公开(公告)号：US09574447B2

公开(公告)日：2017-02-21

申请号：US14023568

申请日：2013-09-11

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Christopher Edward Thompson ,  John David Ward ,  James Ryan Connor ,  Mark Lawrence Hunt ,  Blake Allen Fulton

IPC: F01D5/00 ,  F01D5/14 ,  B23P6/00

CPC classification number: F01D5/14 ,  B23P6/005 ,  F01D5/005 ,  Y10T29/49734

Abstract: A modification process and modified article are disclosed. The modification process includes locating an area in an article, removing the area by machining to form a machined region, inserting a modification material into the machined region, securing the modification material to the article, machining the modification material flush with a geometry of the article, and applying a coating over at least a portion of the article. Another modification process includes locating an area under a suction side leading edge tip shroud fillet of an airfoil, removing the area by machining to form a hole, inserting a modification material having improved material properties as compared to an original base material into the hole, securing the modification material in place, machining the modification material and the airfoil to form a new fillet contour, and applying a coating over at least a portion of the airfoil. Also disclosed is the modified article.

Abstract translation: 公开了修改过程和修改的文章。 修改过程包括将制品中的区域定位，通过机加工去除区域以形成机加工区域，将改性材料插入加工区域，将改性材料固定到制品上，用制品的几何形状加工改性材料 ，并且在所述制品的至少一部分上涂覆涂层。 另一种改进方法包括将机翼的吸力侧前缘尖端护罩圆角下方的区域定位，通过加工去除该区域以形成孔，将与原始基底材料相比具有改善的材料特性的改性材料插入到孔中，固定 所述改性材料就位，加工所述改性材料和所述翼型件以形成新的圆角轮廓，以及在所述翼型的至少一部分上施加涂层。 还公开了修改的文章。

公开(公告)号：US20160362988A1

公开(公告)日：2016-12-15

申请号：US15245985

申请日：2016-08-24

Applicant: General Electric Company

Inventor： John David Ward ,  Kelvin Rono Aaron ,  James Ryan Connor ,  Melbourne James Myers ,  Brad Wilson VanTassel

IPC: F01D5/22

CPC classification number: F01D5/225 ,  F01D5/005 ,  F05D2220/32 ,  F05D2230/10 ,  F05D2230/50 ,  F05D2230/80 ,  F05D2260/94 ,  F05D2270/332 ,  Y10T29/49234 ,  Y10T83/04

Abstract: A method is provided for modifying an airfoil shroud located at a tip of a blade of an airfoil, the airfoil shroud having a first end edge, a second end edge, a leading edge, and a trailing edge. The method includes locating a reference location in the first end edge of the airfoil shroud, the reference location including a portion of a seal rail extending circumferentially from a radially outer surface of the airfoil shroud, and a fillet extending from the radially outer surface and positioned directly adjacent to the seal rail. The method further includes forming a relief cut in the seal rail and fillet without performing a weld process on the airfoil shroud to remove the reference location, and installing the airfoil shroud in a turbomachine directly following forming the relief cut, wherein modifying the airfoil shroud is complete following forming the relief cut.

Abstract translation: 提供了一种用于改变位于翼型件的叶片的尖端处的翼型护罩的方法，翼型护罩具有第一端边缘，第二端边缘，前缘和后缘。 该方法包括将参考位置定位在翼型护罩的第一端边缘中，参考位置包括从翼型护罩的径向外表面周向延伸的密封轨道的一部分，以及从径向外表面延伸的圆角， 直接靠近密封轨。 该方法还包括在密封导轨和圆角上形成浮雕切口，而不对翼型护罩进行焊接处理以去除参考位置，并且在形成浮雕切割之后将翼型件护罩直接安装在涡轮机中，其中修改翼型护罩是 完成以后形成救济切割。