Session: 12-13 General Film Cooling I

Paper Number: 78519

78519 - Optimized Film Cooling Flow on a Contoured Endwall Within a Transonic Annular Cascade 

Film cooling was studied on the endwall of a five-vane annular cascade in a blowdown wind tunnel at an exit Mach number of 0.9. The adiabatic film cooling effectiveness was calculated from the partial pressure of oxygen measured with binary pressure sensitive paint (BPSP). Cylindrical film cooling holes were located in the upstream and passage regions with the coolant-to-mainstream mass flow ratio (MFR) independently varied for each region. One row was located upstream of the vanes and supplied by the upstream plenum. Two rows were located in the passage between two vanes and supplied by the downstream plenum. Three total MFRs were investigated: 1%, 1.5%, and 2%. For a given total MFR, four upstream and downstream combinations were compared to an even split of coolant: +0.25% and -0.25%, +0.125% and -0.125%, -0.125% and +0.125%, and -0.25% and +0.25%. Coolant-to-mainstream density ratios (DRs) of 1.0 and 2.0 were investigated. The most efficient use of coolant hinged on balancing the downstream MFR for the second row due to the endwall pressure gradient preventing coolant from exiting or high jet velocity causing liftoff. For this row, selecting the optimum MFR increased effectiveness by up to 300%. Depending on the MFR, increasing the DR changed the effectiveness +/-65%.

Presenting Author: Lesley Wright Texas A&M University

Presenting Author Biography: N/A

Authors:

Timothy Burdett Texas A&M University
Izhar Ullah Texas A&M University
Lesley Wright Texas A&M University
Je-Chin Han Texas A&M University
John Mcclintic Honeywell Aerospace
Daniel Crites Honeywell Aerospace
Ardeshir Riahi Honeywell Aerospace