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公开(公告)号：KR101847201B1
公开(公告)日：2018-04-09
申请号：KR1020160169755
申请日：2016-12-13
Applicant: 한국항공우주연구원
CPC classification number: F02K9/62 , F02K9/97 , F05D2230/237 , F05D2230/90
Abstract: 본발명의일 실시예는, 내부라이너의원주방향을따라복수개의접선홀을가공하고, 연소실외부하우징의내주면및 접선홀이가공된내부라이너의외주면중 하나이상에브레이징용가재(brazing filler)를도포하는제1 단계와, 외부하우징과내부라이너를서로조립하는제2 단계와, 접선홀을갖는내부라이너의내주면을덮는브레이징백을준비하고, 브레이징백의양단부와외부하우징의양단부를결합하는제3 단계와, 외부하우징, 내부라이너및 브레이징백의조립체를브레이징컨테이너에고정장착한후, 브레이징컨테이너를브레이징로(brazing furnace)에장입하여브레이징공정을실시하는제4 단계와, 외부하우징과내부라이너로부터브레이징백을제거하는제5단계를포함하는접선홀이있는이중벽연소실제조방법을개시한다.
Abstract translation: 本发明的一个实施例中，机加工在所述内衬套的圆周方向的多个切向孔，并施加钎料（钎料），以加工的内衬层，该内周面与所述燃烧室外部壳体的切向孔的外周面中的至少一个 的第一步骤中，在外壳和内衬，并覆盖具有切向孔钎焊baekeul制备的内衬层的内周面的第三工序组装在一起的第二步骤，和键合到铜焊的两端部后端部和外壳 ，外壳体，然后固定地安装到内衬层与钎焊包组件钎焊容器，和装载的（钎焊炉）的钎容器钎焊来进行钎焊工艺，以从外壳和内衬除去钎baekeul的第四步骤 第五步是形成切向孔。
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公开(公告)号：KR1020110057997A
公开(公告)日：2011-06-01
申请号：KR1020090114645
申请日：2009-11-25
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A combustion gas treatment device for a burn-in test of a gas generator is provided to enable convenient connection and separation between a gas generator and a noise reducing device by employing a connector including a bellows. CONSTITUTION: A combustion gas treatment device for a burn-in test of a gas generator comprises a connector(210) and a liquid nitrogen feeder(220). The connector is installed between a gas generator and a noise reducing device to block the inflow of external gas. The liquid nitrogen feeder supplies liquid nitrogen and water to the inside of the connector. The liquid nitrogen feeder comprises a liquid nitrogen supply flange(223) which is installed on an end of the connector and a liquid nitrogen injection hole(221) which is formed on the liquid nitrogen supply flange as being connected to the inside of the connector.
Abstract translation: 目的：提供一种用于气体发生器老化试验的燃烧气体处理装置，通过采用包括波纹管的连接器，能够方便地在气体发生器和降噪装置之间进行连接和分离。 构成：用于气体发生器的老化试验的燃烧气体处理装置包括连接器（210）和液氮进料器（220）。 连接器安装在气体发生器和降噪装置之间，以阻止外部气体的流入。 液氮供给器将液氮和水供应到连接器的内部。 液氮给料器包括安装在连接器端部上的液氮供应凸缘（223）和形成在液氮供应凸缘上的连接到连接器内部的液氮注入孔（221）。
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公开(公告)号：KR1020110037780A
公开(公告)日：2011-04-13
申请号：KR1020090095346
申请日：2009-10-07
Applicant: 한국항공우주연구원
CPC classification number: F02K9/97 , B23P15/008 , F02K9/60 , F02K99/00
Abstract: PURPOSE: Device and method for manufacturing the outer cover of a combustor nozzle of a liquid rocket engine are provided to remove the need for a separate heating unit since a conical outer cover is heated using a rotary support and a gas torch. CONSTITUTION: A device for manufacturing the outer cover of a combustor nozzle of a liquid rocket engine comprises a lower tool(100) and an upper tool. The lower tool comprises lower tool mold(110) and a tool support(120). The lower tool mold has a shape, which matches with the inner shape of the outer cover of a nozzle. The tool support is coupled to the lower part of the lower tool mold and supports the lower tool mold. The upper tool comprises a upper tool mold, which has a shape matching with the outer shape of the outer cover of the nozzle, and a fixed plate, which is coupled to the upper end of the upper tool mold.
Abstract translation: 目的：提供用于制造液体火箭发动机的燃烧器喷嘴的外盖的装置和方法，以消除对单独的加热单元的需要，因为锥形外盖使用旋转支撑件和气体焰炬加热。 构成：用于制造液体火箭发动机的燃烧器喷嘴的外盖的装置包括下部工具（100）和上部工具。 下部工具包括下部工具模具（110）和工具支撑件（120）。 下模具具有与喷嘴的外盖的内部形状相匹配的形状。 工具支撑件联接到下工具模具的下部并支撑下模具。 上部工具包括具有与喷嘴的外盖的外形匹配的形状的上部工具模具和联接到上部模具的上端的固定板。
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公开(公告)号：KR101014787B1
公开(公告)日：2011-02-14
申请号：KR1020080083440
申请日：2008-08-26
Applicant: 한국항공우주연구원
Abstract: 본 발명은 액체로켓의 연소기 헤드에 관한 것으로서, 상부는 돔형으로 형성되고 그 내부에는 인젝터를 일정한 형태로 위치시키는 인젝터 페이스가 형성되어 있으며 그 중앙 상부에는 산화제 공급관이 연결된 헤드와, 상기 헤드의 플랜지부와 연소기를 김발구조물에 장착할 수 있도록 하는 조립링체 사이에 설치된 김발지지대를 포함하는 액체로켓 연소기에 있어서, 상기 산화제 공급관이 연결되는 연소기 헤드의 상면과 조립링체 사이에 헤드의 수직변형을 감소시키는 김발보강대가 설치된 것을 특징으로 하여, 연소기가 고압에서 작동 시 헤드의 변형을 감소시킬 수 있다.
액체로켓, 연소기, 헤드, 돔, 인젝터 페이스, 김발지지대, 수직보강재-
公开(公告)号：KR1020100024742A
公开(公告)日：2010-03-08
申请号：KR1020080083440
申请日：2008-08-26
Applicant: 한국항공우주연구원
Abstract: PURPOSE: A combustor head of a liquid propellant rocket is provided to facilitate the manufacture of a combustor by detachably installing a vertical reinforcing member inside a head. CONSTITUTION: A combustor head of a liquid propellant rocket comprises a head(110), a support(160), and a reinforcing frame(170). The head is domed. An injector and an injector pace face(112) are formed inside the head. An oxidizing agent supply pipe(140) is connected to the upper center of the head. The support is installed between a flange part(110a) of the head and an assembly ring body(150) for mounting a combustor. The reinforcing frame reduces the vertical deformation of the head between the upper side of the combustor head and the assembly ring body.
Abstract translation: 目的：提供液体推进剂火箭的燃烧器头部，以通过将头部内的垂直加强件可拆卸地安装来促进燃烧器的制造。 构成：液体推进剂火箭的燃烧器头包括头部（110），支撑件（160）和加强框架（170）。 头是圆顶。 头部内部形成有喷射器和喷射器起搏面（112）。 氧化剂供给管（140）连接到头部的上部中心。 支撑件安装在头部的凸缘部分（110a）和用于安装燃烧器的组装环体（150）之间。 加强框架减小了头部在燃烧器头部的上侧和组装环体之间的垂直变形。
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Patent Agency Ranking
公开(公告)号：KR1020090073334A
公开(公告)日：2009-07-03
申请号：KR1020070141251
申请日：2007-12-31
Applicant: 한국항공우주연구원
CPC classification number: F02K9/64 , F02K9/96 , F05D2260/81
Abstract: A bidirectional regenerative cooling combustion chamber for a liquid rocket engine is provided to reduce the outermost diameter of an engine by positioning a fuel inlet pipe between the one end and head of a nozzle so that fuel bidirectionally flows in case two or more combustor are assembled. A bidirectional regenerative cooling combustion chamber(200) for a liquid rocket engine comprises: a fuel inlet pipe(110) being formed so that fuel flows into one side; a fuel ring which uniformly supplies the fuel flowed through the fuel inlet pipe to a cooling channel; an orifice inducing the supplied fuel to a head direction cooling channel or a nozzle direction cooling channel; and a return cooling channel inducing the fuel, supplied to the nozzle direction cooling channel, to the head direction in the end of the nozzle.
Abstract translation: 提供了一种用于液体火箭发动机的双向再生冷却燃烧室，用于通过将燃料入口管定位在喷嘴的一端和头部之间来减小发动机的最外径，使得在组装两个或多个燃烧器的情况下燃料双向流动。 用于液体火箭发动机的双向再生冷却燃烧室（200）包括：燃料进入管（110），其形成为使得燃料流入一侧; 燃料环，其将通过燃料入口管流动的燃料均匀地供应到冷却通道; 将供应的燃料引导到头部方向冷却通道或喷嘴方向冷却通道的孔口; 以及向喷嘴方向冷却通道供给燃料的返回冷却通道在喷嘴端部的头部方向。
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公开(公告)号：KR102243671B1
公开(公告)日：2021-04-22
申请号：KR1020190159914
申请日：2019-12-04
Applicant: 한국항공우주연구원
Abstract: 본발명의한 실시예에따른패터네이터는제1 및제2 유체를방사상으로분무하는분사부, 상기분사부의하측에위치하고, 반구셀형상을가지며, 그표면에복수개의샘플링포트가형성된컬렉터, 상기복수개의샘플링포트에각각연결되는복수개의유도관, 상기복수개의유도관에각각연결된복수개의주입부, 상기복수개의주입부가고정되고, 상하방향으로이동가능한주입부고정판, 상기주입부고정판의하측에위치하고상기복수개의주입부각각에대응하는복수개의실린더, 및상기복수개의실린더의하측에상기복수개의실린더각각과접촉할수 있게배치된복수개의로드셀을포함하며, 상기분사부는상기컬렉터를위에서내려다볼때, 상기컬렉터의중심에위치하고, 상기복수개의샘플링포트각각은상기분사부의분무구를향하여방사상으로배치된것을특징으로한다.
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公开(公告)号：KR101876755B1
公开(公告)日：2018-07-10
申请号：KR1020160151900
申请日：2016-11-15
Applicant: 한국항공우주연구원
Abstract: 본발명은액체로켓연소기의연소실과노즐목부에열 차폐코팅이된 경우에도연소기및 엔진의기밀을유지시킬수 있는액체로켓엔진및 연소기용기밀시험장치를제공하는것이그 기술적과제이다. 이를위해, 본발명의액체로켓엔진및 연소기용기밀시험장치는, 연소실과노즐목부를포함하여열 차폐코팅이된 제1 부분과상기노즐목부의아래로열 차폐코팅이되지않은제2 부분을포함하는연소기및 이를장착한액체로켓엔진에사용되는액체로켓엔진및 연소기용기밀시험장치로, 상기제1 부분의상기노즐목부에걸쳐져구비되는상부플레이트; 상기제2 부분에구비되는하부플레이트; 상기하부플레이트의하중을상기상부플레이트에지지시키기위한하중지지부; 및상기하부플레이트의외측면의일 부분을감싸며상기하부플레이트와상기제2 부분의내측면사이를밀봉시키는환 형상의밀봉부재를포함한다.
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公开(公告)号：KR101122026B1
公开(公告)日：2012-03-09
申请号：KR1020090114645
申请日：2009-11-25
Applicant: 한국항공우주연구원
Abstract: 본발명은가스발생기연소시험을위한후류가스처리장치에관한것이다. 가스발생기연소시험을위한후류가스처리장치는연결치구, 액체질소공급장치를포함한다. 연결치구는가스발생기와소음저감장치사이에설치되어외부기체유입을차단한다. 액체질소공급장치는상기연결치구의내부로액체질소를공급한다. 연결치구를설치함으로써가스발생기연소시험시 소음저감장치내부로흡입되는공기를막아공기중의산소가소음저감장치내부에서미연의후류가스와혼합되어폭발이일어나는위험을방지하고, 액체질소공급장치를통해연결치구의내부로비활성인액체질소및 물을공급함으로써비활성인액체질소가기체질소로기화, 혼합되어후류가스의재점화가능성을줄이고액체질소와물이소음저감장치내부온도를낮추어가스발생기연소시험의안정성을증가시켜준다.
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公开(公告)号：KR1020100031909A
公开(公告)日：2010-03-25
申请号：KR1020080090779
申请日：2008-09-16
Applicant: 한국항공우주연구원
CPC classification number: F02K9/52 , F05D2230/60 , F23L2900/07004 , Y02E20/344
Abstract: PURPOSE: An injector head of a liquid propellant rocket combustor is provided to prevent oxidizer and fuel from being leaked and mixed inside the injector head by separately including an oxidizer injector and a fuel injection nozzle. CONSTITUTION: An injector head of a liquid propellant rocket combustor comprises an injection plate(110), a partition plate(120), a fuel injection nozzle(130), and an oxidizer injector(140). The injection plate constitutes the upper side of the combustion chamber and has through-holes(111). The partition plate is apart from the upper part of the injection plate to form a space between the partition plate and the injection plate. The fuel injection nozzle injects fuel supplied from a fuel supply manifold to the combustion chamber. The upper side of the fuel injection nozzle is coupled with the lower side of the partition plate and the lower side of the fuel injection nozzle is inserted into the through-hole. The oxidizer injector injects oxidizer supplied from an oxidizer supply manifold.
Abstract translation: 目的：提供液体推进剂火箭燃烧器的喷射头，以防止氧化剂和燃料通过分别包括氧化剂喷射器和燃料喷射喷嘴而在喷射器头部内泄漏和混合。 构成：液体推进剂火箭燃烧器的喷射头包括注射板（110），分隔板（120），燃料喷射喷嘴（130）和氧化剂喷射器（140）。 注射板构成燃烧室的上侧，并具有通孔（111）。 分隔板与注射板的上部分离，以在分隔板和注射板之间形成空间。 燃料喷射喷嘴将从燃料供应歧管供应的燃料喷射到燃烧室。 燃料喷射喷嘴的上侧与隔板的下侧连接，并且燃料喷嘴的下侧插入通孔中。 氧化剂注射器注入从氧化剂供应歧管提供的氧化剂。
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