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research-article

Advanced Cooling in Gas Turbines - 2016 Max Jakob Memorial Award Paper

[+] Author and Article Information
Je-Chin Han

Turbine Heat Transfer Laboratory, Department of Mechanical Engineering, Texas A&M University, College Station, Texas 77843-3123
jc-han@tamu.edu

1Corresponding author.

ASME doi:10.1115/1.4039644 History: Received February 08, 2018; Revised February 27, 2018

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 1700°C far higher than the yielding point of the blade material temperature about 1200°C. Therefore, turbine rotor blades need to be cooled by 3-5% of high-pressure compressor air around 700°C. To design an efficient turbine blade cooling system, it is critical to have a thorough understanding of gas turbine heat transfer characteristics within complex 3-D unsteady high-turbulence flow conditions. Moreover, recent research trend focuses on aircraft gas turbines operate at even higher RIT up to 2000°C with a limited amount of cooling air, and land-based power generation gas turbines (including 300-400 MW 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 developments 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.

Copyright (c) 2018 by ASME
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