Siemens Energy, Inc.

Atul L Navale

Ivan F Oliver Vargas

Gerald Joseph Bruck

Ahmed Kamel

James A Yarbrough

Somesh J Ghunakikar

Brandon W Shinn

A method for repairing a tip portion of a turbine component having a structural defect is provided. The method includes removing a damaged section in turbine component with a structural defect in a tip portion of the turbine component. A pre-sintered preform is provided including a first portion having a first composition and a second portion having a second composition. The pre-sintered preform is configured to mate with an upper surface of a remaining portion of the turbine component. The method also includes applying the pre-sintered preform to the upper surface, wherein the PSP comprises a superalloy material and a braze material. The PSP and the remaining portion of the turbine component are subjected to a brazing process to melt the braze material and fill in the structural defect.

Tip repair of a turbine component using a composite tip boron base pre-sintered preform

A process is provided for repairing a damaged portion of a gas turbine blade comprising: providing a preform comprising a low-melt alloy material and a base alloy material; locating the preform on the gas turbine engine blade damaged portion; and heat treating the preform and the blade such that the preform is brazed to the blade.

Pre-sintered preform repair of turbine blades

A method, including: replacing an original blade shelf () of a gas turbine engine blade () with a new blade shelf () that is located closer to a base () of the blade than the original blade shelf; adding mass to the blade until a mass of the blade with the new blade shelf is greater than a mass of the blade with the original blade shelf in order to maintain a same contribution by the blade with the new blade shelf as a contribution by the blade with the original blade shelf to a dynamic balance of a rotor arrangement.

Method for repairing a gas turbine engine blade tip

A coating arrangement (), including: a layer () of bond coat material (); and a light-transmissive thermal barrier coating (TBC) mesh () having a TBC material () and secured in position relative to the layer of bond coat material. The coating arrangement may be positioned over a superalloy substrate material () and melted with a laser beam () to metallurgically bond the thermal barrier coating onto the substrate.

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Houston, TX, United States of America

Atul L Navale