Melt Infiltrated Ceramic Matrix Composites for Shrouds and Combustor Liners of Advanced Industrial Gas Turbines

Corman, Gregory S.; Luthra, Krishan L.; Jonkowski, Jill; Mavec, Joseph; Bakke, Paul; Haught, Debbie A.; Smith, M. D.

doi:10.2172/1004879

Cited by 6 publications

(1 citation statement)

References 4 publications

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“…In the past two decades, CMCs have attracted a lot of research in gas turbine components such as combustor liners, shrouds, and nozzles. 22–27 Research on CMC blades for high-pressure turbine blades is still in its preliminary design and development stages. CMCs have been identified as a good candidate for vanes and blades because of their high-temperature endurance capability (over 1200°C).…”

Section: Introductionmentioning

confidence: 99%

Thermodynamics of CMC bladed marine gas turbine-LM 2500: Effect of cycle operating parameters

Rathore

Kar

Sanjay

2022

International Journal of Engine Research

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Recent developments in ceramic-matrix composites and their successful use in combustor liners and shrouds have generated interest among researchers to adopt these materials in rotating gas turbine blades, especially in the first stages of high-pressure turbines where gas temperatures are highest. CMC blades have the potential of being retrofitted to replace superalloy turbine blades in operating gas turbines. In this paper, a comparative study on the thermodynamic performance of a marine gas turbine engine, LM 2500, featuring directionally solidified nickel superalloy blades versus novel CMC blades in the high-pressure turbine sections has been reported. Mathematical modeling of the gas turbine cycle components has been developed and then coded in C++ language. The effects of turbine inlet temperature on thermodynamic efficiencies, coolant mass flow rates, and work ratios on the two systems have been analyzed. Finally, the exergy analysis of the systems’ components has been done to identify the benefits of adopting CMC blades in the LM 2500 system. It has been observed that when compared to the directionally solidified bladed turbine system, the projected first law efficiency of CMC bladed LM 2500 gas turbines can be enhanced over 7% (from 34.17% to 41.21%). The projected work ratio can be improved by over 16% (from 0.49 to 0.57) at the turbine inlet temperature of 1725 K.

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