This paper presents the results of a study conducted to determine the life expectancy of a power turbine disk. The purpose of the study is to revisit the original design calculations with current numerical computing techniques. By determining the state of stress and temperature in the vicinity of the stress concentrations, combined with material properties, the life expectancy of power turbine disks can be established.
Water or steam injection for NOX control or power augmentation can impact turbine hot section component life and maintenance interval. This relates to the effect of added water on hot-gas transport properties. Higher gas conductivity, in particular, increases heat transfer to blade and vane, and can lead to higher metal temperature and reduced part life. Part life impact from steam or water injection is also related to the way engine is controlled. Life cycle impact of steam injection on the LM6000PC HP turbine blade has been studied. The relationship between steam injection, LP turbine inlet temperature control, blade metal temperature, and corresponding life change was analyzed. The analysis result can be used for the assessment of life cycle impact with steam injection and temperature control limit.
Realistic assessment of the remaining serviceable life in turbine hot section components plays an important role in engine condition-based maintenance and overhaul. This paper presents application of an engineering approach that integrates mechanical and performance engineering with metallurgy for turbine blade remaining life on-line assessment. By identifying the life limiting factors in a given application and monitoring the rate of the damage, economical repair, replacement and overhaul intervals can be established. Examples are given to illustrate application of this engineering approach in identifying failure mechanisms and predicting blade remaining serviceable life for TransCanada PipeLines LM1600 fleet.
The objective of this paper is to critically review the cooling design for the MS6001 first stage buckets and examine alternate designs for improved cooling. Several basic designs were considered to improve cooling performance, extend service life, and improve the reliability of the first stage bucket. Of the designs being considered and compared with existing and past designs, two options containing 13 and 13M (modified) cooling holes were investigated. The target for the design which was met by the 13M design, was to reduce bucket bulk metal temperature by an average of 13.9°C (25°F), while maintaining current unit performance and bucket integrity. Finite element analysis was performed to evaluate the aerofoil thermal gradients and the results demonstrate that a cooler core and an overall reduction in bulk metal temperature was obtained with the modified designs. In addition to the design analysis, bucket alloys were reviewed and IN-738 was chosen for its reliability and predictable performance.
Gas turbine performance calculations are either predictive or diagnostic. Predictive calculations tell what the gas turbine can do and diagnostic calculations tell how the engine is doing. Both types of calculations are inter-related in that the diagnostic calculation requires a predictive calculation to compare with so that a diagnosis can be made. Engine designers are primarily concerned with predictive calculations and users are concerned with the diagnostic calculations. This paper will show the development of a predictive calculation and how a diagnostic calculation can be coupled with the predictive calculation so that both the designer and user can take advantage of gas turbine performance code. The development of Dresser-Rand’s predictive code LGTP and Liburdi Engineering Limited’s LGTP-Health diagnostic code will be discussed as demonstration examples.
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