The present study investigates the effects of relative position on heat transfer distributions of a showerhead film-cooled stationary rotor blade. Detailed heat/mass transfer coefficients were measured using the naphthalene sublimation method. A low-speed wind tunnel was used, with a single annular turbine stage consisting of sixteen guide vanes and blades. The axial chord length of the test blade was 136 mm. The inlet and exit angles of the test blade were 56.4° and −62.6°, respectively, which produced a turning angle of 119.0°. Three rows of film cooling holes were drilled in the leading edge region of the blade. Each row had 10 circular cooling holes along the spanwise direction, and the diameter of each cooling hole was 1.2 mm. Detailed heat transfer coefficients were measured at two different guide vane and rotor blade relative positions, while changing the blowing rate (M) from 1.0 to 2.0. The inlet Reynolds number was fixed at 1.3×105 based on the blade axial chord length. As the blowing rate increased, overall heat transfer rates increased, and the lower peaks formed on the pressure side by the separation bubble were reduced, and disappeared at M = 2.0. The effects of vane/blade relative position were significant because the incoming flow condition was changed. However, the spanwise average Sherwood number became similar as the blowing rate increased.
Skip Nav Destination
ASME Turbo Expo 2010: Power for Land, Sea, and Air
June 14–18, 2010
Glasgow, UK
Conference Sponsors:
- International Gas Turbine Institute
ISBN:
978-0-7918-4399-4
PROCEEDINGS PAPER
Effects of Vane/Blade Relative Positions and Showerhead Film Cooling on a Stationary Blade: Heat Transfer
Dong Hyun Lee,
Dong Hyun Lee
Yonsei University, Seoul, Korea
Search for other works by this author on:
Dong-Ho Rhee,
Dong-Ho Rhee
Korea Aerospace Research Institute, Daejeon, Korea
Search for other works by this author on:
Kyung Min Kim,
Kyung Min Kim
Yonsei University, Seoul, Korea
Search for other works by this author on:
Hyung Hee Cho
Hyung Hee Cho
Yonsei University, Seoul, Korea
Search for other works by this author on:
Dong Hyun Lee
Yonsei University, Seoul, Korea
Dong-Ho Rhee
Korea Aerospace Research Institute, Daejeon, Korea
Kyung Min Kim
Yonsei University, Seoul, Korea
Hyung Hee Cho
Yonsei University, Seoul, Korea
Paper No:
GT2010-23321, pp. 1785-1794; 10 pages
Published Online:
December 22, 2010
Citation
Lee, DH, Rhee, D, Kim, KM, & Cho, HH. "Effects of Vane/Blade Relative Positions and Showerhead Film Cooling on a Stationary Blade: Heat Transfer." Proceedings of the ASME Turbo Expo 2010: Power for Land, Sea, and Air. Volume 4: Heat Transfer, Parts A and B. Glasgow, UK. June 14–18, 2010. pp. 1785-1794. ASME. https://doi.org/10.1115/GT2010-23321
Download citation file:
18
Views
Related Proceedings Papers
Related Articles
Aerothermal Investigations of Tip Leakage Flow in Axial Flow Turbines—Part III: TIP Cooling
J. Turbomach (January,2009)
Heat Transfer Measurements on Turbine Airfoils Using the Naphthalene Sublimation Technique
J. Turbomach (July,1995)
Related Chapters
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Outlook
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Introduction
Consensus on Operating Practices for Control of Water and Steam Chemistry in Combined Cycle and Cogeneration