Man Diesel & Turbo Se

Man Turbo Ag

Ghh Borsig Turbomaschinen Gmbh

Diffusion Alloys Limited

Sharad Chandra

Norbert Czech

Markus Beukenberg

Roland Herzog

Berthold Ellermann

Heinz Gathmann

John Smith

Werner Schnieders

A hot-gas conducting component for a flow machine has a nickel-base wrought alloy as structural material and a hot gas-side lining made from the group of iron-chromium-aluminum-yttrium alloys and a flow machine having a component of this type.

Hot gas-guided component of a turbomachine

Disclosed is a heat-insulating protective layer for a component located within the hot gas zone of a gas turbine. Said protective layer is composed of an adhesive layer, a diffusion layer, and a ceramic layer which is applied to the high temperature-resistant basic metal of the component. The adhesive layer comprises a metal alloy [MCrAlY (M=Ni, Co)] containing Ni, Co, Cr, Al, Y, the diffusion layer is produced by calorizing the adhesive layer, and the ceramic layer is composed of ZrO2 which is partially stabilized by means of yttrium oxide. One or several chemical metal elements that have a large atomic diameter and are selected among the group comprising Re, W, Si, Hf, and/or Ta are alloyed to the material of the adhesive layer. The adhesive layer has the following chemical composition after being applied: Co 15 to 30 percent, Cr 15 to 25 percent, Al 6 to 13 percent, Y 0.2 to 0.7 percent, Re up to 5 percent, W up to 5 percent, Si up to 3 percent, Hf up to 3 percent, Ta up to 5 percent, the remainder being composed of Ni.

Heat-insulating protective layer for a component located within the hot gas zone of a gas turbine

A method is provided for coating a hollow, internally cooled blade () of a gas turbine, in which method an outer coating () comprising an MCrAlY-based bonding layer () and a ceramic thermal barrier layer () of zirconium oxide is applied to the base material () of the blade () on the outer side of the blade () and an inner coating () comprising a Cr diffusion layer () is applied to the base material () of the blade () on the inner side of the blade (). The MCrAlY-based bonding layer () is thereby applied to the finished blade (). At the same time, along with the inner coating (), the Cr diffusion layer () is also applied to the MCrAlY-based bonding layer () of the outer coating () by chemical vapor deposition. Subsequently, an Al diffusion layer () and an outer brittle Al build-up layer are applied by chemical vapor deposition to the bonding layer () coated with the Cr diffusion layer (). After that, the outer brittle Al build-up layer is removed by an abrasive treatment and the ceramic thermal barrier layer () is applied to the Al diffusion layer ().

Method for coating a blade and blade of a gas turbine

This invention relates to the simultaneous treatment of the internal and external surfaces of turbine blades or vanes. In particular it provides a process for coating an external and an internal surface of a turbine blade or vane with aluminium and chromium, respectively, at substantially the same time. The process comprises the following steps (i) and (ii) in either order: (i) applying to the external surface an aluminising compound comprising aluminium, a moderator, an energiser and a diluent; and (ii) applying to the internal surface a chromising compound comprising chromium, an energiser and a diluent. These steps are followed by (iii) heating the turbine blade or vane to form an aluminium layer on the external surface and a chromium layer on the internal surface. The invention also provides a suitable aluminising compound and a chromising compound per se.

Coatings for turbine blades

To protect a base metal layer () against high-temperature corrosion and high-temperature erosion, an adhesive layer () based on MCrAlY is applied to the base metal layer (). The adhesive layer () is coated with an Al diffusion layer () by alitizing. The diffusion layer () is subjected to an abrasive treatment, so that the outer built-up layer () on the diffusion layer () prepared by alitizing is removed by the abrasive treatment. A ceramic heat insulation layer () consisting of zirconium oxide, which is partially stabilized by yttrium oxide, is applied to the diffusion layer () thus treated.

Process for applying a protective layer

A hot gas-carrying gas collection pipe (,) of a gas turbine, which is arranged between the combustion chamber and the turbine blades. The gas collection pipe (,) has two inlet openings (,) for receiving the hot gas. The outlet comprises the flanges (,), which are connected to the turbine. The material of the gas collection pipe (,) is a high-temperature- and corrosion-resistant base metal (,) with a high-temperature corrosion and oxidation coating (,) applied to both the inside and the outside of the base metal (,). In the area of the inner cone (,), an HTCO coating (,) is applied to the base metal (,) on one side and a thermal barrier coating (,) is applied on the opposite side.

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Oberhausen, Germany

Sharad Chandra