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Title: State-of-the-Art Cooling Technology for a Turbine Rotor Blade

Journal Article · · Journal of Turbomachinery
DOI:https://doi.org/10.1115/1.4039942· OSTI ID:1461194
 [1];  [2];  [3];  [1];  [4]
  1. Pennsylvania State Univ., University Park, PA (United States)
  2. National Energy Technology Lab. (NETL), Morgantown, WV (United States)
  3. National Energy Technology Lab. (NETL), Pittsburgh, PA, (United States)
  4. Purdue Univ., West Lafayette, IN (United States)
+ Show Author Affiliations

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. Furthermore, the trailing edge is internally cooled using jet impingement and externally film cooled through partitioned cuts on the pressure side of the blade.

Research Organization:
National Energy Technology Lab. (NETL), Morgantown, WV (United States)
Sponsoring Organization:
USDOE
OSTI ID:
1461194
Report Number(s):
NETL-PUB-21762
Journal Information:
Journal of Turbomachinery, Vol. 140, Issue 7; ISSN 0889-504X
Publisher:
ASMECopyright Statement
Country of Publication:
United States
Language:
English
Citation Metrics:
Cited by: 23 works
Citation information provided by
Web of Science

References (24)

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Experimental and Numerical Cross-Over Jet Impingement in an Airfoil Trailing-Edge Cooling Channel journal April 2011
Aerothermal Investigation of a Rib-Roughened Trailing Edge Channel With Crossing Jets—Part II: Heat Transfer Analysis journal December 2010
Trailing Edge Film Cooling of Gas Turbine Airfoils—External Cooling Performance of Various Internal Pin Fin Configurations journal April 2011
Effect of In-Hole Roughness on Film Cooling From a Shaped Hole journal November 2016
Evaluation of internal heat-transfer coefficients for impingement-cooled turbine airfoils. journal May 1969
Thermal Performance of Angled, V-Shaped, and W-Shaped Rib Turbulators in Rotating Rectangular Cooling Channels (AR=4:1) journal October 2004
Aerodynamics of a Letterbox Trailing Edge: Effects of Blowing Rate, Reynolds Number, and External Turbulence on Aerodynamic Losses and Pressure Distribution journal May 2010
The Optimal Distribution of Pin Fins for Blade Tip Cap Underside Cooling journal September 2014
The Optimal Distribution of Chordwise Rib Fin Arrays for Blade Tip Cap Underside Cooling journal September 2013
Letterbox Trailing Edge Heat Transfer: Effects of Blowing Rate, Reynolds Number, and External Turbulence on Heat Transfer and Film Cooling Effectiveness journal September 2009
Impingement Heat Transfer Enhancement on a Cylindrical, Leading Edge Model With Varying Jet Temperatures journal March 2013
Evaluation of Superposition Predictions for Showerhead Film Cooling on a Vane journal April 2015
Experimental and Numerical Crossover Jet Impingement in a Rib-Roughened Airfoil Trailing-Edge Cooling Channel journal June 2013
Heat Transfer Measurements in a Leading Edge Geometry With Racetrack Holes and Film Cooling Extraction journal March 2013
Adiabatic and Overall Effectiveness for the Showerhead Film Cooling of a Turbine Vane journal September 2013
Measurements of Adiabatic Film and Overall Cooling Effectiveness on a Turbine Vane Pressure Side With a Trench journal June 2013
Optimization of a U-Bend for Minimal Pressure Loss in Internal Cooling Channels—Part II: Experimental Validation journal June 2013
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Experimental Simulation of Turbine Airfoil Leading Edge Film Cooling journal April 1988
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Thermal Field Measurements for a Shaped Hole at Low and High Freestream Turbulence Intensity journal November 2016

Figures / Tables (24)

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gas turbines
film cooling
leading edge cooling
trailing edge cooling
blade cooling