公开(公告)号：US20130167870A1

公开(公告)日：2013-07-04

申请号：US13339468

申请日：2011-12-29

申请人： Mark Carmine Bellino ,  Jonathan Matthew Lomas ,  Matthew Paul Berkebile

发明人： Mark Carmine Bellino ,  Jonathan Matthew Lomas ,  Matthew Paul Berkebile

IPC分类号： B08B9/032 ,  B08B3/02

CPC分类号： B08B17/00 ,  B24C3/32 ,  B24C11/00 ,  F05D2230/80 ,  F05D2230/90

摘要： Methods of pressure cleaning a target surface of an article comprising one or more passageways include fluidly connecting a pressure masker comprising pressurized masking fluid to a first side of at least one passageway, passing the pressurized masking fluid through the at least one passageway from the first side to a second side comprising the target surface, and, cleaning the target surface using a cleaning material, wherein the pressurized masking fluid passing through the at least one passageway prevents the cleaning material from permanently altering a cross sectional area of the at least one passageway.

摘要翻译： 包括一个或多个通道的制品的目标表面的压力清洁方法包括将包括加压掩模流体的压力掩模流体地连接到至少一个通道的第一侧，使加压的掩蔽流体从第一侧通过至少一个通道 到包括目标表面的第二侧，以及使用清洁材料清洁目标表面，其中通过所述至少一个通道的所述加压掩蔽流体防止所述清洁材料永久地改变所述至少一个通道的横截面积。

公开(公告)号：US08734111B2

公开(公告)日：2014-05-27

申请号：US13169142

申请日：2011-06-27

申请人： Jonathan Matthew Lomas ,  Mark Lawrence Hunt

发明人： Jonathan Matthew Lomas ,  Mark Lawrence Hunt

IPC分类号： F01D5/14

CPC分类号： F01D5/187 ,  F05D2230/10 ,  F05D2240/81 ,  F05D2250/185 ,  F05D2250/294 ,  F05D2260/202 ,  F05D2260/22141 ,  Y02T50/676 ,  Y10T29/49341

摘要： A method for creating a platform cooling passage in a turbine rotor blade, wherein the turbine rotor blade comprises a platform at an interface between an airfoil and a root, wherein the platform includes a platform topside along an outboard surface. The method may include the steps of forming a recessed area along the platform topside; forming a coverplate; and affixing the coverplate to the platform topside. The coverplate may be configured to correspond to the shape of the recessed area such that, when affixed to the platform topside in a desired manner, the coverplate substantially encloses the recessed area to form the platform cooling passage therein.

摘要翻译： 一种用于在涡轮机转子叶片中产生平台冷却通道的方法，其中所述涡轮机转子叶片包括在翼型件和根部之间的界面处的平台，其中所述平台包括沿着外侧表面的顶部平台。 该方法可以包括以下步骤：沿着平台顶部形成凹陷区域; 形成盖板; 并将盖板固定在平台的顶部。 盖板可以被构造成对应于凹陷区域的形状，使得当以期望的方式固定到平台顶部时，盖板基本上封闭凹陷区域以在其中形成平台冷却通道。

公开(公告)号：US20120328451A1

公开(公告)日：2012-12-27

申请号：US13169142

申请日：2011-06-27

申请人： Jonathan Matthew Lomas ,  Mark Lawrence Hunt

发明人： Jonathan Matthew Lomas ,  Mark Lawrence Hunt

IPC分类号： F01D5/18 ,  B23P15/02

CPC分类号： F01D5/187 ,  F05D2230/10 ,  F05D2240/81 ,  F05D2250/185 ,  F05D2250/294 ,  F05D2260/202 ,  F05D2260/22141 ,  Y02T50/676 ,  Y10T29/49341

摘要： A method for creating a platform cooling passage in a turbine rotor blade, wherein the turbine rotor blade comprises a platform at an interface between an airfoil and a root, wherein the platform includes a platform topside along an outboard surface. The method may include the steps of forming a recessed area along the platform topside; forming a coverplate; and affixing the coverplate to the platform topside. The coverplate may be configured to correspond to the shape of the recessed area such that, when affixed to the platform topside in a desired manner, the coverplate substantially encloses the recessed area to form the platform cooling passage therein.

摘要翻译： 一种用于在涡轮机转子叶片中产生平台冷却通道的方法，其中所述涡轮机转子叶片包括在翼型件和根部之间的界面处的平台，其中所述平台包括沿着外侧表面的顶部平台。 该方法可以包括以下步骤：沿着平台顶部形成凹陷区域; 形成盖板; 并将盖板固定在平台的顶部。 盖板可以被构造成对应于凹陷区域的形状，使得当以期望的方式固定到平台顶部时，盖板基本上封闭凹陷区域以在其中形成平台冷却通道。

公开(公告)号：US20130336801A1

公开(公告)日：2013-12-19

申请号：US13524026

申请日：2012-06-15

申请人： Sheo Narain Giri ,  Harish Bommanakatte ,  Mohankumar Banakar ,  John David Ward, JR. ,  Jonathan Matthew Lomas

发明人： Sheo Narain Giri ,  Harish Bommanakatte ,  Mohankumar Banakar ,  John David Ward, JR. ,  Jonathan Matthew Lomas

IPC分类号： F01D5/14

CPC分类号： F01D5/143 ,  F01D5/147 ,  F05D2240/80

摘要： A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform.

摘要翻译： 涡轮机的旋转翼型部件，其中部件具有在部件的翼展方向上对齐的翼型，柄以及横向于翼展方向定向的平台。 平台具有邻近翼型的外径向表面，以及限定在其外径向表面中的至少一个凹陷区域。 凹陷区域从包含在凹陷区域的上游和下游的外部径向表面的部分的平台平面相对于翼展方向延伸。 凹陷区域与平台的端壁邻接并从其向翼型延伸。 凹陷区域限定了边界由平台平面包围的表面形状，并且具有从端壁向翼型延伸的轮廓形状。 凹陷区域的尺寸和形状可以增加平台的刚度。

公开(公告)号：US09033669B2

公开(公告)日：2015-05-19

申请号：US13524026

申请日：2012-06-15

申请人： Sheo Narain Giri ,  Harish Bommanakatte ,  Mohankumar Banakar ,  John David Ward, Jr. ,  Jonathan Matthew Lomas

发明人： Sheo Narain Giri ,  Harish Bommanakatte ,  Mohankumar Banakar ,  John David Ward, Jr. ,  Jonathan Matthew Lomas

IPC分类号： F01D5/14

CPC分类号： F01D5/143 ,  F01D5/147 ,  F05D2240/80

摘要： A rotating airfoil component of a turbomachine, in which the component has an airfoil aligned in a spanwise direction of the component, a shank, and a platform therebetween oriented transverse to the spanwise direction. The platform has an outer radial surface adjacent the airfoil, and at least one recessed region defined in its outer radial surface. The recessed region extends opposite the spanwise direction from a platform plane that contains portions of the outer radial surface that are upstream and downstream from the recessed region. The recessed region is contiguous with an end wall of the platform and extends therefrom toward the airfoil. The recessed region defines a surface shape whose boundary is contained by the platform plane, and has a profile shape that extends from the end wall toward the airfoil. The recessed region is sized and shaped to increase the stiffness of the platform.

摘要翻译： 涡轮机的旋转翼型部件，其中部件具有在部件的翼展方向上对齐的翼型，柄以及横向于翼展方向定向的平台。 平台具有邻近翼型的外径向表面，以及限定在其外径向表面中的至少一个凹陷区域。 凹陷区域从包含在凹陷区域的上游和下游的外部径向表面的部分的平台平面相对于翼展方向延伸。 凹陷区域与平台的端壁邻接并从其向翼型延伸。 凹陷区域限定了边界由平台平面包围的表面形状，并且具有从端壁向翼型延伸的轮廓形状。 凹陷区域的尺寸和形状可以增加平台的刚度。