General Electric Technology Gmbh

Ansaldo Energia IP UK Limited

Alstom Technology Limited

Guenter Ambrosy

Matthias Hoebel

Thomas Etter

Sorin Keller

Felix Michael Reinert

Jeffrey Alan De Jonge

Michael Seemann

Daniel Beckel

Hans Bissig

Thomas Opderbecke

Tobias Schmitt

Dirk Jaekel

Stefan Schlegel

Balint Horvath

Hermann Emminger

The present relates to a method of welding in deep joints in narrow-gap geometry. The two metallic components are arranged next to each other such that there is nearly a zero gap between the two components. The step of joining two metallic components is performed in two stages, the first stage being a root weld and the second stage being a fill up weld. The root weld is completed at the joining of the two discs starting from a middle portion to a point up to which there is still a zero gap between the two discs. From the point there exists a non-zero gap between the two discs up to an outer portion. The filler gap is filled by fill up welding. During fill up welding, a filler wire is melted along with the two discs by using the first source of energy, and to fill the filler gap along with molten material of the two discs.

Method of welding in deep joints

A method for post-weld heat treatment of a without a filler material welded high strength component made of a gamma prime (&#x3b3;') strengthened superalloy can include providing the welded component, heating the welded component by applying a rapid heating-up rate in the range of 20&#xb0; C./min to 40&#xb0; C./min during the entire temperature range from room temperature (RT) up to a temperature Tof at least 1000&#xb0; C., holding the welded component at Tand then heating the component by applying a slow heating-up rate of about 5&#xb0; C./min to a final temperature T, then holding the welded component at Tfor a time tsufficient for at least partially dissolving the gamma prime phase in a weld of the welded component and also in a base material surrounding the weld, and cooling the component with a cooling rate that is greater than or equal to about 20&#xb0; C./min.

Method for post-weld heat treatment of welded components made of gamma prime strengthened superalloys

An insert element for closing an opening inside a wall of a hot gas path component of a gas turbine includes a plate like body with an opening sided surface. The surface provides at least one first area which projects beyond at least one second area of said surface which surrounds the at least one first area frame-like. The at least one first area is encompassed by a circumferential edge corresponding in form and size to the opening such that the circumferential edge and the opening contour limit a gap at least in some areas, while the at least one second area contacts directly or indirectly the wall of the hot gas path component at a rear side facing away from the hot gas path. The plate like body provides at least a first functional layer-system, providing at least one layer made of heat resistant material, defining the first area of the surface (S).

Insert element for closing an opening inside a wall of a hot gas path component of a gas turbine and method for enhancing operational behaviour of a gas turbine

A method is provided for repairing a single crystal turbine blade, which includes an airfoil with a tip having a tip cover plate, tip cooling air holes and a tip crown. The method includes removing the tip crown by manual grinding, thereby preserving the underlying tip cover plate; preparing the tip cooling air holes by manual grinding; closing said prepared tip cooling air holes by manual welding; and building-up a new tip crown by a LMF (Laser Metal Forming) process.

Method for repairing a single crystal turbine blade

Growing community of inventors

Fislisbach, Switzerland

Guenter Ambrosy