公开(公告)号：US20170080458A1

公开(公告)日：2017-03-23

申请号：US14973935

申请日：2015-12-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Surinder Singh PABLA ,  Richard Todd EVERHART

IPC: B05D5/00 ,  F23R3/00 ,  C09D5/08

Abstract: A treatment composition is disclosed including a carrier and a sacrificial oxide-forming material suspended within the carrier. The sacrificial oxide-forming material is selected from the group consisting of tin oxide, magnesium oxide, antimony pentaoxide, and combinations thereof. A treatment process for a gas turbine component including an abradable ceramic coating is disclosed. The process includes contacting the abradable ceramic coating with the treatment composition. The sacrificial oxide-forming material is infused into the abradable ceramic coating to form sacrificial oxide-forming deposits within the abradable ceramic coating. A rejuvenation process is disclosed including contacting the hot gas path surface of a gas turbine component with a rinse composition comprising water and the treatment composition to form the sacrificial oxide-forming deposits within the abradable ceramic coating.

公开(公告)号：US20200165923A1

公开(公告)日：2020-05-28

申请号：US16608214

申请日：2017-04-25

Applicant: General Electric Company

Inventor： Jianzhi ZHAO ,  Chuan LIN ,  Shizhong WANG ,  Mihir Kumar LAL ,  Richard Todd EVERHART

IPC: F01D5/28 ,  C04B41/50 ,  C01B33/20 ,  C09D5/00 ,  C09D1/00 ,  C04B41/52 ,  F01D25/08 ,  C09D5/08 ,  C04B41/87 ,  C04B41/89 ,  C01G25/00 ,  C23C4/11 ,  C23C4/134

Abstract: A gas turbine component includes a substrate and a corrosion resistant layer coupled to the substrate. The corrosion resistant layer includes zirconium silicate and is configured to protect the substrate from exposure to a vanadium corrodent.

公开(公告)号：US20170081964A1

公开(公告)日：2017-03-23

申请号：US14857912

申请日：2015-09-18

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Richard Todd EVERHART

IPC: F01D5/28 ,  F23R3/42 ,  F23R3/00 ,  C09D5/08 ,  F01D9/04

CPC classification number: F01D5/288 ,  C09D5/084 ,  C23C8/42 ,  C23C8/80 ,  C23C24/08 ,  C23C28/3215 ,  C23C28/345 ,  C23C28/3455 ,  F01D9/041 ,  F05D2220/32 ,  F05D2230/31 ,  F05D2230/90 ,  F05D2240/128 ,  F05D2240/30 ,  F05D2240/35 ,  F05D2300/21 ,  F05D2300/611 ,  F23R3/002 ,  F23R3/42

Abstract: A treatment process for a gas turbine component comprising a bond coating and a ceramic coating, an oxide-forming treatment composition, and a treated component are disclosed. The ceramic coating is contacted with a treatment composition. The treatment composition includes a carrier and a particulate oxide-forming material suspended within the carrier. The particulate oxide-forming material is one or more of yttria oxide, antimony, or tin oxide. The treatment composition is heated to form an oxide overlay coating on the ceramic coating. The treated component includes a ceramic coating and one or both of a corrosion inhibitor and an oxide formed by an oxide-forming treatment composition having the corrosion inhibitor.