scholarly journals Development of Coating System for Gas Turbine. III. Reaction Diffusion Analysis for Interface between Ni Based Super Alloy and MCrAlY Coating.

1997 ◽  
Vol 46 (8) ◽  
pp. 927-932
Author(s):  
Yoshiyasu ITOH ◽  
Masataka TAMURA ◽  
Yasuo TAKAHASHI
Keyword(s):  
Gas Turbine ◽  
Reaction Diffusion ◽  
Coating System ◽  
Mcraly Coating ◽  
Diffusion Analysis ◽  
Super Alloy

Analysis of surface texture of Ni-based super alloy with thermal barrier coating system (TBC) for gas turbine blade

2020 ◽  
Author(s):  
Sangeetha Manimaran ◽  
Anderson Arul Gnana Dhas ◽  
Nivin Joy ◽  
K. S. Sridhar Raja ◽  
Krishnanu Saikia ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Thermal Barrier Coating ◽  
Turbine Blade ◽  
Surface Texture ◽  
Thermal Barrier ◽  
Coating System ◽  
Gas Turbine Blade ◽  
Thermal Barrier Coating System ◽  
Barrier Coating ◽  
Super Alloy

scholarly journals Failure Analysis of Gas Turbine Rotary Blade

2017 ◽  
pp. 1-6
Keyword(s):  
Finite Element ◽  
Gas Turbine ◽  
Rotor Blade ◽  
Rotor Blades ◽  
Centrifugal Forces ◽  
Analysis Software ◽  
Two Stage ◽  
Element Analysis ◽  
Finite Element Software ◽  
Super Alloy

In the present work the first stage rotor blade of a two- stage gas turbine has been analyzed for structural, thermal using ANSYS 9.0, which is a powerful Finite Element Software. In the present work, the first stage rotor blade of the gas turbine has been analyzed for the mechanical and radial elongations resulting from the tangential, axial and centrifugal forces. The gas forces namely tangential, axial were determined by constructing velocity triangles at inlet and exist of rotor blades. The rotor blade was then analyzed using ANSYS 9.0 for the temperature distribution. The material of the blade was specified as N155 but its properties were not given. This material is an iron based super alloy and structural and thermal properties at gas room and room temperatures. The turbine blade along with the groove is considered for the static, thermal, modal analysis. The first stage rotor blade of a two-stage gas turbine has been analyzed for structural, thermal using ANSYS 9.0 Finite Element Analysis software.

scholarly journals Nondestructive Evaluation of Locally Repaired Coating for Gas Turbine Blades

1996 ◽  
Author(s):  
Y. Shen ◽  
N. Pietranera ◽  
U. Guerreschi ◽  
S. Corcoruto ◽  
E. Gandini
Keyword(s):  
Gas Turbine ◽  
Plasma Spray ◽  
Turbine Blades ◽  
Base Material ◽  
Vacuum Plasma Spray ◽  
Gas Turbine Blades ◽  
Mcraly Coating ◽  
Gas Plasma ◽  
Examination Methods ◽  
Scan Data

Ultrasonic examination methods have been developed to qualify the locally repaired coating on gas turbine blades. The acoustic velocity of the MCrAlY coating obtained by Inert Gas Plasma Spray (IGPS) has been measured and compared with that of Vacuum Plasma Spray (VPS) coating. The thickness of the locally repaired coating on specimens and blades has been evaluated. The coating adhesion on the base material and its distribution have been investigated by A-scan and C-scan data display methods. The influence of surface roughness on the test results has also been examined.

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