Aerodynamic Implication of Endwall and Profile Film Cooling in a Transonic Annular Cascade
2013 (English)In: 21st ISABE Conference / [ed] ISABE, Busan, Korea, 2013Conference paper (Refereed)
An experimental study is performed to observe the aerodynamic implications of endwall and profile film cooling on flow structures and aerodynamic losses. The investigated vane is a geometrically similar transonic nozzle guide vane with engine-representative cooling geometry. Furthermore, a new formulation of the cooling aerodynamic loss equation is presented and compared with the conventional methods. Results from a 5-hole pneumatic probe show that the film coolant significantly alters the secondary flow structure. The effect of different assumptions for the loss calculation is shown to significantly change the measured loss.
Place, publisher, year, edition, pages
Busan, Korea, 2013.
, ISABE-2013, ISABE-2013-1155
Engineering and Technology Mechanical Engineering Aerospace Engineering Energy Engineering Applied Mechanics
Research subject SRA - Energy
IdentifiersURN: urn:nbn:se:kth:diva-128934OAI: oai:DiVA.org:kth-128934DiVA: diva2:648863
21st International Symposium on Air Breathing Engines (ISABE-2103), September 9-13, Busan, Korea
QC 201404092013-09-172013-09-172014-09-09Bibliographically approved