Effective internal and external cooling of airfoils is key to maintaining component life for efficient gas turbines. Cooling designs have spanned the range from simple internal convective channels to more advanced double-walls with shaped film-cooling holes. This paper describes the development of an internal and external cooling concept for a state-of-the-art cooled turbine blade. These cooling concepts are based on a review of literature and patents, as well as, interactions with academic and industry turbine cooling experts. The cooling configuration selected and described in this paper is referred to as the “baseline” design, since this design will simultaneously be tested with other more advanced blade cooling designs in a rotating turbine test facility using a “rainbow turbine wheel” configuration. For the baseline design, the leading edge is cooled by internal jet impingement and showerhead film cooling. The midchord region of the blade contains a three-pass serpentine passage with internal discrete V-shaped trip strips to enhance the internal heat transfer coefficient (HTC). The film cooling along the midchord of the blade uses multiple rows of shaped diffusion holes. The trailing edge is internally cooled using jet impingement and externally film cooled through partitioned cuts on the pressure side of the blade.
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July 2018
Research-Article
State-of-the-Art Cooling Technology for a Turbine Rotor Blade
Karen A. Thole,
Karen A. Thole
Mechanical and Nuclear Engineering Department,
Pennsylvania State University,
College Park, PA 16802
e-mail: kthole@engr.psu.edu
Pennsylvania State University,
College Park, PA 16802
e-mail: kthole@engr.psu.edu
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Tom I-P. Shih
Tom I-P. Shih
School of Aeronautics and Astronautics,
Purdue University,
West Lafayette, IN 47907
e-mail: tomshih@purdue.edu
Purdue University,
West Lafayette, IN 47907
e-mail: tomshih@purdue.edu
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Jason Town
Douglas Straub
James Black
Karen A. Thole
Mechanical and Nuclear Engineering Department,
Pennsylvania State University,
College Park, PA 16802
e-mail: kthole@engr.psu.edu
Pennsylvania State University,
College Park, PA 16802
e-mail: kthole@engr.psu.edu
Tom I-P. Shih
School of Aeronautics and Astronautics,
Purdue University,
West Lafayette, IN 47907
e-mail: tomshih@purdue.edu
Purdue University,
West Lafayette, IN 47907
e-mail: tomshih@purdue.edu
1Corresponding author.
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received March 2, 2018; final manuscript received March 26, 2018; published online June 14, 2018. Editor: Kenneth Hall.
J. Turbomach. Jul 2018, 140(7): 071007 (12 pages)
Published Online: June 14, 2018
Article history
Received:
March 2, 2018
Revised:
March 26, 2018
Citation
Town, J., Straub, D., Black, J., Thole, K. A., and Shih, T. I. (June 14, 2018). "State-of-the-Art Cooling Technology for a Turbine Rotor Blade." ASME. J. Turbomach. July 2018; 140(7): 071007. https://doi.org/10.1115/1.4039942
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