A detailed analysis of film-cooling physics: Part 4 -- Compound-angle injection with shaped holes

Journal Article · Sat Jan 01 04:00:00 EST 2000 · Journal of Turbomachinery

DOI:https://doi.org/10.1115/1.555419· OSTI ID:20086948

Brittingham, R A; Leylek, J H

The flow physics of film cooling with compound-angle shaped holes is documented for realistic gas turbine parameters. For the first time in the open literature, the combined effects of compound-angle injection and hole shaping are isolated and the dominant mechanisms are examined. Results provide valuable insight into the flowfield of this class of film-cooling jets. Computational and experimental results are presented for a row of holes injected at 35 degrees on a flat plate with three distinct geometric configurations: (1) streamwise injected cylindrical holes (reference case); (2) 15 degrees forward-diffused holes injected at a 60 degree compound angle; and (3) 12 degrees laterally diffused holes injected at a 45 degree compound angle. Detailed field and surface data, including adiabatic effectiveness ({eta}) and heat transfer coefficient (h), of the two compound-angle shaped holes are provided and compared to: (a) the reference streamwise cylindrical case; (b) results from Part 2 detailing the compound-angle flowfield for cylindrical holes; (c) results of Part 3 detailing the streamwise injected shaped-hole flowfield; and (d) experimental data. the 60 degrees compound-angle forward-diffused holes provided excellent lateral coolant distribution, but suffered from crossflow ingestion at the film-hole exit plane. The 45 degrees compound-angle lateral-diffused hole had much steeper lateral effectiveness variations. A previously documented and validated computational methodology was utilized. Computations were performed using a multiblock, unstructured-adaptive grid, fully implicit pressure-correction Navier-Stokes code with multigrid and underrelaxation type convergence accelerators.

• Research Organization: Clemson Univ., SC (US)
• Sponsoring Organization: US Department of Energy
• DOE Contract Number: FC21-92MC29061
• OSTI ID: 20086948
• Journal Information: Journal of Turbomachinery, Journal Name: Journal of Turbomachinery Journal Issue: 1 Vol. 122; ISSN JOTUEI; ISSN 0889-504X
• Country of Publication: United States
• Language: English

Related Subjects

32 ENERGY CONSERVATION, CONSUMPTION, AND UTILIZATION
CALCULATION METHODS
ENERGY EFFICIENCY
FILM COOLING
GAS FLOW
HEAT TRANSFER
PERFORMANCE
TURBINE BLADES