Siemens Aktiengesellschaft

Other

Beate Heimberg

Michael Ott

Werner Stamm

Wolfram Beele

Ulrich Bast

Peter Greil

Fritz Aldinger

Karl Kempter

Thomas Haubold

Knut Halberstadt

Michael Hoffmann

Dirk Goldschmidt

Rainer Nies

Jens Birkner

Walter David

Axel Endriss

Chu-Wan Hong

Hans J Seifert

Wolfgang Hermann

Rudolf Gensler

Boris Bublath

Bora Kocdemir

Arne Grassmann

Jörg SCHÜRHOFF

The invention relates to a method for repairing a damaged and/or aged component of a turbomachine, which is made at least in part of a ceramic composite material. The aim of the invention is to create a method which allows the downtime of the turbomachine caused by damaged components to be reduced while making it possible to repair damaged components. The abovementioned aim is achieved by a generic method for repairing a damaged component () of a turbomachine made of a ceramic composite material (), comprising the following steps: the joint of the component is dissolved; the matrix () is extracted and/or the component is machined; infiltration to restore and/or renew the ceramic matrix () of the component; and the joint is re-established.

Method for repairing a component of a turbomachine

The invention relates to a product ( ), particularly a gas turbine blade that can be exposed to a hot aggressive gas ( ). The product ( ) has a metallic basic body ( ), which is provided with a thermal barrier coating ( ) having a spinel of the composition AB O .

Product, especially a gas turbine component, with a ceramic heat insulating layer

An article that is particularly well suited for use as a gas turbine engine component has a metallic substrate and a ceramic thermal barrier layer including a mixed metal oxide system comprising a compound selected from the group consisting of (i) a lanthanum aluminate and (ii) a calcium zirconate, the calcium in which is partially replaced by at least one calcium-substitute element, such as strontium (Sr) or barium (Ba). In addition, the lanthanum in the lanthanum aluminate can be partially replaced by a lanthanum-substitute element from the lanthanide group, particularly gadolinium (Gd). A process for producing such an article comprises providing a pre-reacted mixed metal oxide system as described above and applying it to the substrate by plasma spraying or an evaporation coating process.

Process for producing a ceramic thermal barrier layer for gas turbine engine component

Ceramic thermal barrier layer for gas turbine engine component

Protective layer system for gas turbine engine component

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Berlin, Germany

Beate Heimberg