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71. 发明公开

KR1020130141814A 재생냉각 연소실용 강도와 기밀시험 장치 无效
标题翻译：用于再生冷却燃烧室强度和泄漏试验的装置
公开(公告)号：KR1020130141814A
公开(公告)日：2013-12-27
申请号：KR1020120064804
申请日：2012-06-18
申请人： 한국항공우주연구원
发明人： 안규복 , 유철성 , 허성찬 , 김종규 , 최환석
IPC分类号： F02K9/96 , F02K9/64
CPC分类号： F02K9/96 , F02K9/64 , F05D2260/12 , F05D2260/81 , F05D2260/83
摘要： The present invention relates to an apparatus for testing strength and airtightness for a regenerative cooling combustion chamber, which is installed inside a combustion chamber by being opposite to a film cooling hole of the combustion chamber, and comprises a mounting ring where an accommodating groove is formed to communicate with the film cooling hole; a first elastic unit which is inserted into the accommodating groove by being opposite to the film cooling hole; and a second elastic unit which is inserted into the accommodating groove, whose outer circumference is in contact with the inner circumference of the first elastic unit, and whose left and right circumferences are separated from the accommodating groove. The apparatus for testing strength and airtightness for a regenerative cooling combustion chamber can facilitate a test and prevent safety accidents of a testing person by supplying pressure at a higher strength than the regenerative cooling combustion chamber formed with the inner skin and the outer skin and at a higher pressure than an airtightness test and by sealing the film cooling hole during the airtightness test.
摘要翻译：本发明涉及一种通过与燃烧室的薄膜冷却孔相对的方式安装在燃烧室内的再生式冷却燃烧室的强度和气密性的测试装置，包括形成容纳槽的安装环与薄膜冷却孔通讯; 第一弹性单元，其通过与薄膜冷却孔相对插入到容纳槽中; 以及第二弹性单元，其插入到所述容纳槽中，所述第二弹性单元的外周与所述第一弹性单元的内周接触，并且其左右周与所述容纳槽分离。用于再生冷却燃烧室的强度和气密性的测试装置可以通过以比内皮和外皮形成的再生式冷却燃烧室更高的强度提供压力来促进测试人员的安全事故，并且以比气密性试验更高的压力和在气密性试验期间密封薄膜冷却孔。

72. 发明授权

KR101286330B1 가스 터빈 有权
公开(公告)号：KR101286330B1
公开(公告)日：2013-07-15
申请号：KR1020117008077
申请日：2010-03-16
申请人： 미츠비시 쥬고교 가부시키가이샤
发明人： 이이다고이찌로오
IPC分类号： F01D1/04 , F01D9/04 , F01D11/04 , F02C7/18
CPC分类号： F01D5/141 , F01D5/142 , F01D9/04 , F01D9/041 , F02C7/18 , F05D2220/321 , F05D2220/3213 , F05D2260/81 , Y02T50/673
摘要： 정익과 동익 사이의 축 방향 간극 및 날개 단부면의 냉각을 효과적으로 행할 수 있는 가스 터빈을 제공한다. 제2단 정익과 제3단 정익의 날개부(17)의 매수차가 0으로 된 가스 터빈에 있어서, 제2단 정익과 제3단 정익의 둘레 방향에 있어서의 상대 위치는, 클로킹에 의해, 제3단 정익의 정익부(17)의 허브측으로부터의 스팬 방향의 길이의 0％ 이상 15％ 이하의 범위에서, 제2단 정익의 정익부에 의해 형성된 후류가, 제3단 정익의 정익부(17)의 전방 모서리로 유도되도록 결정되어 있다.

73. 发明授权

KR101846625B1 냉각수 상태 진단 시스템 및 방법 有权
公开(公告)号：KR101846625B1
公开(公告)日：2018-04-09
申请号：KR1020150147674
申请日：2015-10-23
申请人： 현대자동차주식회사
发明人： 이동훈
IPC分类号： B60L11/18 , H01M8/04
CPC分类号： H01M8/04425 , F04B51/00 , F04D15/0066 , F04D15/0088 , F04D15/0236 , F05D2260/80 , F05D2260/81 , F05D2260/821 , F05D2270/309 , H01M8/04029 , H01M8/04358 , H01M8/04373 , H01M8/04417 , H01M8/04664
摘要： 냉각수펌프의속도지령값과상기냉각수펌프의실제속도측정값의차에따라상기냉각수펌프에전력을제공하는인버터의출력전류지령값을생성하는속도제어기를포함하는냉각수펌프제어시스템에적용되는냉각수상태진단시스템이개시된다. 상기냉각수상태진단시스템은, 상기출력전류지령값에따른상기냉각수펌프의속도를예측한속도추정값을생성하는펌프속도예측모델부; 및상기속도추정값과상기냉각수펌프의실제속도측정값을상호비교하여냉각수의순환상태를진단하는펌프상태진단부를포함한다.

74. 发明公开

KR1020170066268A 적응형 엔진 모델 토크 배분 최적화 审中-实审
标题翻译：自适应引擎模型扭矩分配优化
公开(公告)号：KR1020170066268A
公开(公告)日：2017-06-14
申请号：KR1020160163562
申请日：2016-12-02
申请人： 제네럴 일렉트릭 컴퍼니
发明人： 폴자크 , 야르디비타릭
IPC分类号： F02C3/107 , F02C7/36 , F02K3/06 , F01D17/02
CPC分类号： F02C9/28 , B64D27/10 , B64D31/06 , F01D21/003 , F02C6/02 , F02C6/20 , F02C7/22 , F02C9/42 , F05D2220/323 , F05D2260/81 , F05D2270/052 , G05B17/02
摘要： 적응형엔진모델을사용하는멀티-엔진시스템에서엔진들사이에토크배분(toqure split)을결정하기위한시스템및 방법이제공된다. 일실시예에있어서, 토크배분을결정하는방법은, 제1 엔진(110)에대해측정된작동점에적어도부분적으로기초하여, 제1 엔진(110)을위한토크대 연료흐름을특정하는제1 모델(515)을생성하는단계; 및제2 엔진(120)에대해측정된작동점에적어도부분적으로기초하여, 제2 엔진(120)을위한토크대 연료흐름을특정하는제2 모델(525)을생성하는단계를포함할수 있다. 상기방법은상기제1 모델(515) 및제2 모델(525)에적어도부분적으로기초하여, 상기제1 엔진(110) 및제2 엔진(120)에대한연료흐름을감소시키는, 상기제1 엔진(110) 및제2 엔진(120)을위한토크배분을결정하는단계; 및상기토크배분에적어도부분적으로기초하여, 상기제1 엔진(110) 및제2 엔진(120)의토크출력을제어하는단계를추가로포함할수 있다.
摘要翻译：提供了一种系统和方法，用于使用自适应引擎模型来确定多引擎系统中引擎之间的转矩分配。在一个实施例中，用于确定转矩分配的方法至少部分地基于至少部分基于针对第一发动机110测量的工作点，第一发动机110的第一转矩110，生成模型515; 并且至少部分地基于第二发动机120的测量的操作点生成第二模型525，该第二模型525指定第二发动机120的扭矩对燃料流量。该方法还包括至少部分地基于第一模型515和第二模型525来减少流向第一发动机110和第二发动机120的燃料流量，并且第二发动机120的扭矩分配; 并且至少部分地基于扭矩分配来控制第一发动机（110）和第二发动机（120）的扭矩输出。

75. 发明公开

KR1020090073334A 액체로켓엔진용 양방향 재생냉각 연소실 및 이의 모사시험장치 失效
标题翻译：液压推进式发动机双向再生冷却燃烧室
公开(公告)号：KR1020090073334A
公开(公告)日：2009-07-03
申请号：KR1020070141251
申请日：2007-12-31
申请人： 한국항공우주연구원
发明人： 이광진 , 김종규 , 김성구 , 한영민 , 최환석
IPC分类号： F02K9/64 , F02K9/62 , F02K9/60
CPC分类号： F02K9/64 , F02K9/96 , F05D2260/81
摘要： 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.
摘要翻译：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。

76. 发明申请

WO2018215566A1 ROTOR BLADE MANUFACTURING AND TESTING METHOD 审中-公开
公开(公告)号：WO2018215566A1
公开(公告)日：2018-11-29
申请号：PCT/EP2018/063567
申请日：2018-05-23
申请人： SIEMENS AKTIENGESELLSCHAFT
发明人： OSBORNE, Mark , PAN, Wenke
IPC分类号： F01D25/28 , G01N3/00
CPC分类号： F01D25/285 , F05D2260/80 , F05D2260/81 , F05D2260/83 , G01M1/00 , G01N3/00 , G01N3/08 , G01N3/32 , G01N2203/0298
摘要： A method of manufacturing a rotor blade (100) for a turbo machine, in which the rotor blade design has a root portion (106), and an aerofoil portion (104) which extends from the root portion (106). The method comprises the steps of determining a desired physical strength of the root portion (106) of the rotor blade (100), and producing a test piece (110) by an additive manufacturing technique. The test piece (110) comprises a root portion (112) which has the same design as the root portion (106) of the rotor blade (100), and a tool body (116) which extends from the root portion (112). The method further comprises determining a physical strength of the test piece root portion (112) by fixing the root portion (112) in a receiving part (114), and exerting a tensile force on the tool body (116), then comparing the determined physical strength of the root portion (112) to the desired physical strength of the root portion (106) of the rotor blade design (100) to determine if the root portion (112) has the desired physical strength allowing to start the manufacturing process..

77. 发明申请

WO2018132156A1 SYSTEM AND METHOD FOR MONITORING A STEAM TURBINE AND PRODUCING ADAPTED INSPECTION INTERVALS 审中-公开
公开(公告)号：WO2018132156A1
公开(公告)日：2018-07-19
申请号：PCT/US2017/059861
申请日：2017-11-03
申请人： GENERAL ELECTRIC COMPANY
发明人： VENEDIKIS, Leonidas , LEIDICH, Frank
IPC分类号： F01D25/00 , F01D21/14 , F01K13/02 , G01N17/00 , G01N33/18 , G05B23/02
CPC分类号： G06F17/5009 , F01D17/08 , F01D21/003 , F01D21/14 , F01D25/007 , F01K13/003 , F01K13/02 , F05D2260/80 , F05D2260/81 , F05D2270/11 , F05D2270/30 , F05D2270/71 , F05D2270/80 , G05B23/0283
摘要： A system and method for monitoring the operating conditions of a steam turbine and developing an adaptive inspection interval (200) includes access to a digital data storage archive (210) containing information relating to use and operation of comparable steam turbines and plant/service events, one or more turbine operational condition sensors (260) for monitoring steam quality in real time during operation of the steam turbine. A processor (220) calculates a steam quality value (271) based upon cation conductivity of the steam (40) used to operate the steam turbine as measured by the sensors (260). The processor uses the calculated steam quality information (271) either alone or together with other acquired operational and parametric data to determine an adapted inspection interval for the steam turbine (405). The processor (220) produces an output which includes the determined adapted inspection interval and may additionally include updated maintenance and repair schedules (407).

78. 发明申请

WO2017221923A1 ガスタービンのタービン出口温度予測方法及び装置审中-公开
标题翻译：燃气轮机的涡轮出口温度预测方法和装置
公开(公告)号：WO2017221923A1
公开(公告)日：2017-12-28
申请号：PCT/JP2017/022665
申请日：2017-06-20
申请人：株式会社IHI
发明人：シュミット　ニコラ , 鹿庭　政人 , 河野　幸弘 , 袖子田　志保
IPC分类号： F02C7/00 , F01D25/00 , F02C9/00
CPC分类号： F01D25/002 , F02C7/30 , F02C9/00 , F02C9/26 , F05D2260/81 , F05D2260/821 , F05D2270/11 , F05D2270/303 , F05D2270/304
摘要：ガスタービンの過去の使用実績に基づいて将来の使用時におけるタービン出口温度を予測する方法であって、将来の使用時に予定される環境・運用条件のパラメータと将来の使用時に予定されるファン回転数とを説明変数として用いて、目的変数としての将来の使用時におけるタービン出口温度をタービン出口温度モデルによって予測し、かつ、学習トリガ条件が成立する度に前記説明変数に対する係数を学習によって同定する。係数の学習においては、前記ガスタービンの過去の使用時における前記パラメータ、前記ファン回転数及び前記タービン出口温度を用いて行った、前記タービン出口温度モデルの前記説明変数及び前記目的変数の回帰学習の結果に基づいて、前記説明変数に対する係数が同定される。
摘要翻译：根据作为预测未来使用时的涡轮出口温度的方法的燃气轮机的过去使用记录，预测将来使用时的涡轮出口温度的方法，通过涡轮机出口温度模型和解释变量预测将来使用时的涡轮机出口温度作为目标变量通过学习。在系数的学习中，使用燃气轮机过去使用时的参数，风扇转速和涡轮机出口温度进行的涡轮机出口温度模型的解释变量和目标变量的回归学习根据结果确定解释变量的系数。

79. 发明申请

WO2016133578A2 ESTIMATING DYNAMIC THRUST OR SHAFT POWER OF AN ENGINE 审中-公开
标题翻译：估计发动机的动态扭矩或扭矩
公开(公告)号：WO2016133578A2
公开(公告)日：2016-08-25
申请号：PCT/US2015/063607
申请日：2015-12-03
申请人： SIKORSKY AIRCRAFT CORPORATION
发明人： HETTLER, Eric Nelson , PALMER, Carl
IPC分类号： G06F19/10
CPC分类号： G01L5/133 , F01D21/003 , F02C9/00 , F05D2220/323 , F05D2260/81 , F05D2270/71
摘要： A measuring system is provided that includes a turbine engine thrust estimator that computes "virtual measurements" of dynamic engine thrust and other parameters of interest from test cell data in a very short amount of time. The measuring system 'tunes' a user's engine model, in a numerical propulsion system simulation, by optimizing system biases and health parameters to match the sensor outputs of a set of steady state data points across the operating range. The tuned model is then utilized by the measuring system to create a constant gain extended Kalman filter that is added directly within a code of the numerical propulsion system simulation. Results, including thrust, from the numerical propulsion system simulation with Kalman filter are then presented as 'actual' corrected data.
摘要翻译：提供了一种测量系统，其包括涡轮发动机推力估计器，其在非常短的时间内从测试单元数据计算动态发动机推力和其它感兴趣参数的“虚拟测量”。在数值推进系统仿真中，测量系统通过优化系统偏差和健康参数来调整用户的发动机模型，以匹配整个工作范围内的一组稳态数据点的传感器输出。调谐模型然后由测量系统利用，以创建直接在数值推进系统仿真的代码内添加的恒定增益扩展卡尔曼滤波器。结果，包括推力，从卡尔曼滤波器的数值推进系统模拟，然后呈现为“实际”的校正数据。

80. 发明申请

WO2015108858A1 SYSTEMS AND METHODS FOR THERMAL LOCATION OF COOLING HOLES 审中-公开
标题翻译：冷却孔的热定位系统和方法
公开(公告)号：WO2015108858A1
公开(公告)日：2015-07-23
申请号：PCT/US2015/011176
申请日：2015-01-13
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： RAULERSON, David A. , SMITH, Kevin D. , OUYANG, Zhong , BRASCHE, Lisa J. , BRINDLEY, William J. , POTTER, David N.
IPC分类号： F04D31/00
CPC分类号： B23P6/002 , B23P2700/06 , F01D5/005 , F01D5/186 , F01D5/288 , F01D9/02 , F01D21/003 , F01D25/12 , F05D2220/32 , F05D2230/13 , F05D2230/80 , F05D2260/80 , F05D2260/81 , F05D2300/611 , G01N21/952 , G01N21/95692 , G01N25/72 , G06T7/73 , G06T2207/10048 , G06T2207/30164
摘要： Systems and methods are disclosed herein for repairing components. A material layer may be deposited on a surface of a component. The material layer may cover a cooling hole. A pulsed heat source may heat the component and the material layer. An infrared camera may take a series of images of the component. A location of the cooling hole may be identified based on thermal properties of the component. A removal tool may remove a portion of the material layer in order to expose the cooling hole.
摘要翻译：本文公开了用于修复部件的系统和方法。材料层可以沉积在部件的表面上。材料层可以覆盖冷却孔。脉冲热源可以加热组件和材料层。红外摄像机可能会拍摄该组件的一系列图像。可以基于部件的热性质来识别冷却孔的位置。去除工具可以去除材料层的一部分以暴露冷却孔。

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