Shower Head and Trailing Edge Cooling Influence on Transonic Vane Aero Performance
2014 (English)In: ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, ASME Press, 2014Conference paper (Refereed)
An experimental investigation on a cooled nozzle guide vane has been conducted in an annular sector to quantify aerodynamic influences of shower head and trailing edge cooling. The investigated vane is a typical high pressure gas turbine vane, geometrically similar to a real engine component, operated at a reference exit Mach number of 0.89. The investigations have been performed for various coolant-to-mainstream mass-flux ratios. New loss equations are derived and implemented regarding coolant aerodynamic losses. Results lead to a conclusion that both trailing edge cooling and shower head film cooling increase the aerodynamic loss compared to an uncooled case. In addition, the trailing edge cooling has higher aerodynamic loss compared to the shower head cooling. Secondary losses decrease with inserting shower head film cooling compared to the uncooled case. The trailing edge cooling appears to have less impact on the secondary loss compared to the shower head cooling. Area-averaged exit flow angles around midspan increase for the trailing edge cooling.
Place, publisher, year, edition, pages
ASME Press, 2014.
Aerodynamic loss, Film cooling, Nozzle guide vane, Shower head cooling, Trailing edge cooling
Aerospace Engineering Applied Mechanics Energy Engineering
Research subject Aerospace Engineering; Energy Technology
IdentifiersURN: urn:nbn:se:kth:diva-148423DOI: 10.1115/GT2014-25613ISI: 000361923200018ScopusID: 2-s2.0-84922224108ISBN: 978-079184562-2OAI: oai:DiVA.org:kth-148423DiVA: diva2:736548
ASME Turbo Expo 2014: Turbine Technical Conference and Exposition, GT 2014, Dusseldorf, Germany, 16 June 2014 through 20 June 2014
QC 201502172014-08-072014-08-072015-10-29Bibliographically approved