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61. 发明公开

KR1020100080476A 압축기 스테이터 블레이드의 동조 방법 无效
标题翻译：与频率调节涡轮叶片相关的方法，系统和/或装置
公开(公告)号：KR1020100080476A
公开(公告)日：2010-07-08
申请号：KR1020090134497
申请日：2009-12-30
申请人： 제너럴 일렉트릭 캄파니
发明人： 드벤가다시다라자엠 , 쿠마르라빈드라
IPC分类号： F01D9/02 , F01D5/14 , F01D25/00
CPC分类号： F01D5/16 , F01D5/26 , F01D9/041 , Y10T29/49336 , F01D9/02 , F01D5/14 , F01D25/00
摘要： PURPOSE: A tuning method of a compressor stator blade is provided to change the natural frequency of an airfoil of a turbine blade without changing the shape of an air foil or the design of a root. CONSTITUTION: A tuning method of a compressor stator blade comprises following steps. The natural frequency of the compressor stator blade(155) is distinguished. The target natural frequency of the compressor stator blade is determined. Material is removed by the structure constituting target natural frequency from one among side surfaces of a base portion of the compressor stator blade.
摘要翻译：目的：提供压缩机定子叶片的调节方法，以改变涡轮叶片的翼型的固有频率，而不改变气翼的形状或根部的设计。构成：压缩机定子叶片的调谐方法包括以下步骤。压缩机定子叶片（155）的固有频率被区分开。确定压缩机定子叶片的目标固有频率。通过构成目标固有频率的结构从压缩机定子叶片的基部的侧表面之一移除材料。

62. 发明公开

KR1020100080451A 로터 블레이드 无效
标题翻译：涡轮叶片配置
公开(公告)号：KR1020100080451A
公开(公告)日：2010-07-08
申请号：KR1020090133235
申请日：2009-12-29
申请人： 제너럴 일렉트릭 캄파니
发明人： 보이어브래들리티
IPC分类号： F01D5/34 , F01D5/14 , F01D5/30
CPC分类号： F01D5/3007 , F05D2240/80
摘要： PURPOSE: A rotor blade is provided to enable efficient manufacture, assembly, or task by improving the design of roots of a turbine blade. CONSTITUTION: A rotor blade comprises a root and an airfoil(136). The airfoil is extended from the root in the radial direction. The root comprises one or more root alignment surfaces(178). The slope may have a non-radial direction orientation. A rotor blade(126) comprises two or more root alignment surfaces wherein one is placed on an input side of the rotor blade and the other is placed on the suction side of the rotor blade. A root alignment surface is able to be sloped.
摘要翻译：目的：提供转子叶片，以通过改进涡轮叶片根部的设计来实现高效的制造，组装或任务。构成：转子叶片包括根部和翼型件（136）。机翼从径向方向延伸。根部包括一个或多个根部对准表面（178）。坡度可以具有非径向定向。转子叶片（126）包括两个或多个根部对准表面，其中一个被放置在转子叶片的输入侧，另一个被放置在转子叶片的吸力侧。根对准表面能够倾斜。

63. 发明公开

KR1020100054804A 증기 터빈 스테이지 无效
标题翻译：蒸汽涡轮舞台
公开(公告)号：KR1020100054804A
公开(公告)日：2010-05-25
申请号：KR1020107003461
申请日：2007-07-27
申请人： 안살도 에너지아 에스.피.에이
发明人： 마끼오',마우로 , 세츠히,스테파노 , 마라바시,프란체스코
IPC分类号： F01D5/14 , F01D9/04
CPC分类号： F01D25/32 , F05D2220/31 , F05D2230/232 , F05D2250/324 , F05D2250/711 , F05D2260/95
摘要： A stage of a steam turbine, having a rotor (2) extending along a longitudinal axis (A), has a fixed stage (8) and a movable stage (9) arranged successively along a flow channel (4) for feeding steam in a direction (D) substantially parallel to the longitudinal axis (A); the fixed stage (8) has an inner ring (20) coaxial with the longitudinal axis (A), and a number of stator blades (22) arranged radially about the inner ring (20); each stator blade (22) is fixed to an annular top portion (27) of the inner ring (20), which has a top surface (30) facing the flow channel (4) and crosswise to the longitudinal axis (A); and the movable stage (9) has a number of rotor blades (15) arranged radially about the rotor (2) and fixed to the rotor (2).
摘要翻译：具有沿着纵向轴线（A）延伸的转子（2）的蒸汽涡轮机的级具有固定级（8）和可沿着流动通道（4）连续排列的可移动级（9），用于在方向（D）基本上平行于纵向轴线（A）; 所述固定平台（8）具有与所述纵向轴线（A）同轴的内圈（20）和围绕所述内圈（20）径向布置的多个定子叶片（22）。每个定子叶片（22）固定到内环（20）的环形顶部（27），其具有面向流动通道（4）并且横向于纵向轴线（A）的顶表面（30）。并且所述可动台（9）具有多个绕所述转子（2）径向配置并固定在所述转子（2）上的转子叶片（15）。

64. 发明授权

KR100875785B1 증기 터빈 회전 날개 有权
标题翻译： 증기터빈회전날개
公开(公告)号：KR100875785B1
公开(公告)日：2008-12-26
申请号：KR1020070099734
申请日：2007-10-04
申请人： 가부시키가이샤 히타치세이사쿠쇼
发明人： 아사이구니오 , 구도오다께시 , 나까무라다떼끼
IPC分类号： F01D5/14 , F01D25/00 , F01D5/12
CPC分类号： F01D5/16 , F01D5/225 , F05D2220/31
摘要： A subject of the present invention is to prevent the reduction of rigidity caused by the increased length of a steam turbine rotor blade (100) and the degradation of vibration characteristics. A steam turbine rotor blade (100) according to the present invention comprises a profile (1) and a cover (2) integrally formed on and at an end of the profile (1), the leading edge of the cover (2) formed on the profile and the trailing edge of a cover (2) formed on an adjacent preceding profile (1) being in contact and connected with each other by the torsional return force (7) produced during rotation, and wherein the cover (2) formed on the profile (1) is provided with a radially-formed stepped portion (20) at the trailing edge, the stepped portion (20) having a height larger than the thickness of the cover (2).
摘要翻译：本发明的课题在于防止由于汽轮机动叶片100的长度变长而引起的刚性的降低和振动特性的降低。根据本发明的蒸汽涡轮机转子叶片（100）包括型材（1）和在型材（1）的端部一体形成的盖（2），盖（2）的前缘形成在在相邻的在前型材（1）上形成的盖（2）的轮廓和后缘通过在旋转过程中产生的扭转回复力（7）彼此接触和连接，并且其中盖（2）形成在所述型材（1）在所述后缘处设置有径向形成的台阶部分（20），所述台阶部分（20）的高度大于所述盖子（2）的厚度。

65. 发明公开

KR1020080067980A 가스 터빈 엔진 코팅 방법 및 장치 无效
标题翻译：用于喷涂涡轮发动机的方法和装置
公开(公告)号：KR1020080067980A
公开(公告)日：2008-07-22
申请号：KR1020080004824
申请日：2008-01-16
申请人： 제너럴 일렉트릭 캄파니
发明人： 로우레이몬드그랜트 , 맥고번타라이스터 , 머피제인앤 , 스쿠그앤드류제이 , 스토웰윌리엄알 , 마크스폴토마스 , 데벨리스리사 , 클레어제임스에이치
IPC分类号： F01D5/28 , F01D25/00 , F01D5/14 , F02C7/00
CPC分类号： C23C4/02 , F01D5/288 , F05D2230/90 , Y02T50/673
摘要： A method and an apparatus for coating a gas turbine engine are provided to coat a soft layer-thermal protecting coating layer on a portion of a DVC thermal protecting coating layer by separating a spray device from a component by a distance of about 5.08 cm. A coating layer is formed on at least one of components. A spray device is used to perform a high DVC(Density Vertically Cracked) thermal protecting coating layer(100) on at least one portion of the coating layer. The spray device is positioned at a first distance from the component. A soft layer-thermal protecting coating layer(102) is stacked on the DVC thermal protecting coating layer by using the spray device distanced from the second distance. The spray device is separated from the component by a distance of about 5.08cm.
摘要翻译：提供了一种用于涂覆燃气涡轮发动机的方法和装置，以通过将喷射装置与组件分离约5.08cm的距离来涂覆DVC热保护涂层的一部分上的软层保护涂层。在至少一个部件上形成涂层。喷涂装置用于在涂层的至少一部分上执行高DVC（密度垂直破裂）热保护涂层（100）。喷雾装置定位在离部件的第一距离处。通过使用距离第二距离的喷雾装置，在DVC热保护涂层上层叠软层保护涂层（102）。喷雾装置与组件分开约5.08cm的距离。

66. 发明公开

KR1020080057183A 불노우즈형 밀봉 터빈 스테이지 无效
标题翻译： BULLNOSE密封涡轮舞台
公开(公告)号：KR1020080057183A
公开(公告)日：2008-06-24
申请号：KR1020070133440
申请日：2007-12-18
申请人： 제너럴 일렉트릭 캄파니
发明人： 클라싱케빈사무엘 , 리칭-팡 , 헌터스코트데이비드
IPC分类号： F01D9/02 , F01D5/14 , F01D11/08 , F01D5/20
CPC分类号： F01D5/145 , F01D5/082 , F01D5/143 , F01D9/041 , F01D11/001 , F05D2250/19 , Y02T50/673 , Y02T50/676
摘要： A bullnose type seal turbine stage is provided to raise the turbine efficiency by using a rotary sealing section interposed between a stator nozzle and a rotor blade. A bullnose type seal turbine stage comprises an annular stator nozzle(40) and blades(52). The annular stator nozzle includes vanes(42) mounted between an internal band(44) and an external band(46). The internal band has a mounting flange(48) extending radially inward from the internal band. The blades are mounted around a rotor disk(54), and are spaced apart from the mounting flange to form a front cavity(56) for guiding purge air. Each blade includes an internal platform(58) adjacent to the internal band in a rotary sealing section(60) disposed at the upper end of the front cavity in order to discharge the purge air. The internal band includes a stator bullnose at the rear edge thereof to reduce aerodynamic loss in cooperation with the rotary sealing section.
摘要翻译：提供了一种公牛型密封涡轮级，通过使用插入在定子喷嘴和转子叶片之间的旋转密封部来提高涡轮效率。长颈型密封涡轮级包括环形定子喷嘴（40）和叶片（52）。环形定子喷嘴包括安装在内部带（44）和外部带（46）之间的叶片（42）。内部带具有从内部带径向向内延伸的安装凸缘（48）。叶片围绕转子盘（54）安装并且与安装凸缘间隔开以形成用于引导吹扫空气的前腔（56）。每个叶片包括在设置在前腔的上端处的旋转密封部分（60）中与内部带相邻的内部平台（58），以便排出吹扫空气。内带在其后缘包括一个定子，以减少与旋转密封部分配合的气动损失。

67. 发明公开

KR1020080037586A 터빈 노즐용 에어포일 형상 无效
标题翻译：涡轮喷嘴气翼形状
公开(公告)号：KR1020080037586A
公开(公告)日：2008-04-30
申请号：KR1020070107992
申请日：2007-10-25
申请人： 제너럴 일렉트릭 캄파니
发明人： 휴만척크레이그 , 비엘렉크레이그 , 파랄린다 , 맥밀란글렌
IPC分类号： F01D9/02 , F01D5/14 , F01D25/00
CPC分类号： F01D9/041 , F05D2250/74
摘要： An airfoil profile for a turbine nozzle is provided to produce an airfoil which satisfies limited thermal and mechanical operating requirements for a specific stage. A nozzle for a gas turbine is provided with an airfoil(210) which has the shape of an envelope within ±0.160 inches in a vertical direction with respect to the surface position of the airfoil. The airfoil has a nominal profile substantially in accordance with Cartesian coordinate values of X, Y and Z. In this case, X and Y values are in inches and define airfoil profile sections at each distance Z, and the profile sections at the Z distances are joined smoothly to form a complete airfoil shape.
摘要翻译：提供了一种用于涡轮喷嘴的翼型轮廓以产生一种翼型，该翼型件满足特定阶段的有限的热和机械操作要求。燃气轮机的喷嘴设置有相对于翼型件的表面位置在垂直方向上具有在±0.160英寸内的外壳形状的翼型件（210）。翼型件具有基本上符合X，Y和Z的笛卡尔坐标值的标称轮廓。在这种情况下，X和Y值以英寸为单位，并且在每个距离Z处限定翼型轮廓部分，并且Z距离处的轮廓部分顺利结合，形成完整的翼型。

68. 发明授权

KR100814166B1 터빈 버킷 및 터빈 失效
标题翻译：第二级涡轮机空气弹簧
公开(公告)号：KR100814166B1
公开(公告)日：2008-03-14
申请号：KR1020030064025
申请日：2003-09-16
申请人： 제너럴 일렉트릭 캄파니
发明人： 휴먼척데이비드존 , 비엘레크크레이그알렌 , 브리팅햄로버트알란 , 발쿰제임스타이슨 , 존스앤드류이세
IPC分类号： F01D5/14
CPC分类号： F01D5/14 , F01D5/141 , F05D2220/3212 , F05D2240/301 , F05D2250/20 , F05D2250/70 , F05D2250/74 , Y10S416/02
摘要： 제 2 스테이지 버킷(22)은 실질적으로 표 1에 나타낸 X, Y 및 Z의 데카르트 좌표 값에 따른 에어포일 프로파일을 가지며, X 및 Y 값은 인치 단위이며, Z 값은 터빈 반경과 일치하는 버킷 중심선을 따라 무차원이며, Z 값에 에어포일의 높이를 곱하고 그 결과 값에 루트 반경을 더하여 터빈 축으로부터의 인치 단위 Z 거리로 변환 가능하다. 버킷에 대해 확대 또는 축소된 에어포일 섹션을 제공하도록 X 및 Y 거리는 동일한 상수 또는 숫자의 함수로서 확대 또는 축소될 수 있다. X, Y 및 Z에 의해 주어진 공칭 에어포일은 ±0.160인치(0.406㎝)의 인벨로프내에 위치한다.

69. 发明公开

KR1020080018184A 좌우대칭형 에어포일을 구비한 워터 터어빈 失效
标题翻译：具有双对称气翼的水轮机
公开(公告)号：KR1020080018184A
公开(公告)日：2008-02-27
申请号：KR1020077028627
申请日：2006-05-18
申请人： 로텍 홀딩스 리미티드
发明人： 톰슨데이비드스튜어트
IPC分类号： F03B13/26 , F03B3/12 , F03B17/06 , F01D5/14
CPC分类号： F01D5/141 , F03B3/121 , F03B13/264 , F03B17/061 , F05B2210/404 , F05B2240/13 , F05B2240/133 , F05B2240/301 , F05B2240/40 , F05D2210/44 , F05D2240/301 , F05D2240/40 , F05D2250/74 , Y02E10/223 , Y02E10/28 , Y02T50/673
摘要： Known underwater turbine units suffer from problems, e.g. an ability to operate in ebb and/or flow tides. Accordingly, the invention provides aerofoil (5), wherein the aerofoil (5) is symmetrical about a mid-chord line (A) thereof. The aerofoil (5) may be symmetrical about a chord (B) thereof. The underwater turbine unit (3) comprises at least one turbine (25) which comprises at least one blade (20) which comprises the aerofoil (5).
摘要翻译：已知的水下涡轮机单元遇到问题，例如在潮汐和/或潮汐中操作的能力。因此，本发明提供机翼（5），其中机翼（5）关于其中弦线（A）对称。机翼（5）可以关于其弦（B）对称。水下涡轮机组件（3）包括至少一个涡轮机（25），其包括至少一个包括机翼（5）的叶片（20）。

70. 发明公开

KR1020080002882A 터빈 휠 有权
标题翻译：涡轮轮
公开(公告)号：KR1020080002882A
公开(公告)日：2008-01-04
申请号：KR1020077024696
申请日：2006-03-24
申请人： 에이비비 터보 시스템즈 아게
发明人： 자일러마르틴
IPC分类号： F01D5/04 , F01D5/14
CPC分类号： F04D29/34 , F01D5/048 , F05D2220/40 , F05D2240/30 , F05D2250/70 , F05D2250/71
摘要： The invention relates to a turbine wheel (1) comprising a hub (15) and impeller blades (14), each impeller blade (14) being connected to the hub along a curved section (12) thereof. The impeller blades are embodied and arranged on the hub in such a way that the hub section (12) deviates from the radial direction and is bent towards the pressure side of the impeller blade, and the hub has a scalloping contour (11) between two adjacent impeller blades, in the region of a rear wall of the hub. The hub section (12) of each impeller blade (14) is positioned in relation to the scalloping surface (Fl + F2) in such a way that said surface is supported as symmetrically as possible by the impeller blade. Less stresses appear in the inventive turbine wheel with three-dimensionally curved impeller blades and scalloping in the region of the rear wall of the hub due to the scalloping deformations.
摘要翻译：本发明涉及一种包括轮毂（15）和叶轮叶片（14）的涡轮机叶轮（1），每个叶轮叶片（14）沿其弯曲部分（12）连接到轮毂。叶轮叶片被实施并布置在毂上，使得毂部分（12）从径向方向偏离并且朝向叶轮叶片的压力侧弯曲，并且轮毂在两个之间具有扇形轮廓（11）相邻的叶轮叶片，在轮毂的后壁的区域中。每个叶轮叶片（14）的轮毂部分（12）相对于扇形表面（F1 + F2）定位成使得所述表面由叶轮叶片尽可能对称地支撑。由于扇形变形，在本发明的涡轮机轮上出现较少的应力，其涡轮叶轮具有三维弯曲的叶轮叶片，并且在轮毂的后壁区域中产生扇形。

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