公开(公告)号：US06951447B2

公开(公告)日：2005-10-04

申请号：US10738288

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： F01D5/147 ,  F01D5/141 ,  F05D2230/80 ,  F05D2240/80 ,  F05D2250/71 ,  Y02T50/673

摘要： A turbine blade has an undercut beneath its platform at a trailing edge. The undercut has a complex shape to move thermal stress concentration away from the platform. A preferred undercut shape has a pair of curved fillets at upper and lower extents of the undercut with an intermediate straight section. The intermediate straight section is preferably parallel to a principle stress field of the platform.

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：US20070269315A1

公开(公告)日：2007-11-22

申请号：US11437189

申请日：2006-05-18

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

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

IPC分类号： F01D5/30

CPC分类号： F01D5/3007 ,  F01D11/006

摘要： A rotor assembly having a seal member in the root section of a rotor blade is disclosed. Various construction details are developed for blocking the flow of gases between adjacent rotor blades. In one detailed embodiment, a deformable seal member formed of a high temperature material is disposed between the root sections of adjacent rotor blades and engages the blades under operative conditions.

摘要翻译： 公开了一种转子组件，其具有在转子叶片的根部中的密封构件。 开发了各种结构细节来阻止相邻转子叶片之间的气体流动。 在一个详细的实施例中，由高温材料形成的可变形的密封件设置在相邻的转子叶片的根部之间并在操作条件下与叶片接合。

公开(公告)号：US07059834B2

公开(公告)日：2006-06-13

申请号：US10350635

申请日：2003-01-24

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

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

IPC分类号： F01D5/18

CPC分类号： F01D5/147 ,  F01D5/187 ,  F01D5/20 ,  F05D2230/21 ,  F05D2230/235

摘要： A turbine blade tip plenum has means for preferentially directing or diverting cooling air from a cooling passageway network to cool areas subject to extreme heat.

摘要翻译： 涡轮叶片尖端气室具有用于优先地将冷却空气从冷却通道网络引导或转向冷却受极端热的区域的装置。

公开(公告)号：US5313786A

公开(公告)日：1994-05-24

申请号：US980085

申请日：1992-11-24

申请人： Wieslaw A. Chlus ,  Michael Gonsor ,  David P. Houston ,  Paul D. Kudra

发明人： Wieslaw A. Chlus ,  Michael Gonsor ,  David P. Houston ,  Paul D. Kudra

IPC分类号： F01D5/26 ,  F01D5/22 ,  F01D11/00 ,  F02C3/00

CPC分类号： F01D5/22 ,  F01D11/006 ,  F05D2260/97 ,  Y10S416/50

摘要： An integrated damper and windage cover 52 has a windage cover portion 56 cantilevered at the upstream end, free of contact with the blade platform 24, 32. The contact portion 54 is rigid and bears against the underside of the blade platform 24, spanning blade platform clearance 50.

摘要翻译： 集成的阻尼器和风挡盖52具有在上游端悬臂的防风罩部分56，与叶片平台24,32没有接触。接触部分54是刚性的，并且抵靠在叶片平台24的下侧，跨越叶片平台 清关50。