Siemens Energy, Inc.

Other

James A Yarbrough

Somesh J Ghunakikar

Petya M Georgieva

Mark A Garcia

Atul L Navale

Brandon W Shinn

Ivan F Oliver Vargas

Steven Valadez

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 pre-sintered preform () and a repair process () utilizing the pre-sintered preform () are disclosed, each of which result in a brazement () comprising a replacement protective coating () deposited on a component surface (). The protective coating () exhibits excellent temperature and oxidation resistance, improved adhesion to superalloy surfaces, and reduced depletion over a service life of the associated component ().

Pre-sintered preform for repair of service run gas turbine components

A helmet training aid for obscuring the vision of a user. The helmet training aid includes a panel having a pair of distal ends securely affixed to a pair of opposing blinders. A fastener is secured at a lower end of each blinder, wherein the fastener removably secures each blinder to an opposing side of a helmet such that an upper end of each blinder covers an open portion of the helmet therebetween a brim and a cage of the helmet. The panel contains one or more fasteners on a first surface that removably secures to the cage of the helmet. In an alternative embodiment, opposing sidewalls of the blinders flare outwardly from the lower end to the upper end, the fastener on each blinder is secured to a protrusion at the lower end, and the panel is made of a mesh material.

Helmet training aid

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 multi-component braze filler alloy comprising at least 70% by weight MarM509A superalloy with the remainder MarM509B superalloy is diffusion brazed to a CM247 alloy base substrate, such as a gas turbine blade or vane. It is shown that generally higher braze temperatures lead to improved results including the possibility of re-welding such a brazed component, resulting in a re-repaired brazed component capable of continued commercial service.

Braze alloy compositions and brazing methods for superalloys

A multi-component braze filler alloy comprising 60-70% by weight CM247 superalloy and BRB braze alloy is diffusion brazed to a CM247 alloy base substrate, such as a gas turbine blade or vane. The substrate/braze interface may be subsequently weld-repaired without de-melting and migrating the braze alloy from the interface. The weld zone and surrounding area are solidification crack resistant. After the alloy composition is brazed to the base substrate the component may be returned to service. Thereafter the component remains repairable by welding or re-brazing, if needed to correct future in-service defects.

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Spring, TX, United States of America

James A Yarbrough