Chamber Life Time Evaluation of a Regeneratively Cooled Thrust Chamber with Thermal Barrier Coatings

2017 ◽  
Author(s):  
Hiroaki Amakawa ◽  
Miki Nishimoto ◽  
Hideyo Negishi ◽  
Toshiya Kimura ◽  
Shin-ichi Moriya ◽  
...  
Keyword(s):  
Thermal Barrier Coatings ◽  
Life Time ◽  
Thermal Barrier ◽  
Barrier Coatings ◽  
Thrust Chamber ◽  
Time Evaluation

Life time of new SYSZ thermal barrier coatings produced by plasma spraying method under thermal shock test and high temperature treatment

2014 ◽  
Vol 40 (1) ◽  
pp. 1405-1414 ◽  
Author(s):  
Mohammad Reza Loghman-Estarki ◽  
Reza Shoja Razavi ◽  
Hossein Edris ◽  
Mousa pourbafrany ◽  
Hossein Jamali ◽  
...  
Keyword(s):  
High Temperature ◽  
Thermal Barrier Coatings ◽  
Life Time ◽  
Temperature Treatment ◽  
High Temperature Treatment ◽  
Thermal Barrier ◽  
Thermal Shock Test ◽  
Barrier Coatings ◽  
Shock Test ◽  
Spraying Method

Failure Mechanism of Pure Nickel (Ni 200/201) under Thermo-Mechanical Loading

2007 ◽  
Vol 348-349 ◽  
pp. 793-796 ◽  
Author(s):  
Hubert Koeberl ◽  
Gerhard Winter ◽  
Martin Riedler ◽  
Wilfried Eichlseder
Keyword(s):  
Cyclic Loading ◽  
Failure Mechanism ◽  
Thermal Barrier Coatings ◽  
Low Cycle Fatigue ◽  
Life Time ◽  
Damage Mechanism ◽  
Pure Nickel ◽  
Thermal Barrier ◽  
Barrier Coatings ◽  
Time Calculation

Cyclic loading of metallic engineering components at constant elevated or fluctuating temperature causes a complex evolution of damage which be can hardly be described in a unique and straightforward manner. Often the thermal behaviour of the base metals is to weak, so thermal barrier coatings were needed. Nickel is generally used for such thermal barrier coatings. Therefore it is necessary to study the thermo-mechanical fatigue (TMF) of this material. The lifetime of these coatings is very strong affected by the temperature loading in general, both described by nodal temperatures and their local gradient. The thermal cyclic loading takes place as thermo-mechanical and low cycle fatigue (LCF) damage regime. To classify the thermo-mechanical failure mechanism of pure nickel, OP (out of phase) and IP-TMF (in phase) test series were examined. The use of damage parameters like the unified energy approach make sense, a more detailed life time calculation for pure Nickel can be done by using the Neu-Sehitoglu model. Summary, thermomechanical loadings activate multiple damage mechanism. Surface embrittlement by oxidation is the major distinctive mechanism in addition to pure fatigue damage. Different lifetime approaches were tested and analysed to fulfil the requirements for the fatigue analysis of nickel made components.

A life time model for ceramic thermal barrier coatings

2003 ◽  
Vol 358 (1-2) ◽  
pp. 255-265 ◽  
Author(s):  
F. Traeger ◽  
M. Ahrens ◽  
R. Vaßen ◽  
D. Stöver
Keyword(s):  
Thermal Barrier Coatings ◽  
Life Time ◽  
Thermal Barrier ◽  
Time Model ◽  
Barrier Coatings

Characterization of thermal barrier coatings formed by electon-beam physical vapor deposition (EB-PVD)

1989 ◽  
Vol 47 ◽  
pp. 426-427
Author(s):  
Ozer Unal
Keyword(s):  
Thermal Barrier Coatings ◽  
Physical Vapor Deposition ◽  
Ceramic Coating ◽  
High Vacuum ◽  
Ceramic Coatings ◽  
High Energy ◽  
Thermal Barrier ◽  
Protective Oxide ◽  
Barrier Coatings ◽  
Energy Beam

Interest in ceramics as thermal barrier coatings for hot components of turbine engines has increased rapidly over the last decade. The primary reason for this is the significant reduction in heat load and increased chemical inertness against corrosive species with the ceramic coating materials. Among other candidates, partially-stabilized zirconia is the focus of attention mainly because ot its low thermal conductivity and high thermal expansion coefficient.The coatings were made by Garrett Turbine Engine Company. Ni-base super-alloy was used as the substrate and later a bond-coating with high Al activity was formed over it. The ceramic coatings, with a thickness of about 50 μm, were formed by EB-PVD in a high-vacuum chamber by heating the target material (ZrO2-20 w/0 Y2O3) above its evaporation temperaturef >3500 °C) with a high-energy beam and condensing the resulting vapor onto a rotating heated substrate. A heat treatment in an oxidizing environment was performed later on to form a protective oxide layer to improve the adhesion between the ceramic coating and substrate. Bulk samples were studied by utilizing a Scintag diffractometer and a JEOL JXA-840 SEM; examinations of cross-sectional thin-films of the interface region were performed in a Philips CM 30 TEM operating at 300 kV and for chemical analysis a KEVEX X-ray spectrometer (EDS) was used.

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