公开(公告)号：US20150233253A1

公开(公告)日：2015-08-20

申请号：US14700517

申请日：2015-04-30

申请人： IHI Corporation

发明人： Masaaki HAMABE ,  Ayumi MAMADA ,  Ruriko YAMAWAKI ,  Hiroshi HAMAZAKI ,  Akira TAKAHASHI

IPC分类号： F01D5/14

CPC分类号： F01D5/141 ,  F01D5/14 ,  F01D5/147 ,  F01D9/02 ,  F05D2220/30 ,  F05D2240/304 ,  F05D2250/14 ,  F05D2250/71 ,  Y02T50/671 ,  Y02T50/673

摘要： A turbine blade has a profile including a blade suction side line, a blade pressure side line, and a blade trailing edge positioned between the rear ends of the blade suction side and pressure sidelines. The blade trailing edge of the profile is formed by connecting a pressure side arc-like curve having a constant radius of curvature and extending from the rear end of the blade pressure side line toward the camber line of the profile, and a suction side line portion which extends from the rear end of the blade suction side line toward the camber line while passing through a region closer to the camber line than a symmetric curve portion which is line-symmetric to the pressure side arc-like curve with respect to the camber line. The suction side line portion is represented by curves constituting ellipses which constitute ellipses, and a straight line.

摘要翻译： 涡轮叶片具有包括叶片吸入侧线，叶片压力侧线和位于叶片吸入侧的后端和压力侧线之间的叶片后缘的轮廓。 轮廓的叶片后缘通过连接具有恒定曲率半径并且从叶片压力侧线的后端朝向轮廓的弯度线延伸的压力侧弧形曲线形成，并且吸力侧线部分 其从叶片吸入侧线的后端朝向弯曲线延伸，同时穿过比靠近外倾线的区域比相对于弯度线与压力侧弧形曲线线对称的对称曲线部分 。 抽吸侧线部分由构成椭圆形的椭圆的曲线和直线表示。

公开(公告)号：US09103220B2

公开(公告)日：2015-08-11

申请号：US13643569

申请日：2011-04-20

申请人： Fabrice Marcel Noel Garin ,  Alain Dominique Gendraud ,  Thierry Lequitte ,  Romain Nicolas Lunel

发明人： Fabrice Marcel Noel Garin ,  Alain Dominique Gendraud ,  Thierry Lequitte ,  Romain Nicolas Lunel

IPC分类号： F01D5/30 ,  F01D5/08

CPC分类号： F01D5/3092 ,  F01D5/081 ,  F01D5/3007 ,  F05D2240/81 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2260/20 ,  F05D2260/30 ,  F05D2260/36 ,  F05D2260/941 ,  F05D2260/96

摘要： An interface element to be mounted between a blade root and a blade root housing provided in a turbine disc of a gas turbine engine to limit wear between the root and the housing. The interface element includes: a base, configured to be aligned with a lower part of the root; and first and second upper side walls connected to the base and configured to surround the blade root up to an upper portion thereof, the first upper side wall including at least one ventilation opening to allow a flow of cooling air flowing through the rotor disc housing to flow over the upper portion of the root via the ventilation opening.

摘要翻译： 安装在叶片根部和设置在燃气涡轮发动机的涡轮盘中的叶片根部壳体之间的界面元件，以限制根部和壳体之间的磨损。 接口元件包括：基座，构造成与根部的下部对准; 以及第一和第二上侧壁，其连接到基部并且被构造成围绕叶片根部直到其上部，第一上侧壁包括至少一个通风开口，以允许流过转子盘壳体的冷却空气流动到 通过通风口流过根部的上部。

公开(公告)号：US20150184523A1

公开(公告)日：2015-07-02

申请号：US14143599

申请日：2013-12-30

申请人： General Electric Company

发明人： Stephen Paul Wassynger ,  Aaron Ezekiel Smith

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F01D5/188 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/71 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2250/713 ,  F05D2250/75 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

摘要： A turbine blade having an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may include a rib configuration that partitions the chamber and defines a flow passage having a first and a second side. The flow passage may include a port formed through the first side. A projection of a center axis of the port through the flow passage may define a strike point on the second side of the flow passage, and a backstrike recess may be positioned on the second side of the flow passage so to contain the strike point.

摘要翻译： 一种具有由凹形压力侧外壁和凸形吸入侧外壁限定的翼型件的涡轮机叶片，其沿着前缘和后缘连接，并且在它们之间形成用于接收冷却剂流动的径向延伸室。 涡轮机叶片可以包括肋构造，其分隔室并限定具有第一侧和第二侧的流动通道。 流路可以包括通过第一侧形成的端口。 通过流动通道的端口的中心轴线的突起可以限定流动通道的第二侧上的撞击点，并且反冲击凹口可以定位在流动通道的第二侧上以便容纳撞击点。

公开(公告)号：US20150184521A1

公开(公告)日：2015-07-02

申请号：US14143564

申请日：2013-12-30

申请人： General Electric Company

发明人： Lisa Anne Wichmann ,  Aaron Ezekiel Smith

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F01D5/188 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/71 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2250/713 ,  F05D2250/75 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141 ,  Y02T50/676

摘要： A turbine blade comprising an airfoil defined by a concave shaped pressure side outer wall and a convex shaped suction side outer wall that connect along leading and trailing edges and, therebetween, form a radially extending chamber for receiving the flow of a coolant. The turbine blade may further include: a rib configuration that partitions the chamber into radially extending flow passages that include a first flow passage and a second flow passage; and a crossover passage that fluidly connects an inlet formed in the first flow passage to an outlet formed in the second flow passage. The crossover passage may include a canted configuration relative to the second flow passage.

摘要翻译： 一种涡轮机叶片，包括由凹形压力侧外壁和凸形吸入侧外壁限定的翼型件，该外壁沿着前缘和后缘连接，并且在其之间形成用于接收冷却剂流的径向延伸的室。 涡轮叶片还可以包括：肋构造，其将腔室分隔成径向延伸的流动通道，其包括第一流动通道和第二流动通道; 以及将形成在第一流动通道中的入口流体连接到形成在第二流动通道中的出口的交叉通道。 交叉通道可以包括相对于第二流动通道的倾斜构造。

公开(公告)号：US20150184520A1

公开(公告)日：2015-07-02

申请号：US14143472

申请日：2013-12-30

申请人： General Electric Company

发明人： Brian Denver Potter ,  Gregory Thomas Foster

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F01D5/188 ,  F05D2240/305 ,  F05D2240/306 ,  F05D2250/71 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2250/713 ,  F05D2250/75 ,  F05D2260/22141 ,  Y02T50/676

摘要： A turbine blade that includes an airfoil and a radially extending chamber therein for a coolant. The turbine blade may also include a rib configuration that partitions the chamber into radially extending flow passages. The rib configuration may include: a camber line rib that defines a near-wall flow chamber; and traverse ribs extending between the camber line rib and one of the outer walls so to divide the near-wall flow chamber into successively stacked flow passages that each include a segment of the camber line rib. The segment of the camber line rib of one of the flow passages may have a narrowing profile that includes a profile that narrows from opposing ends toward a neck disposed therebetween.

摘要翻译： 一种涡轮机叶片，其包括用于冷却剂的翼型件和径向延伸的室。 涡轮叶片还可以包括将腔室分隔成径向延伸的流动通道的肋构型。 所述肋构造可以包括：限定近壁流动室的弧形线肋; 以及在所述弯曲肋条和所述外壁中的一个之间延伸的横向肋，以便将所述近壁流动室分成依次层叠的流动通道，每个所述流动通道包括所述弯曲肋条的一段。 一个流动通道的弧形线肋的段可以具有变窄轮廓，其包括从相对端变窄到设置在它们之间的颈部的轮廓。

公开(公告)号：US09068513B2

公开(公告)日：2015-06-30

申请号：US13747868

申请日：2013-01-23

申请人： Ching-Pang Lee

发明人： Ching-Pang Lee

IPC分类号： F04D31/00 ,  F02C7/28 ,  F01D5/08 ,  F01D11/00 ,  F01D11/04

CPC分类号： F02C7/28 ,  F01D5/082 ,  F01D11/001 ,  F01D11/04 ,  F05D2250/71

摘要： A seal assembly between a disc cavity and a hot gas path in a gas turbine engine includes a rotating blade assembly having a plurality of blades that rotate with a turbine rotor during operation of the engine, and a stationary vane assembly having a plurality of vanes and an inner shroud. The inner shroud includes a radially outwardly facing first surface, a radially inwardly facing second surface, and a plurality of grooves extending into the second surface. The grooves are arranged such that a space having a component in a circumferential direction is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

摘要翻译： 燃气涡轮发动机中的盘腔和热气路之间的密封组件包括旋转叶片组件，其具有在发动机运转期间与涡轮转子一起旋转的多个叶片，以及具有多个叶片和 内罩。 内护罩包括径向向外的第一表面，径向向内的第二表面和延伸到第二表面中的多个凹槽。 凹槽被布置成使得在相邻凹槽之间限定具有圆周方向的部件的空间。 在发动机操作期间，凹槽将吹扫空气从盘腔朝向热气路径引导，使得净化空气相对于热气流通过热气路径的方向在所需方向上流动。

公开(公告)号：US09003759B2

公开(公告)日：2015-04-14

申请号：US11719799

申请日：2004-12-01

申请人： Gabriel Suciu ,  Gary D. Roberge ,  Brian Merry

发明人： Gabriel Suciu ,  Gary D. Roberge ,  Brian Merry

IPC分类号： F02G3/00 ,  F02C7/052 ,  F01D5/02 ,  F02C3/073 ,  F02C7/05 ,  F02K3/068

CPC分类号： F02C7/052 ,  F01D5/022 ,  F02C3/073 ,  F02C7/05 ,  F02K3/068 ,  F05D2250/71

摘要： A particle separator (20) for a tip turbine engine (10) includes a generally conical inclined leading surface (24) leading to a maximum radius (25) and a tapered trailing surface (56) having a radius at all points therealong less than the maximum radius (25). The trailing surface (56) of the particle separator (20) is tapered and/or curved radially inwardly away from the maximum radius (25). Air flowing toward the core airflow inlet is first diverted radially outwardly by the inclined leading surface (24) of the particle separator (20) to the maximum radius (25) of the particle separator (20). The air then follows the trailing surface (56) radially inwardly to flow axially into the core airflow inlet. While the air can follow the contours of the particle separator (20) around the maximum radius (25) and into the core airflow inlet, any particles, such as dirt, will have more inertia and will pass radially outwardly of the core airflow inlet through the bypass fan.

摘要翻译： 用于尖端涡轮发动机（10）的颗粒分离器（20）包括通向圆锥形的倾斜前导表面（24），其导致最大半径（25）和锥形后表面（56），所述锥形后表面在所有点处具有小于 最大半径（25）。 颗粒分离器（20）的后表面（56）从最大半径（25）向内径向向内渐缩和/或弯曲。 首先通过颗粒分离器（20）的倾斜引导表面（24）向颗粒分离器（20）的最大半径（25）径向向外转向空气流向核心气流入口。 然后空气径向向内跟随后表面（56），从而轴向流入核心气流入口。 当空气可以沿着最大半径（25）和颗粒气流入口跟随颗粒分离器（20）的轮廓时，任何颗粒（例如污物）将具有更大的惯性并且将通过核心气流入口的径向向外通过 旁路风扇。

公开(公告)号：US20140310959A1

公开(公告)日：2014-10-23

申请号：US14324952

申请日：2014-07-07

申请人： General Electric Company

发明人： Kevin Michael Fiebig ,  Joshua Brown ,  Joseph Nath

IPC分类号： F01N13/18

CPC分类号： F01N13/18 ,  F02C7/222 ,  F05D2220/32 ,  F05D2230/51 ,  F05D2250/71 ,  F05D2250/75 ,  F05D2260/96

摘要： A method of assembling a fluid manifold includes: providing an array of spaced-apart manifold fittings, each manifold fitting having: a generally tubular neck; a pair of spaced-apart generally tubular arms extending away from a first end of the neck; and a coupling connected to a second end of the neck; and placing each manifold fitting in a predetermined angular orientation; and providing a plurality of curved tubes, and coupling one end of each tube to one arm of each of two adjacent ones of the manifold fittings, such that the assembled manifold has a predetermined first natural frequency.

摘要翻译： 组装流体歧管的方法包括：提供间隔开的歧管配件的阵列，每个歧管配件具有：大致管状的颈部; 一对间隔开的大致管状臂，远离颈部的第一端延伸; 以及连接到所述颈部的第二端的联接器; 并将每个歧管配件放置在预定的角度定向中; 并且提供多个弯曲管，并且将每个管的一端联接到两个相邻的歧管配件中的每一个的一个臂，使得组装的歧管具有预定的第一固有频率。

公开(公告)号：US20140205441A1

公开(公告)日：2014-07-24

申请号：US14043958

申请日：2013-10-02

申请人： Ching-Pang Lee

发明人： Ching-Pang Lee

IPC分类号： F02C7/28

CPC分类号： F01D11/001 ,  F01D11/02 ,  F05D2240/80 ,  F05D2250/37 ,  F05D2250/38 ,  F05D2250/71 ,  F05D2260/14

摘要： A seal assembly between a disc cavity and a turbine section hot gas path includes a stationary vane assembly and a rotating blade assembly downstream from the vane assembly and including a plurality of blades that are supported on a platform and rotate with a turbine rotor and the platform during operation of the engine. The platform includes a radially outwardly facing first surface, a radially inwardly facing second surface, a third surface, and a plurality of grooves extending into the third surface. The grooves are arranged such that a space is defined between adjacent grooves. During operation of the engine, the grooves guide purge air out of the disc cavity toward the hot gas path such that the purge air flows in a desired direction with reference to a direction of hot gas flow through the hot gas path.

摘要翻译： 在盘腔和涡轮部分热气路径之间的密封组件包括固定叶片组件和在叶片组件下游的旋转叶片组件，并且包括支撑在平台上并与涡轮转子和平台一起旋转的多个叶片 在发动机运行期间。 平台包括径向向外的第一表面，径向向内的第二表面，第三表面和延伸到第三表面中的多个凹槽。 凹槽被布置成使得在相邻凹槽之间限定空间。 在发动机操作期间，凹槽将吹扫空气从盘腔朝向热气路径引导，使得净化空气相对于热气流通过热气路径的方向在所需方向上流动。

公开(公告)号：US20140178198A1

公开(公告)日：2014-06-26

申请号：US14125266

申请日：2012-05-30

申请人： Richard Bluck ,  Carlos Felipe Favaretto ,  Stuart Stott

发明人： Richard Bluck ,  Carlos Felipe Favaretto ,  Stuart Stott

IPC分类号： F01D5/08

CPC分类号： F01D5/081 ,  F01D5/187 ,  F05D2250/71

摘要： A root section of a rotor blade for interacting with working fluid upon rotating the rotor blade is provided. The root section includes a curved cooling passage for guiding a cooling fluid within the root section. A cooling fluid entry plenum has an entry aperture for introducing the cooling fluid into the cooling passage. A platform is located at a radially outer end of the root section. The curved cooling passage penetrates through the platform, and the following condition is satisfied at least in a portion of a radial extent of the cooling passage: 0.25*dr

摘要翻译： 提供了一种用于在旋转转子叶片时与工作流体相互作用的转子叶片的根部分。 根部包括用于引导根部内的冷却流体的弯曲冷却通道。 冷却流体进入气室具有用于将冷却流体引入冷却通道的入口孔。 平台位于根部的径向外端。 弯曲的冷却通道穿过平台，并且至少在冷却通道的径向部分的一部分中满足以下条件：0.25 * dr