A preliminary characterization of the flow field inside an advanced leading edge cooling channel characterized by multiple internal impinging jests has been carried out by means of 2D and Stereo PIV. The measurements have been conducted both in the jets impingement region and in the feeding channel. Test conditions are characterized by a Reynolds number of 30k and a Rotation number of 0.05, both values are defined with reference to the jet characteristics. Different crossflow conditions, namely feeding channel over jet flow rates ratio, have been used to simulate the three main blade regions (i.e. HUB, MID, and TIP). The flow inside the feeding channel turned out to be significantly affected by rotation, with stronger effects found at blade TIP, where the local rotation number is higher. Conversely, when moving inside the main impingement duct, the jet core has been found to be only marginal modified due to rotation. Finally, Reynolds number effect has been also investigated by repeating measurements for the MID crossflow condition at Re=10k. A substantial Reynolds number independence has been found.
Aerodynamic behavior under rotation of an advanced leading edge impingement cooling channel
FURLANI, Luca;ARMELLINI, Alessandro;CASARSA, Luca
2015-01-01
Abstract
A preliminary characterization of the flow field inside an advanced leading edge cooling channel characterized by multiple internal impinging jests has been carried out by means of 2D and Stereo PIV. The measurements have been conducted both in the jets impingement region and in the feeding channel. Test conditions are characterized by a Reynolds number of 30k and a Rotation number of 0.05, both values are defined with reference to the jet characteristics. Different crossflow conditions, namely feeding channel over jet flow rates ratio, have been used to simulate the three main blade regions (i.e. HUB, MID, and TIP). The flow inside the feeding channel turned out to be significantly affected by rotation, with stronger effects found at blade TIP, where the local rotation number is higher. Conversely, when moving inside the main impingement duct, the jet core has been found to be only marginal modified due to rotation. Finally, Reynolds number effect has been also investigated by repeating measurements for the MID crossflow condition at Re=10k. A substantial Reynolds number independence has been found.I documenti in IRIS sono protetti da copyright e tutti i diritti sono riservati, salvo diversa indicazione.
