The heat/mass transfer for flow is studied through perforated plates for application to combustor wall and turbine blade film cooling. The results indicate that heat/mass transfer coefficients inside the hole surface vary significantly due to flow separation and reattachment. The transfer coefficient near the reattachment point is about four and half times that for a fully developed circular tube flow. The heat/mass transfer coefficient on the leeward surface has the same order as that on the windward surface because of a strong recirculation flow between neighboring jets from that array holes. For flow through in-line layers, the transfer coefficients affected by the gap spacing is approximately 100% higher on the windward surface of the second wall is about 20% lower on the side inside hole surface than that with a single layer.
|Original language||English (US)|
|Number of pages||1|
|Journal||American Society of Mechanical Engineers (Paper)|
|State||Published - Jan 1 1995|
|Event||Proceedings of the International Gas Turbine and Aeroengine Congress and Exposition - Houston, TX, USA|
Duration: Jun 5 1995 → Jun 8 1995