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1. 发明公开

EP1731716A2 Forward tilted turbine nozzle 有权
标题翻译： Forwärtsgeneigte Statorschaufel
公开(公告)号：EP1731716A2
公开(公告)日：2006-12-13
申请号：EP06252928.4
申请日：2006-06-06
申请人： The General Electric Company
发明人： Orlando, Robert Joseph , Lee, Ching-Pang , Beacock, Robert John , Carson, Scott Michael , Moniz, Thomas Ory , Cherry, David Glenn , Clifford, William Larson
IPC分类号： F01D9/04 , F01D5/14
CPC分类号： F01D5/141 , F01D5/142 , F01D9/041 , F02C3/067 , F02K3/072 , F05D2220/323 , F05D2250/314 , Y02T50/671 , Y02T50/673
摘要： A turbine nozzle (58) includes a row of vanes (60) joined to radially outwardly inclined outer and inner bands (62,64). Each vane (60) has camber and an acute twist angle for importing swirl in combustion gases discharged at trailing edges (80) thereof. The trailing edges (80) are tilted forwardly from the inner band (64) to the outer band (62) for increasing aerodynamic efficiency.
摘要翻译：涡轮喷嘴（58）包括连接到径向向外倾斜的外带和内带（62,64）的一排叶片（60）。每个叶片（60）具有外倾和用于在其后缘（80）处排出的燃烧气体中引入涡流的急扭角。后缘（80）从内带（64）向外倾斜到外带（62），以提高空气动力学效率。

2. 发明公开

EP1712737A1 Crescentic ramp turbine stage 有权
标题翻译： HalbmondförmigerTurbinenschaufel- /Plattformübergang
公开(公告)号：EP1712737A1
公开(公告)日：2006-10-18
申请号：EP06250684.5
申请日：2006-02-09
申请人： The General Electric Company
发明人： Lee, Ching-Pang , Kirtley, Kevin Richard , Tam, Anna , Lamson, Scott Henry
IPC分类号： F01D5/14
CPC分类号： F01D5/143 , F05D2250/711 , F05D2250/712 , Y02T50/673 , Y10S415/914
摘要： A turbine stage includes a row of airfoils (14) joined to corresponding platforms (16) to define flow passages (30) therebetween. Each airfoil (14) includes opposite pressure and suction sides (20,22) and extends in chord between opposite leading and trailing edges (24,26). Each platform (16) includes a crescentic ramp (32) increasing in height from the leading and trailing edges (24,26) toward the midchord of the airfoil (14) along the pressure side (20) thereof.
摘要翻译：涡轮级包括连接到相应的平台（16）的一排翼型件（14），以在它们之间限定流动通道（30）。每个翼片（14）包括相对的压力和吸力侧面（20,22），并且在相对的前缘和后缘（24,26）之间以和弦延伸。每个平台（16）包括新月形斜坡（32），其沿着其压力侧（20）从前缘和后缘（24,26）朝向翼型（14）的中部增加高度。

3. 发明公开

EP1698757A2 Bell-shaped film cooling holes for turbine airfoil 有权
标题翻译： GlockenförmigeÖffnungenzurFilmkühlungeiner Turbinenschaufel
公开(公告)号：EP1698757A2
公开(公告)日：2006-09-06
申请号：EP06251024.3
申请日：2006-02-27
申请人： The General Electric Company
发明人： Lee, Ching-Pang
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/18 , F05D2200/24 , F05D2250/20 , F05D2250/26 , F05D2250/292 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A turbine airfoil (22) having an external surface defining a curvature, and including a leading edge (26) and an axially spaced-part trailing edge (28), the leading edge (26) having an axially-extending aerodynamic external surface curvature. A plurality of cooling holes (50) are formed in the external surface of the airfoil (22) in fluid communication with the cooling circuit (40), at least some of the plurality of cooling holes (50) having a metering section (58) downstream of the cooling circuit (40), and a diffuser section (51). The side walls and one or the other of the top and bottom walls (55, 56) of the diffuser section (51) have a bell-shaped configuration for achieving a flow of the cooling film from the cooling circuit (40) with enhanced spread, enhanced attachment and less turbulence to a downstream surface of the airfoil (22) local to each respective cooling hole (50).
摘要翻译：具有限定曲率的外表面并且包括前缘（26）和轴向间隔开的后缘（28）的涡轮机翼片（22），所述前缘（26）具有轴向延伸的空气动力学外表面曲率。多个冷却孔（50）形成在与冷却回路（40）流体连通的翼型件（22）的外表面中，多个冷却孔（50）中的至少一些具有计量部分（58）冷却回路（40）的下游，以及扩散器部（51）。扩散器部分（51）的侧壁和顶壁和底壁（55,56）中的一个或另一个具有钟形构造，用于实现来自冷却回路（40）的冷却膜的流动，其具有增强的扩展增强了对各个冷却孔（50）局部的翼型件（22）的下游表面的附着和较少的湍流。

4. 发明公开

EP1726781A1 Turbine airfoil with tapered trailing edge ribs 审中-公开
标题翻译： Tippinenblatt mitverjüngtenRippen an derAbströmkante
公开(公告)号：EP1726781A1
公开(公告)日：2006-11-29
申请号：EP06251686.9
申请日：2006-03-28
申请人： The General Electric Company
发明人： Lee, Ching-Pang , Brassfield, Steven Robert , Danowski, Michael Joseph , Singh, Hardev
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2250/13 , F05D2250/184 , F05D2250/292 , F05D2260/221 , Y02T50/673 , Y02T50/676
摘要： An airfoil (118) for a gas turbine engine has opposed pressure and suction sidewalls (120), (122) extending between a leading edge (124) and a trailing edge (126). The airfoil includes an array of radially-spaced apart longitudinally-extending lands (130) which define a plurality of trailing edge slots (128) therebetween. Each of the trailing edge slots (128) has an inlet in fluid communication with an interior of the airfoil (118) and an exit (134) in fluid communication with the trailing edge (126). At least one of the lands (130) is tapered such that a width of the land (130) measured in a radial direction decreases from the suction sidewall (122) to the pressure sidewall (120).
摘要翻译：用于燃气涡轮发动机的翼型件（118）具有在前缘（124）和后缘（126）之间延伸的相对的压力和吸力侧壁（120），（122）。翼型件包括沿径向间隔开的纵向延伸的平台（130）的阵列，其在它们之间限定多个后缘槽（128）。每个后缘槽（128）具有与翼型件（118）的内部和与后缘（126）流体连通的出口（134）流体连通的入口。所述焊盘（130）中的至少一个是锥形的，使得沿径向测量的焊盘（130）的宽度从抽吸侧壁（122）减小到压力侧壁（120）。

5. 发明公开

EP1691033A1 Rectangular diffusion hole for film cooled turbine airfoil 有权
标题翻译： Rechteckiges DiffusorlochfürfilmgekühlteTurbinenschaufel
公开(公告)号：EP1691033A1
公开(公告)日：2006-08-16
申请号：EP06250410.5
申请日：2006-01-25
申请人： The General Electric Company
发明人： Lee, Ching-Pang
IPC分类号： F01D5/18
CPC分类号： B23H9/10 , F01D5/186 , F05D2250/12 , F05D2260/202
摘要： A turbine airfoil (32) includes a leading edge (36) and an axially spaced-part trailing edge (38), the leading edge (36) having an axially-extending external surface curvature. A cooling circuit (50) in the airfoil includes cooling holes (60) formed in the leading edge (36) along the span axis of the airfoil. The cooling holes (60) have a diffuser section communicating with the leading edge (36) surface. The diffuser section has four opposed walls defining a generally quadralinear exit opening on the surface of the leading edge (36). One of the diffuser walls has a convex curvature that approximates the external surface curvature of the leading edge (36) whereby fluid flow from the cooling hole exits is evenly dispersed and spread along land portions of the leading edge (36) adjacent the cooling holes (60).
摘要翻译：涡轮机翼片（32）包括前缘（36）和轴向间隔开的后缘（38），前缘（36）具有轴向延伸的外表面曲率。机翼中的冷却回路（50）包括沿着翼型的跨度轴线形成在前缘（36）中的冷却孔（60）。冷却孔（60）具有与前缘（36）表面连通的扩散器部分。扩散器部分具有在前缘（36）的表面上限定大致四边形出口的四个相对的壁。扩散壁之一具有近似于前缘（36）的外表面曲率的凸曲率，从而来自冷却孔的流体流出物均匀地分散并且沿与冷却孔相邻的前缘（36）的陆部分散布 60）。

6. 发明公开

EP1681438A2 Turbine stage with scalloped surface platform 有权转让
标题翻译： Turbinenstufe mitbogenförmigerPlattformoberfläche
公开(公告)号：EP1681438A2
公开(公告)日：2006-07-19
申请号：EP05257850.7
申请日：2005-12-20
申请人： The General Electric Company
发明人： Tam, Anna , Lee, Ching-Pang , Kirtley, Kevin Richard , Bunker, Ronald Scott , Lamson, Scott Henry , Carson, Scott Michael
IPC分类号： F01D5/14
CPC分类号： F01D5/145 , F01D5/143 , F05D2240/80 , F05D2250/70 , F05D2250/711 , F05D2250/712 , Y02T50/673
摘要： A turbine stage includes a row of airfoils (14) joined to corresponding platforms (16) to define flow passages (36) therebetween. Each airfoil (14) includes opposite pressure and suction sides (20, 22) and extends in chord between opposite leading and trailing edges (24, 26). Each platform (16) has a scalloped flow surface including a bulge (38) adjoining the pressure side (20) adjacent the leading edge (24), and a bowl (40) adjoining the suction side (22) aft of the leading edge (24).
摘要翻译：涡轮级包括连接到相应的平台（16）的一排翼型件（14），以在它们之间限定流动通道（36）。每个翼片（14）包括相对的压力和吸力侧（20,22），并且在相对的前缘和后缘（24,26）之间以和弦延伸。每个平台（16）具有扇形流动表面，该扇形流动表面包括邻近前缘（24）的压力侧（20）的凸起（38）和邻接前缘边缘的吸力侧（22） 24）。

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