公开(公告)号：US20140193664A1

公开(公告)日：2014-07-10

申请号：US13735342

申请日：2013-01-07

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Christopher Edward THOMPSON ,  John D. WARD, JR. ,  Mark Lawrence HUNT ,  Jonathan Matthew LOMAS ,  Gareth William David LEWIS ,  Michael Anthony DEPALMA, III

IPC: F01D5/28

CPC classification number: F01D5/288 ,  F01D5/005 ,  F05D2230/31 ,  Y10T428/12618

Abstract: Recoating process and recoated turbine blade are disclosed. The recoating process includes providing a coated turbine blade, then removing a portion of the thermal barrier coating system to form a partially-stripped turbine blade, then applying a bond recoat to the stripped region of the partially-stripped turbine blade; and then applying a thermal barrier recoat to the bond recoat to form a recoated turbine blade. The recoated turbine blade comprises the bond coating portion abutting the bond recoat, the thermal barrier coating portion abutting the thermal barrier recoat, and the stepped configuration. The coated turbine blade has a thermal barrier coating system positioned on a substrate. The partially-stripped turbine blade has a stripped region, a bond coating portion, a thermal barrier coating portion, and a stepped configuration.

Abstract translation: 公开了再循环工艺和重新涂覆的涡轮叶片。 重涂过程包括提供涂覆的涡轮叶片，然后移除热障涂层系统的一部分以形成部分剥离的涡轮叶片，然后将粘合重涂施加到部分剥离的涡轮叶片的剥离区域; 然后将热屏蔽涂层施加到粘结重涂层以形成重新涂覆的涡轮叶片。 重新包覆的涡轮机叶片包括邻接粘结重涂的粘合涂层部分，邻接热障涂层的热障涂层部分和阶梯状构造。 涂覆的涡轮叶片具有定位在基底上的热障涂层系统。 部分剥离的涡轮叶片具有剥离区域，粘合涂覆部分，热障涂层部分和阶梯构造。