Advanced Cooling in Gas Turbines 2016 Max Jakob Memorial Award Paper Academic Article uri icon

abstract

  • Gas turbines have been extensively used for aircraft engine propulsion, land-based power generation, and industrial applications. Power output and thermal efficiency of gas turbines increase with increasing turbine rotor inlet temperatures (RIT). Currently, advanced gas turbines operate at turbine RIT around 1700C far higher than the yielding point of the blade material temperature about 1200C. Therefore, turbine rotor blades need to be cooled by 35% of high-pressure compressor air around 700C. To design an efficient turbine blade cooling system, it is critical to have a thorough understanding of gas turbine heat transfer characteristics within complex three-dimensional (3D) unsteady high-turbulence flow conditions. Moreover, recent research trend focuses on aircraft gas turbines that operate at even higher RIT up to 2000C with a limited amount of cooling air, and land-based power generation gas turbines (including 300400MW combined cycles with 60% efficiency) burn alternative syngas fuels with higher heat load to turbine components. It is important to understand gas turbine heat transfer problems with efficient cooling strategies under new harsh working environments. Advanced cooling technology and durable thermal barrier coatings (TBCs) play most critical roles for development of new-generation high-efficiency gas turbines with near-zero emissions for safe and long-life operation. This paper reviews basic gas turbine heat transfer issues with advanced cooling technologies and documents important relevant papers for future research references.

published proceedings

  • JOURNAL OF HEAT TRANSFER-TRANSACTIONS OF THE ASME

altmetric score

  • 1.5

author list (cited authors)

  • Han, J.

citation count

  • 57

complete list of authors

  • Han, Je-Chin

publication date

  • July 2018