公开(公告)号：US11691223B2

公开(公告)日：2023-07-04

申请号：US17881224

申请日：2022-08-04

Applicant: Raytheon Technologies Corporation

Inventor： Henry H. Thayer ,  Dmitri Novikov ,  Robert J. Meehan ,  Bartolomeo Palmieri

IPC: B23K26/362 ,  B23K26/0622 ,  B23K26/146 ,  B23K26/402 ,  B23K31/10 ,  F01D5/28 ,  B23K101/34

CPC classification number: B23K26/362 ,  B23K26/0622 ,  B23K26/146 ,  B23K26/402 ,  B23K31/10 ,  F01D5/286 ,  B23K2101/35 ,  F05D2230/13

Abstract: A method for stripping ceramic from a component includes applying a liquid to a ceramic coating of an outer surface of the component. The method also includes directing a plurality of laser pulses at the ceramic coating with the applied liquid in order to spall the ceramic coating from the component.

公开(公告)号：US20220298645A1

公开(公告)日：2022-09-22

申请号：US17569102

申请日：2022-01-05

Applicant: Raytheon Technologies Corporation

Inventor： Henry H. Thayer ,  Dmitri Novikov ,  David Ulrich Furrer

IPC: C23C28/00 ,  C23C16/02 ,  C23C14/02

Abstract: A process for forming a thermal barrier coating on a part comprising depositing an aluminum containing bond coat on the part, the bond coat comprising a surface; cleaning the surface to remove oxides and debris from the surface of the bond coat; forming a gamma phase layer proximate the surface of the bond coat; forming an aluminum oxide layer on the surface of the bond coat; and depositing a ceramic topcoat on the aluminum oxide layer on the bond coat.

公开(公告)号：US11781436B2

公开(公告)日：2023-10-10

申请号：US17571202

申请日：2022-01-07

Applicant: Raytheon Technologies Corporation

Inventor： Daniel A. Bales ,  Dmitri Novikov ,  Robert C. Dolan ,  Eric W. Malmborg ,  Steven T. Gordon

IPC: F01D5/30 ,  B23K1/00 ,  F01D5/14 ,  F04D29/38 ,  B23K101/00

CPC classification number: F01D5/3061 ,  B23K1/0018 ,  F01D5/147 ,  F04D29/388 ,  B23K2101/001 ,  F05D2230/232 ,  F05D2240/301

Abstract: An airfoil for a gas turbine engine includes a first portion joined to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section. The airfoil section includes an airfoil body that extends between leading and trailing edges in a chordwise direction, between pressure and suction sides separated in a thickness direction, and from the root section to a tip portion in a spanwise direction. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib that bounds a respective pocket within a perimeter of the recessed region. The recessed region and the at least one rib are dimensioned to extend across the interface. A cover skin is coupled to the airfoil body along the at least one rib to enclose the recessed region.

公开(公告)号：US20220127966A1

公开(公告)日：2022-04-28

申请号：US17571202

申请日：2022-01-07

Applicant: Raytheon Technologies Corporation

Inventor： Daniel A. Bales ,  Dmitri Novikov ,  Robert C. Dolan ,  Eric W. Malmborg ,  Steven T. Gordon

IPC: F01D5/30 ,  B23K1/00 ,  F01D5/14 ,  F04D29/38

Abstract: An airfoil for a gas turbine engine includes a first portion joined to a second portion along an interface such that at least the first portion establishes an airfoil section and the second portion establishes a root section. The airfoil section includes an airfoil body that extends between leading and trailing edges in a chordwise direction, between pressure and suction sides separated in a thickness direction, and from the root section to a tip portion in a spanwise direction. A recessed region extends inwardly from at least one of the pressure and suction sides. The airfoil body includes at least one rib that bounds a respective pocket within a perimeter of the recessed region. The recessed region and the at least one rib are dimensioned to extend across the interface. A cover skin is coupled to the airfoil body along the at least one rib to enclose the recessed region.