Non-Destructive Evaluation of Thermal Barrier Coating Damage and Molten Sand Deposits on Gas Turbine Engine Components via Scanning Acoustic Microscopy

2018 ◽  
Author(s):  
Andy Nieto ◽  
Anindya Ghoshal ◽  
Michael J. Walock ◽  
Muthuvel Murugan
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Acoustic Microscopy ◽  
Thermal Barrier ◽  
Scanning Acoustic Microscopy ◽  
Turbine Engine ◽  
Non Destructive Evaluation ◽  
Barrier Coating ◽  
Engine Components ◽  
Non Destructive

scholarly journals Effect of Fouling, Thermal Barrier Coating Degradation and Film Cooling Holes Blockage on Gas Turbine Engine Creep Life

Procedia CIRP ◽  
2015 ◽  
Vol 38 ◽  
pp. 228-233 ◽  
Author(s):  
Ebi A. Ogiriki ◽  
Yiguang G. Li ◽  
Theoklis Nikolaidis ◽  
ThankGod E. Isaiah ◽  
Gowon Sule
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Film Cooling ◽  
Gas Turbine Engine ◽  
Thermal Barrier ◽  
Creep Life ◽  
Coating Degradation ◽  
Turbine Engine ◽  
Barrier Coating ◽  
Film Cooling Holes

Thermal Analysis & Studies on Low Pressure Gas Turbine Blades Coated with Yitria Stabilized Zirconia (YSZ)

2012 ◽  
Vol 622-623 ◽  
pp. 1596-1600
Author(s):  
N. Rajasekar ◽  
P.M. Shivraj ◽  
C.J. Thomas Renald ◽  
K. Karthick ◽  
M.P. Tamizhmani
Keyword(s):  
Gas Turbine ◽  
Turbine Blades ◽  
Thermal Barrier ◽  
Stabilized Zirconia ◽  
Turbine Engine ◽  
Gas Turbine Blades ◽  
Barrier Coating ◽  
Potential Applications ◽  
Plasma Sprayed ◽  
Engine Components

The thermal barrier coatings have many potential applications in the protection of gas turbine engine components, essentially the turbine blades.In this study micro analysis was carried out on Yitria Stabilized Zirconia(YSZ) coated turbine blades and the results are compared with the uncoated blades.We have used the atmosphere plasma sprayed thermal barrier coating with a thickness of 0.25mm to withstand the high temperature of about 2000 C.We observed that by increasing the thermal coating thickness of about 0.25mm cause to increase 50% of the surface temperature of the turbine blade,which in turn increased the aero engine thrust.

scholarly journals Progress in Novel Electrodeposited Bond Coats for Thermal Barrier Coating Systems

Materials ◽  
2021 ◽  
Vol 14 (15) ◽  
pp. 4214
Author(s):  
Kranthi Kumar Maniam ◽  
Shiladitya Paul
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Gas Turbines ◽  
High Performance ◽  
Turbine Engines ◽  
Thermal Barrier ◽  
Gas Turbine Engines ◽  
Potential Cost ◽  
Bond Coats ◽  
Barrier Coating

The increased demand for high performance gas turbine engines has resulted in a continuous search for new base materials and coatings. With the significant developments in nickel-based superalloys, the quest for developments related to thermal barrier coating (TBC) systems is increasing rapidly and is considered a key area of research. Of key importance are the processing routes that can provide the required coating properties when applied on engine components with complex shapes, such as turbine vanes, blades, etc. Despite significant research and development in the coating systems, the scope of electrodeposition as a potential alternative to the conventional methods of producing bond coats has only been realised to a limited extent. Additionally, their effectiveness in prolonging the alloys’ lifetime is not well understood. This review summarises the work on electrodeposition as a coating development method for application in high temperature alloys for gas turbine engines and discusses the progress in the coatings that combine electrodeposition and other processes to achieve desired bond coats. The overall aim of this review is to emphasise the role of electrodeposition as a potential cost-effective alternative to produce bond coats. Besides, the developments in the electrodeposition of aluminium from ionic liquids for potential applications in gas turbines and the nuclear sector, as well as cost considerations and future challenges, are reviewed with the crucial raw materials’ current and future savings scenarios in mind.

scholarly journals Evaluation of Impact Properties of Thermal Barrier Coating on Gas Turbine Components.

2000 ◽  
Vol 66 (650) ◽  
pp. 1841-1846
Author(s):  
Hiroshige ITOH ◽  
Kazuhiro SAITOH ◽  
Takahiro KUBO ◽  
Masashi TAKAHASHI ◽  
Hideo KASHIWAYA
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Thermal Barrier ◽  
Impact Properties ◽  
Barrier Coating

Field Evaluation of 2CaO-SiO2-CaO-ZrO2 Thermal Barrier Coating on Gas Turbine Vanes

1997 ◽  
Author(s):  
N. Mifune ◽  
Y. Harada ◽  
H. Taira ◽  
S. Mishima
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Thermal Barrier Coatings ◽  
Field Evaluation ◽  
Thermal Barrier ◽  
Barrier Coatings ◽  
Thermal Change ◽  
Barrier Coating ◽  
Turbine Vanes ◽  
Higher Temperature

Abstract Higher-temperature operation in a gas turbine has urged development of heat-resistant coatings and thermal barrier coatings. We have developed a 2CaO-SiO2-CaO-ZrO2 based thermal barrier coating. This coating should effectively prevent separation of the coating by relieving the shear stress generated due to thermal change of environment between layers with dissimilar properties. The coating was applied to stationary vanes of an actual gas turbine in a 25,000-hour test. This paper describes the results of the field test.

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