Full coverage discrete hole film cooling - The influence of the number of holes and pressure loss
Abstract
Experimental measurements of the overall cooling effectiveness for full coverage discrete hole effusion cooling are presented for a wide range of practical geometries and for a density ratio between the coolant and combustion gases of 2.5. The influence of the number of holes per unit surface area was investigated at two fixed total hole areas or design pressure losses of 3 percent and 0.1 percent, at a relatively low coolant flow rate per unit of surface area. Hole configurations suitable for both combustor and turbine blade cooling were investigated with hole sizes from 1.4 to 0.6 mm at 3-percent design pressure loss and 1.3 to 3.3 mm at 0.1-percent design presure loss. The diameter change at a fixed pressure loss was for a constant total hole area with more holes as the size was reduced. This was shown to increase the cooling effectiveness through improved film cooling. Enlarging the hole size for a fixed number of holes and hence reducing the pressure loss for a fixed coolant mass flow was also shown to improve the cooling effectiveness through better film cooling.
- Publication:
-
ASME, 35th International Gas Turbine and Aeroengine Congress and Exposition
- Pub Date:
- June 1990
- Bibcode:
- 1990gatu.confR....A
- Keywords:
-
- Film Cooling;
- Holes (Mechanics);
- Pressure Drop;
- Turbine Engines;
- Combustible Flow;
- Combustion Chambers;
- Flow Geometry;
- High Temperature;
- Turbine Blades;
- Fluid Mechanics and Heat Transfer