公开(公告)号：US10408066B2

公开(公告)日：2019-09-10

申请号：US13586071

申请日：2012-08-15

申请人： Wieslaw A. Chlus ,  Seth J. Thomen

发明人： Wieslaw A. Chlus ,  Seth J. Thomen

IPC分类号： F01D5/20

摘要： An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial direction. The airfoil has a cooling passage arranged between the pressure and suction walls that extend toward a tip of the airfoil. The tip includes a pocket that separates the pressure and suction walls. Scarfed cooling holes fluidly connect the cooling passage to the pocket. The scarfed cooling holes include a portion that is recessed into a face of the suction wall and exposed to the pocket.

公开(公告)号：US20140047842A1

公开(公告)日：2014-02-20

申请号：US13586071

申请日：2012-08-15

申请人： Wieslaw A. Chlus ,  Seth J. Thomen

发明人： Wieslaw A. Chlus ,  Seth J. Thomen

IPC分类号： F01D5/18 ,  F02C7/12 ,  F02C3/04

CPC分类号： F01D5/20 ,  F05D2250/14 ,  F05D2250/232 ,  F05D2250/324 ,  F05D2260/202 ,  Y02T50/676

摘要： An airfoil for a gas turbine engine includes pressure and suction walls spaced apart from one another and joined at leading and trailing edges to provide an airfoil that extends in a radial direction. The airfoil has a cooling passage arranged between the pressure and suction walls that extend toward a tip of the airfoil. The tip includes a pocket that separates the pressure and suction walls. Scarfed cooling holes fluidly connect the cooling passage to the pocket. The scarfed cooling holes include a portion that is recessed into a face of the suction wall and exposed to the pocket.

摘要翻译： 用于燃气涡轮发动机的翼型件包括彼此间隔开并在前缘和后缘连接的压力和吸力壁，以提供在径向方向上延伸的翼型件。 翼型件具有设置在压力和吸力壁之间的冷却通道，其朝向翼型件的尖端延伸。 尖端包括分隔压力和吸力壁的口袋。 围绕的冷却孔将冷却通道流体地连接到口袋。 所述被切割的冷却孔包括凹入到所述吸入壁的表面并暴露于所述口袋的部分。

公开(公告)号：US20130318787A1

公开(公告)日：2013-12-05

申请号：US13489074

申请日：2012-06-05

申请人： Seth J. Thomen ,  Wieslaw A. Chlus

发明人： Seth J. Thomen ,  Wieslaw A. Chlus

IPC分类号： B23P15/02

CPC分类号： B23P15/02 ,  F01D5/3007 ,  F05D2230/61 ,  Y10T29/49336

摘要： A method of manufacturing a family of airfoils includes providing a plurality of airfoil blanks of identical geometry, selecting a first airfoil geometry from a family of airfoil geometries, selecting a second, different airfoil geometry from the family of airfoil geometries, machining a first one of the plurality of airfoil blanks to the first airfoil geometry to produce a first airfoil of the family of airfoil geometries, and machining a second, different one of the plurality of airfoil blanks to the second airfoil geometry to produce a second, different airfoil of the family of airfoil geometries

摘要翻译： 制造翼型族的方法包括提供多个具有相同几何形状的翼型毛坯，从翼型几何形状中选择第一翼型几何形状，从翼型几何形状中选择第二不同的翼型几何形状， 所述多个翼型毛坯到所述第一翼型件几何形状以产生所述翼型几何形状的第一翼型，并且将所述多个翼型毛坯中的第二不同的翼型坯加工到所述第二翼型件几何形状以产生所述系列的第二不同翼型 的翼型几何

公开(公告)号：US07175386B2

公开(公告)日：2007-02-13

申请号：US10738842

申请日：2003-12-17

申请人： Anthony Cherolis ,  Wieslaw A. Chlus

发明人： Anthony Cherolis ,  Wieslaw A. Chlus

IPC分类号： F01D5/14

CPC分类号： F01D5/187 ,  F05D2260/2212 ,  Y02T50/676

摘要： A blade for a gas turbine engine includes a trailing edge cooling chamber, wherein the pressure and suction sides are connected by an array of spaced pedestals. The pedestals in a region most subject to thermal stresses are formed to be elliptical, such that the thermal stresses are spread over a larger area. Thus, stress concentrations are reduced. Also, various sized cylindrical pedestals may be used at other locations.

摘要翻译： 用于燃气涡轮发动机的叶片包括后缘冷却室，其中压力和吸力侧通过间隔开的基座的阵列连接。 最受热应力的区域中的基座形成为椭圆形，使得热应力分布在更大的面积上。 因此，应力集中减少。 此外，可以在其他位置使用各种尺寸的圆柱形基座。

公开(公告)号：US4971272A

公开(公告)日：1990-11-20

申请号：US373969

申请日：1989-06-29

申请人： Joan M. Gudridge ,  Clement A. Senatro ,  Wieslaw A. Chlus

发明人： Joan M. Gudridge ,  Clement A. Senatro ,  Wieslaw A. Chlus

IPC分类号： F02C9/28 ,  F16L3/12 ,  F16L3/137

CPC分类号： F16L3/137 ,  Y10T24/141

摘要： A support structure 10 for positioning a conduit 12 for various environments including that of an aircraft gas turbine engine is disclosed. Various construction details are developed for the support structure which facilitate assembly of portions of the support structure. The support structure includes a clamp assembly 18 and a clip 22 for orienting the clamp assembly in the proper direction. Orientation of the clamp assembly is facilitated by features of the clip. These features include a pair of tabs 32, 34 which face each other from either side of the clamp assembly. In one detailed embodiment, the clamp includes a laterally extending tab 92 to block the channel formed between the pair of longitudinally extending tabs.

摘要翻译： 公开了一种用于定位用于包括飞机燃气涡轮发动机的各种环境的管道12的支撑结构10。 开发了用于支撑结构的各种构造细节，其有利于组装支撑结构的部分。 支撑结构包括用于使夹具组件沿正确方向定向的夹具组件18和夹子22。 夹子组件的方向由夹具的特征促进。 这些特征包括从夹具组件的任一侧彼此面对的一对翼片32,34。 在一个详细的实施例中，夹具包括横向延伸的突片92，以阻挡形成在一对纵向延伸突片之间的通道。

公开(公告)号：US4747750A

公开(公告)日：1988-05-31

申请号：US819943

申请日：1986-01-17

申请人： Wieslaw A. Chlus ,  Stephen E. Potz ,  Arthur W. Lucas, Jr.

发明人： Wieslaw A. Chlus ,  Stephen E. Potz ,  Arthur W. Lucas, Jr.

IPC分类号： F01D11/02 ,  F02C7/28 ,  F04D29/08

CPC分类号： F02C7/28 ,  F01D11/025

摘要： An inner wall for a transition duct between the high pressure and low pressure turbines of a multirotor gas turbine engine in which the wall structure itself is made up of multiple aligned segments which are bolted to the inner shrouds of the vane clusters of the low pressure turbine and in which the segments are secured to forward and rearward cone elements with one of said elements bolted securely to the segments and the other cone having free axial and radial movement with respect to the segments with the cone elements supporting at their inner edges a seal element to cooperate with a rotating element on a low pressure rotor.

摘要翻译： 用于多转轮燃气涡轮发动机的高压和低压涡轮机之间的过渡管道的内壁，其中壁结构本身由多个对准的段组成，该多个对准的段螺栓连接到低压涡轮机的叶片组的内护罩 并且其中所述段被固定到前后锥形元件，其中一个所述元件牢固地螺栓固定到所述段，并且所述另一个锥体相对于所述段具有自由的轴向和径向运动，所述锥形元件在其内边缘处支撑有密封元件 与低压转子上的旋转元件配合。

公开(公告)号：US07726944B2

公开(公告)日：2010-06-01

申请号：US11524102

申请日：2006-09-20

申请人： Richard H. Page ,  Wieslaw A. Chlus

发明人： Richard H. Page ,  Wieslaw A. Chlus

IPC分类号： F01D5/18

CPC分类号： F01D5/20 ,  F05D2240/307 ,  F05D2260/20 ,  F05D2260/2214 ,  Y02T50/676

摘要： A gas turbine engine has a turbine blade having a tip cap to close off internal cooling passages. The tip cap is formed with a plurality of purge holes, with there being at least two rows of purge holes. The increased number of purge holes spreads the cooling air outwardly across more of the surface area of the tip cap, and provides the tip cap with a better ability to withstand the extreme temperatures it faces in use.

摘要翻译： 燃气涡轮发动机具有涡轮叶片，其具有尖端盖以封闭内部冷却通道。 尖端盖形成有多个吹扫孔，其中至少有两排吹扫孔。 吹扫孔数量的增加将冷却空气向外扩散到尖端盖的更多表面区域，并且提供顶盖具有更好的耐受其使用的极端温度的能力。

公开(公告)号：US20100080711A1

公开(公告)日：2010-04-01

申请号：US11524102

申请日：2006-09-20

申请人： Richard H. Page ,  Wieslaw A. Chlus

发明人： Richard H. Page ,  Wieslaw A. Chlus

IPC分类号： F01D5/18

CPC分类号： F01D5/20 ,  F05D2240/307 ,  F05D2260/20 ,  F05D2260/2214 ,  Y02T50/676

摘要： A gas turbine engine has a turbine blade having a tip cap to close off internal cooling passages. The tip cap is formed with a plurality of purge holes, with there being at least two rows of purge holes. The increased number of purge holes spreads the cooling air outwardly across more of the surface area of the tip cap, and provides the tip cap with a better ability to withstand the extreme temperatures it faces in use.

摘要翻译： 燃气涡轮发动机具有涡轮叶片，其具有尖端盖以封闭内部冷却通道。 尖端盖形成有多个吹扫孔，其中至少有两排吹扫孔。 吹扫孔数量的增加将冷却空气向外扩散到尖端盖的更多表面区域，并且提供顶盖具有更好的耐受其使用的极端温度的能力。

公开(公告)号：US06824359B2

公开(公告)日：2004-11-30

申请号：US10355664

申请日：2003-01-31

申请人： Wieslaw A. Chlus ,  Stanley J. Funk

发明人： Wieslaw A. Chlus ,  Stanley J. Funk

IPC分类号： F01D518

CPC分类号： F01D5/187 ,  F01D5/189 ,  F01D5/20 ,  F05D2230/10 ,  F05D2230/13 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/191 ,  F05D2250/192 ,  F05D2250/712 ,  F05D2260/22141 ,  F05D2260/607

摘要： A turbine blade has a platform and an airfoil extending from a root at the platform to a tip. The airfoil has an internal cooling passageway network including at least one trailing edge cavity. A group of trailing edge holes extends from the trailing edge to the trailing edge cavity and a group of tip holes extends from the tip to the trailing edge cavity.

摘要翻译： 涡轮叶片具有平台和从平台上的根延伸到尖端的翼型件。 翼型件具有包括至少一个后缘腔的内部冷却通道网络。 一组后缘孔从后缘延伸到后缘腔，并且一组尖端孔从尖端延伸到后缘腔。

公开(公告)号：US5284421A

公开(公告)日：1994-02-08

申请号：US980848

申请日：1992-11-24

申请人： Wieslaw A. Chlus ,  David P. Houston

发明人： Wieslaw A. Chlus ,  David P. Houston

IPC分类号： F01D5/26 ,  F01D5/22 ,  F01D5/10

CPC分类号： F01D5/22 ,  Y10S416/50

摘要： A rotor blade having axially spaced gussets disposed between a root portion and a platform is disclosed. Various construction details are developed which provide a gusset providing both platform support and damper positioning means. In one particular embodiment, a rotor blade assembly includes a plurality of circumferentially spaced rotor blades having dampers disposed between adjacent blades, wherein each blade includes an axially spaced pair of gussets extending laterally from the rotor blade. The gussets extend from a root portion of the rotor blade to a platform and provide radial support of the platform during rotation of the rotor assembly. The gussets include a curved lateral edge which, during rotation of the rotor assembly, urges the damper away from the root portion of the blade.

摘要翻译： 公开了一种具有设置在根部和平台之间的具有轴向间隔的角撑板的转子叶片。 开发了各种构造细节，其提供提供平台支撑和阻尼器定位装置的角撑板。 在一个具体实施例中，转子叶片组件包括多个周向间隔开的转子叶片，其具有设置在相邻叶片之间的阻尼器，其中每个叶片包括从转子叶片横向延伸的轴向间隔开的一对角撑板。 角撑板从转子叶片的根部延伸到平台并且在转子组件旋转期间提供平台的径向支撑。 角撑板包括弯曲的侧边缘，其在转子组件的旋转期间促使阻尼器远离叶片的根部。