scholarly journals An Analytical Method of Fatigue Damage Estimation for Compressor Stator Blades of Gas Turbines under Rotating Stall. 1st Report. Residual Life Assessment of Gas Turbine Compressor Blades.

2001 ◽  
Vol 67 (654) ◽  
pp. 327-334
Author(s):  
Yasushi HAYASAKA ◽  
Shigeo SAKURAI ◽  
Takeshi KUDO ◽  
Kunihiro ICHIKAWA
Keyword(s):  
Gas Turbine ◽  
Fatigue Damage ◽  
Gas Turbines ◽  
Residual Life ◽  
Rotating Stall ◽  
Life Assessment ◽  
Damage Estimation ◽  
Compressor Blades ◽  
Residual Life Assessment ◽  
Gas Turbine Compressor

Life Management System for Hot-Gas-Path Components of Gas Turbines

1999 ◽  
Author(s):  
Yasushi Hayasaka ◽  
Nobuhiro Isobe ◽  
Shigeo Sakurai ◽  
Kazuhiko Kumata
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Management System ◽  
Residual Life ◽  
Combined Cycle ◽  
Operating Conditions ◽  
Life Assessment ◽  
Hot Gas ◽  
Life Management ◽  
Residual Life Assessment

Recently the number of gas-turbine-powered combined-cycle plants has been increasing because of their efficiency and environmental compatibility. Gas turbine operating conditions are severe, especially for hot-gas-path components. To improve the reliability of such components and to extend their life, we have developed a life management system based on a residual-life-assessment method. The system makes possible integrated residual-life-assessment based on numerical analyses, material destructive-tests, nondestructive inspections, statistical analyses of field machine data, and the use of a database. To develop the system, the primary damage mechanism for each component is clarified and material degradation is evaluated. For nozzles, the system describes a method of predicting the maximum surface crack growth. The validity of the methods is verified by assessment of the inspection data. This paper also describes optimization of operating cost and RAM (reliability, availability and maintainability).

Analytical Method of Fatigue Damage Estimation for Compressor Stator Blades of Gas Turbines Experiencing Rotating Stall

2002 ◽  
Author(s):  
Yasushi Hayasaka ◽  
Shigeo Sakurai ◽  
Takeshi Kudo ◽  
Kunihiro Ichikawa
Keyword(s):  
Stress Analysis ◽  
Fatigue Damage ◽  
Analytical Method ◽  
Gas Turbines ◽  
Estimation Method ◽  
Rotating Stall ◽  
Environmental Data ◽  
Response Analysis ◽  
Damage Estimation ◽  
Stress Peak

To improve the reliability of compressor stator blades of gas turbines, an analytical method for estimating their fatigue damage has been developed. This method is based on blade-vibratory-stress analysis, stress-peak counting, and use of actual environmental data. The blade-vibratory-stress analysis takes the superposition of multi-peaks of the stress spectrum into account. The numerically simulated stress showed better agreement with measured stress than that from a conventional stress analysis, which is based on frequency-response analysis considering a single peak of the lowest single eigen-vibration-mode. A time-domain stress history was synthesized from the blade-vibratory-stress analysis results. Furthermore, the fatigue damage of the blade under rotating stall was estimated by the linear-damage-rule from the stress-peak counting of the stress and from material data. The estimated fatigue-damage agrees well with the measured results. This agreement means that our new fatigue-damage-estimation method is more accurate than the conventional one.

Degradation of Compressor Blades of Gas Turbines in Coastal and Industrial Environment

2016 ◽  
Vol 1133 ◽  
pp. 371-375 ◽  
Author(s):  
Salmi Mohd Yunus ◽  
Saiful Adilin Sekari ◽  
Mohd Hafiz Abdul Ghaffar
Keyword(s):  
Gas Turbine ◽  
Gas Turbines ◽  
Turbine Unit ◽  
Oil Refinery ◽  
Oil Refining ◽  
Degradation Mechanisms ◽  
Gas Turbine Unit ◽  
Compressor Blades ◽  
Industrial Environment ◽  
Gas Turbine Compressor

Gas turbine compressor blades will age and degrade in their operation. There are a lot of factors that will contribute to the degradation mechanisms and its acceleration. These factors encompass the site location, the site conditions including the aspect of air quality, water washing practice, etc. A study undertaken by Materials Engineering Group of TNB Research Sdn Bhd on 2 units of gas turbine compressor those are located near to the sea around Peninsular of Malaysia, to determine the degradation mechanisms of the blades. All these gas turbine units are located in different industrial environment. The first gas turbine unit, so called GTA is located in coastal, petrochemicals production and crude oil refining environment. The second gas turbine unit, so called GTB, located in coastal and industrial environment. The surrounding industries of GTB including oil refinery, chemical, ship fabrication and etc. This paper reports the degradation type of those gas turbine units’ compressor blades with their contributing factors.

Performance of Gas Turbine Compressor Cleaners

1992 ◽  
Author(s):  
H. J. Kolkman
Keyword(s):  
Corrosion Inhibitor ◽  
Gas Turbine ◽  
Corrosion Inhibition ◽  
Gas Turbines ◽  
Jet Engines ◽  
Cleaning Efficiency ◽  
Compressor Blades ◽  
Gas Turbine Compressor

Deposits are regularly removed from compressor blades and vanes of installed jet engines and gas turbines by compressor washing. Hereby a compressor cleaner is sprayed into the compressor while operating at reduced or normal r.p.m. Recently developed compressor cleaners are claimed to be ecologically sound. In addition, many new compressor cleaners contain a corrosion inhibitor. The cleaning efficiency of eight (old and new) compressor cleaners was determined by means of simulated compressor washing of compressor blades that had become foul in service. For the situation simulated, the cleaning efficiency of new, ecologically sound cleaners turned out to be poor as compared with old compressor cleaners. The corrosion inhibition offered by those cleaners that contain a corrosion inhibitor was found to be satisfactory.

Residual Life Assessment of a Critical Component of a Gas Turbine: Achievements and Challenges

2014 ◽  
Author(s):  
Wieslaw Beres ◽  
Zhong Zhang ◽  
David Dudzinski ◽  
W. R. Chen ◽  
X. J. Wu
Keyword(s):  
Crack Propagation ◽  
Gas Turbine ◽  
Mixed Mode ◽  
Residual Life ◽  
Crack Nucleation ◽  
Three Dimensional ◽  
Life Assessment ◽  
Mode Interaction ◽  
Turbine Engine ◽  
Residual Life Assessment

The residual life assessment of a turbine spacer from a gas turbine engine is presented. The spacer has been identified as one of the safety critical components of the engine, therefore the useful life of this component significantly affects economic operation of the fleet. Numerical analyses of fatigue crack propagation at one critical location of the spacer were performed using both three dimensional (3D) finite element based method and the weight function method. These results combined with the material data allowed for basic assessment of the damage tolerance of this component. Experimental validation of the spacer life was performed in a spin rig facility. During this validation, two sets of spacers were tested and the number of cycles to appearance of a detectable crack was recorded. Moreover, a fractographic study was conducted on the fracture surfaces of two spin rig tested spacers using scanning electronic microscopy techniques. It was found that crack nucleation occurred at multiple sites and crack propagation occurred by a mixed mode of striation formation and faceted fracture. Therefore it was concluded that the mixed mode interaction should be considered in predicting the fatigue life of the spacer. Finally, the paper describes the challenges and pitfalls encountered during preparation and execution of the analyses and tests, including availability of engine and operational data and also uncertainties in interpretation of the results.

Gas turbine hot section components: The challenge of ‘residual life’ assessment

2000 ◽  
Vol 214 (3) ◽  
pp. 193-201 ◽  
Author(s):  
M I Wood
Keyword(s):  
Gas Turbine ◽  
Residual Life ◽  
Life Assessment ◽  
Residual Life Assessment ◽  
Assessment Procedures

Gas turbine hot section parts are high-value components which have finite lives. Their durability has an important role in controlling maintenance intervals and the associated costs. This paper reviews the sources of degradation in some components, the technology available to quantify the damage, and publicly available assessment procedures which can be used for component life assessment.

Performance of Gas Turbine Compressor Cleaners

1993 ◽  
Vol 115 (3) ◽  
pp. 674-677 ◽  
Author(s):  
H. J. Kolkman
Keyword(s):  
Corrosion Inhibitor ◽  
Gas Turbine ◽  
Corrosion Inhibition ◽  
Gas Turbines ◽  
Jet Engines ◽  
Cleaning Efficiency ◽  
Compressor Blades ◽  
Gas Turbine Compressor

Deposits are regularly removed from compressor blades and vanes of installed jet engines and gas turbines by compressor washing. A compressor cleaner is sprayed into the compressor while operating at reduced or normal rpm. Recently developed compressor cleaners are claimed to be ecologically sound. In addition, many new compressor cleaners contain a corrosion inhibitor. The cleaning efficiency of eight (old and new) compressor cleaners was determined by means of simulated compressor washing of compressor blades that had become fouled in service. For the situation simulated, the cleaning efficiency of new, ecologically sound cleaners turned out to be poor as compared with old compressor cleaners. The corrosion inhibition offered by those cleaners that contain a corrosion inhibitor was found to be satisfactory.

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