Development of a high-speed imaging technique for observing centrifugal destruction of a ceramic gas turbine blade in hot gas conditions

1995 ◽  
Author(s):  
Makoto Watanabe ◽  
Koushi Ando
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
High Speed ◽  
Imaging Technique ◽  
Gas Turbine Blade ◽  
High Speed Imaging ◽  
Hot Gas

EVALUATION METHOD OF GAS TURBINE BLADES COVERING INTEGRITY BY IR CAMERA

2006 ◽  
Vol 20 (25n27) ◽  
pp. 4329-4334 ◽  
Author(s):  
DONG-JO YANG ◽  
CHOUL-JUN CHOI ◽  
JAE-YEOL KIM
Keyword(s):  
Gas Turbine ◽  
Infrared Thermography ◽  
Turbine Blade ◽  
High Speed ◽  
Evaluation Method ◽  
Coating Layer ◽  
Turbine Blades ◽  
Gas Turbine Blade ◽  
Ir Camera ◽  
Wide Range

Key parts of the main equipment in a gas turbine may likely be damaged due to operation under high temperature, high pressure, high-speed rotation, etc. Accordingly, the cost for maintenance increases and the damaged parts may cause generation to stop. The surface of a blade is thermal-sprayed, using powder with main compositions such as Ni , Cr , Al , etc, in order to inhibit hot oxidation. Conventional regular maintenance of the coating layer of a blade is made by FPI (Fluorescent Penetrant Inspection) and MTP (Magnetic Particle Testing). Such methods, however, are complicated and take a long time and also require high cost. In this study, defect diagnostics were tested on the coating layer of an industrial gas turbine blade, using an infrared thermography camera. Since the infrared thermography method can check a temperature distribution by means of non-contact on a wide range of areas, it can advantageously save expense and time as compared to conventional test methods. For the infrared thermography method, however, thermo-load must be applied onto a tested specimen and it is difficult to quantify the measured data. To solve the problems, this paper includes description about producing a specimen of a gas turbine blade (bucket), applying thermo-load onto the produced specimen, photographing thermography images by an infrared thermography camera, analyzing the thermography images, and pre-testing to analyze defects on the coating layer of the gas turbine blade.

Dominant parameters affecting the reliability of TBCs on a gas turbine blade during erosion by a particle-laden hot gas stream

Wear ◽  
2017 ◽  
Vol 390-391 ◽  
pp. 166-175 ◽  
Author(s):  
Y.Q. Xiao ◽  
L. Yang ◽  
Y.C. Zhou ◽  
Y.G. Wei ◽  
N.G. Wang
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Gas Turbine Blade ◽  
Hot Gas

Evaluation of FEM Based Methods to Predict Temperature Distributions of a Convection Cooled Gas Turbine Blade

2014 ◽  
Author(s):  
B. Woerz ◽  
Y. Mick ◽  
E. Findeisen ◽  
P. Jeschke ◽  
M. Rabs
Keyword(s):  
Heat Transfer ◽  
Numerical Methods ◽  
Gas Turbine ◽  
Turbine Blade ◽  
Gas Turbines ◽  
Cooling System ◽  
Three Dimensional ◽  
Gas Turbine Blade ◽  
Cooling Channels ◽  
Hot Gas

This paper presents different numerical methods to predict the thermal load of a convection cooled gas turbine blade under realistic operating temperature conditions. The subject of the investigation is a gas turbine rotor blade which is equipped with a state-of-the-art convection cooling system. Firstly, two FEM based methods are introduced. One method, referred to as FEM1D method, uses empirical correlations from the open literature to obtain one dimensional heat transfer coefficients along one flow line inside the cooling channels while in the hot gas path a three dimensional CFD simulation is used. The second method (FEM2D) uses three dimensional CFD simulations to obtain two dimensional heat transfer coefficient distributions for both, the inner cooling channels and the hot gas path. The results from both numerical methods are compared with each other and are validated with experimental data, quantifying also their accuracy limits. In total this paper gives an evaluation of two different FEM methods to predict temperature distribution in convection cooled gas turbines. Their accuracy, numerical cost and limitations are evaluated. It turns out that the temperature profiles gained by both methods are generally in good agreement with the experiments. However, while causing higher numerical costs the more detailed FEM2D method achieves more accurate results.

scholarly journals An alternative coating material for gas turbine blade for aerospace applications

2020 ◽  
Vol 1706 ◽  
pp. 012183
Author(s):  
Yajnesh M Poojari ◽  
Koustubh S Annigeri ◽  
Nilesh Bandekar ◽  
Kiran U Annigeri ◽  
Vinayak badiger ◽  
...  
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Coating Material ◽  
Gas Turbine Blade ◽  
Aerospace Applications

Defect assessment in gas turbine blade coatings using non-contact thermography

2020 ◽  
Author(s):  
M. Mahesh Kumar ◽  
A.H.V. Pavan ◽  
R. Markandeya ◽  
Kulvir Singh
Keyword(s):  
Gas Turbine ◽  
Turbine Blade ◽  
Gas Turbine Blade ◽  
Defect Assessment
Sign in / Sign up

Export Citation Format

Share Document