-12
申请号：KR1020110080840
申请日：2011-08-12
Applicant: 국방과학연구소
Abstract: PURPOSE: A device for evaluating the performance of a recuperator for a micro turbine is provided to enable to evaluate properties and the performance of the recuperator according to changes in flow rate conditions of a compressor and turbine and inlet temperature conditions. CONSTITUTION: A device for evaluating the performance of a recuperator(140) for a micro turbine comprises a first air control unit(110), a second air control unit(120), a first diffuser(151), a second diffuser(152), and the recuperator. The first and second air control units supply air of constant temperature, constant temperature, and a flow rate. The first diffuser is connected to the first air control unit. The second diffuser is connected to the second air control unit. Both ends of the recuperator are respectively joined to one of the diffusers.
Abstract translation: 目的：提供一种用于评估微型涡轮机的换热器性能的装置，以便根据压缩机和涡轮机的流量条件以及入口温度条件的变化来评估换热器的性能和性能。 构造：用于评估微型涡轮机的换热器（140）的性能的装置包括第一空气控制单元（110），第二空气控制单元（120），第一扩散器（151），第二扩散器（152） ，和换热器。 第一和第二空气控制单元提供恒温，恒温和流量的空气。 第一扩散器连接到第一空气控制单元。 第二扩散器连接到第二空气控制单元。 分离器的两端分别连接到一个扩散器。
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公开(公告)号：KR1020110125717A
公开(公告)日：2011-11-22
申请号：KR1020100045222
申请日：2010-05-14
Applicant: 국방과학연구소
Abstract: PURPOSE: A diagonal flow type compressor is provided to reduce the outer circumference of a compressor comparing to a centrifugal compressor. CONSTITUTION: A diagonal flow type compressor comprises a diagonal flow type impeller(10) and multiple diffuser vanes(20). The diagonal flow type impeller has an inlet part and an outlet part facing to a diagonal radial direction. Multiple diffuser vanes are curve type. The outlet part of the diagonal flow type impeller and the inlet part of the diffuser vane have the same angle as to the diagonal flow type flow path shape. The axial type outlet of the diffuser vane has a tip-end part. The tip-end part is perpendicularly opened on the flow path.
Abstract translation: 目的：提供一种斜流式压缩机，以减少压缩机与离心压缩机相比的外圆周。 构成：对角流型压缩机包括对角流型叶轮（10）和多个扩压叶片（20）。 对角流型叶轮具有面向对角径向的入口部和出口部。 多个扩散器叶片是曲线类型。 对角流型叶轮的出口部分和扩散器叶片的入口部分具有与对流流动型流路形状相同的角度。 扩散器叶片的轴向出口具有尖端部分。 顶端部分在流动路径上垂直打开。
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公开(公告)号：KR1020110122262A
公开(公告)日：2011-11-10
申请号：KR1020100041654
申请日：2010-05-04
Applicant: 국방과학연구소
Abstract: PURPOSE: A rotating fuel nozzle for a gas turbine is provided to sequentially supply fuel by ignition, acceleration, and fixation steps through each orifice using a fuel injection structure formed in a step shape. CONSTITUTION: A rotating fuel nozzle for a gas turbine comprises a fuel injection hole(240), orifices(301,302,303), a combustion chamber(250), a slope(333), and a closed drum structure(350). The fuel injection hole is orifice. The combustion chamber is located outside a rotary shaft(200). The slope of the closed drum structure of the rotary shaft consists of steps. The orifice is formed on the surface of the slope. The closed drum structure forms walls(331,332). The wall blocks fuel from final orifice from flowing. The orifice is formed perpendicular to the rotary shaft. The orifices have a circular cross section and are arranged in parallel to each other.
Abstract translation: 目的：提供一种用于燃气轮机的旋转燃料喷嘴，以使用形成为台阶形状的燃料喷射结构，通过点火，加速和固定步骤顺序地供应燃料。 构成：用于燃气轮机的旋转燃料喷嘴包括燃料喷射孔（240），孔（301,302,303），燃烧室（250），斜坡（333）和封闭鼓结构（350）。 燃油喷射孔是孔口。 燃烧室位于旋转轴（200）的外侧。 旋转轴的闭合鼓结构的斜面由步骤组成。 孔口形成在斜面的表面上。 封闭的鼓结构形成壁（331,332）。 墙壁阻止来自最终孔口的燃料流动。 孔口垂直于旋转轴形成。 所述孔具有圆形横截面并彼此平行布置。
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