The project was carried out by MTU, Rolls-Royce and Siemens as industrial partners and FZ-Juelich, DLR and DECHEMA as institutes for the purpose of developing a life model for monocrystalline gas turbine blades with metal coatings. This model was to provide reliable information on the life of the ceramic and coupling agent layers. This report describes the activities of the Karl-Winnacker Institute of DECHEMA e.V.: Isothermal oxidation experiments were carried out in the laboratory at 950-1100 degrees centigrade, followed by a characterisation of the oxidation characteristics on the basis of metallographic sections. Particular interest was taken in the development of the TGO (thermally grown oxide) layers, aluminium depletion in the bond co...
Environmental protection and cost effectiveness lead to the demand to increase of the efficiency of ...
Co-encadrement de la thèse : Cécilie DuhamelThèse confidentielle jusqu'au 1er février 2013A thermal ...
Gas turbines operate at combustion chamber temperatures up to 1400°C. Therefore the blades and the c...
Materials for front stage blades and vanes of land based gas turbine and aero engines must be resist...
Temperatures in modern low pressure turbines of aero engines have increased to a level which formerl...
Usual thermal barrier coating in Gas Turbine are made of a Bond-Coat (MCrAlY) and a ceramic layer (y...
Die Oxidation an Bondcoats in Waermedaemmschichtsystemen waehrend des Betriebes ist eines der zentra...
The thrust and efficiency of turbine engines are directly related to the operating temperature. In o...
This study aims to model lifetime of thermal barrier coating (TBC) used on aircraft turbine blades. ...
Promising ferritic/martensitic and austenitic materials were tested for oxidation resistance at temp...
In the context of the research project, long-term and LCF tests were carried out on uncoated and coa...
Gas turbine materials exposed to extreme high temperature require protective coatings. To design rel...
The special research area 339 'Blades and discs in gas turbines, behaviour of material and component...
Gas turbine materials exposed to extreme high temperature require protective coatings. To design rel...
Ziel dieser Arbeit war die Untersuchung von Hochtemperaturoxidationsvorgaengen vor allem mit in situ...
Environmental protection and cost effectiveness lead to the demand to increase of the efficiency of ...
Co-encadrement de la thèse : Cécilie DuhamelThèse confidentielle jusqu'au 1er février 2013A thermal ...
Gas turbines operate at combustion chamber temperatures up to 1400°C. Therefore the blades and the c...
Materials for front stage blades and vanes of land based gas turbine and aero engines must be resist...
Temperatures in modern low pressure turbines of aero engines have increased to a level which formerl...
Usual thermal barrier coating in Gas Turbine are made of a Bond-Coat (MCrAlY) and a ceramic layer (y...
Die Oxidation an Bondcoats in Waermedaemmschichtsystemen waehrend des Betriebes ist eines der zentra...
The thrust and efficiency of turbine engines are directly related to the operating temperature. In o...
This study aims to model lifetime of thermal barrier coating (TBC) used on aircraft turbine blades. ...
Promising ferritic/martensitic and austenitic materials were tested for oxidation resistance at temp...
In the context of the research project, long-term and LCF tests were carried out on uncoated and coa...
Gas turbine materials exposed to extreme high temperature require protective coatings. To design rel...
The special research area 339 'Blades and discs in gas turbines, behaviour of material and component...
Gas turbine materials exposed to extreme high temperature require protective coatings. To design rel...
Ziel dieser Arbeit war die Untersuchung von Hochtemperaturoxidationsvorgaengen vor allem mit in situ...
Environmental protection and cost effectiveness lead to the demand to increase of the efficiency of ...
Co-encadrement de la thèse : Cécilie DuhamelThèse confidentielle jusqu'au 1er février 2013A thermal ...
Gas turbines operate at combustion chamber temperatures up to 1400°C. Therefore the blades and the c...