Gas turbine blades are often cooled by using combined internal and external cooling methods where for internal cooling purposes, usually, serpentine passages are applied. In order to optimize the design of these serpentine passages it is inevitable to know the influence of mass extraction due to film cooling holes, dust holes, or due to side walls for feeding successive cooling channels as for the trailing edge on the internal cooling performance. Therefore, the objective of the present study was to analyze the influence of side wall mass extraction on pressure loss and heat transfer distribution in a two-pass internal cooling channel representing a cooling scheme with flow towards the trailing edge. The investigated rectangular two-pass channel consisted of an inlet and outlet duct with a height-to-width ratio of connected by a 180 deg sharp bend. The tip-to-web distance was kept constant at . The mass extraction was realized using several circular holes in the outlet pass side wall. Two geometric configurations were investigated: A configuration with mass extraction solely in the outlet pass and a configuration with mass extraction in the bend region and outlet pass. The extracted mass flow rate was 0%, 10%, and 20% of the inlet channel mass flow. Spatially resolved heat transfer distributions were obtained using the transient thermochromic liquid crystal technique. Pressure losses were determined in separate experiments by local static pressure measurements. Furthermore, a computational study was performed solving the Reynolds-averaged Navier–Stokes equations using the commercial finite-volume solver FLUENT. The numerical grids were generated using the hybrid grid generator CENTAUR. Three different turbulence models were considered: the realizable model with two-layer wall treatment, the model, and the model. The experimental data of the investigation of side wall ejection showed that the heat transfer in the bend region slightly increased when the ejection were in operation, while the heat transfer in the section of the outlet channel with side wall ejection was nearly not affected. After this section, a decrease in heat transfer was observed, which can be attributed to the decreased mainstream mass flow rate.
Skip Nav Destination
e-mail: itlr@itlr.uni-stuttgart.de
Article navigation
April 2011
Research Papers
The Effect of Side Wall Mass Extraction on Pressure Loss and Heat Transfer of a Ribbed Rectangular Two-Pass Internal Cooling Channel
Sven Olaf Neumann
Sven Olaf Neumann
Institut für Thermodynamik der Luft-und Raumfahrt (ITLR),
e-mail: itlr@itlr.uni-stuttgart.de
Universität Stuttgart
, Pfaffenwaldring 31, D-70569 Stuttgart, Germany
Search for other works by this author on:
Sven Olaf Neumann
Institut für Thermodynamik der Luft-und Raumfahrt (ITLR),
Universität Stuttgart
, Pfaffenwaldring 31, D-70569 Stuttgart, Germanye-mail: itlr@itlr.uni-stuttgart.de
J. Turbomach. Apr 2011, 133(2): 021002 (11 pages)
Published Online: October 19, 2010
Article history
Received:
July 14, 2009
Revised:
August 3, 2009
Online:
October 19, 2010
Published:
October 19, 2010
Citation
Schüler, M., Zehnder, F., Weigand, B., von Wolfersdorf, J., and Neumann, S. O. (October 19, 2010). "The Effect of Side Wall Mass Extraction on Pressure Loss and Heat Transfer of a Ribbed Rectangular Two-Pass Internal Cooling Channel." ASME. J. Turbomach. April 2011; 133(2): 021002. https://doi.org/10.1115/1.4000552
Download citation file:
Get Email Alerts
Cited By
Impacts of Material and Machine on the Variation of Additively Manufactured Cooling Channels
J. Turbomach (March 2025)
Scaling Heat Transfer and Pressure Losses of Novel Additively Manufactured Rib Designs
J. Turbomach (March 2025)
Related Articles
The Effect of Turning Vanes on Pressure Loss and Heat Transfer of a Ribbed Rectangular Two-Pass Internal Cooling Channel
J. Turbomach (April,2011)
Internal Cooling Near Trailing Edge of a Gas Turbine Airfoil With Cooling Airflow Through Blockages With Holes
J. Turbomach (July,2008)
Experimental and Numerical Study of Mass/Heat Transfer on an Airfoil Trailing-Edge Slots and Lands
J. Turbomach (April,2007)
Film Cooling From a Row of Holes Supplemented With Antivortex Holes
J. Turbomach (April,2009)
Related Proceedings Papers
Related Chapters
Control and Operational Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential
Laminar Fluid Flow and Heat Transfer
Applications of Mathematical Heat Transfer and Fluid Flow Models in Engineering and Medicine
Thermodynamic Performance
Closed-Cycle Gas Turbines: Operating Experience and Future Potential