公开(公告)号：US20160083829A1

公开(公告)日：2016-03-24

申请号：US14493789

申请日：2014-09-23

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Thomas Robert REID ,  Jonathan Matthew LOMAS ,  Patrick Thomas WALSH ,  Lawrence Matthew LEVY ,  John Christopher LAMBERT ,  Michael Anthony DEPALMA, III

IPC: C23C4/02 ,  C23C4/12

CPC classification number: C23C4/02 ,  B05B13/0431 ,  B05D1/32 ,  C23C4/12 ,  C23C4/129 ,  C23C4/134 ,  F05D2230/30

Abstract: A coating process is provided. The coating process includes positioning a component within an enclosed coating system, the enclosed coating system including a coating apparatus, applying a first coating over at least a portion of the component, then robotically applying a mask to the component, then applying a second coating over at least the portion of the component. The component remains within the enclosed coating system throughout the process. Another process also includes removing a first coating head portion of the coating apparatus after applying the first coating and replacing the first coating head portion with a masking head portion, then removing the masking head portion after robotically applying the mask to the component and replacing the masking head portion with a second coating head portion.

Abstract translation: 提供涂布工艺。 涂覆方法包括将组分定位在封闭的涂层体系内，封闭的涂层系统包括涂覆装置，在部件的至少一部分上施加第一涂层，然后在组件上机械地施加掩模，然后施加第二涂层 至少部分组件。 在整个过程中，组分保持在封闭的涂层体系内。 另一方法还包括在施加第一涂层之后去除涂覆装置的第一涂覆头部分，并用掩模头部分代替第一涂覆头部分，然后在机器上将掩模施加到部件上并取代掩模之后去除掩蔽头部部分 头部具有第二涂覆头部。

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。