Full coverage discrete hole wall cooling - Cooling effectiveness
Abstract
The development of a test facility for investigating full coverage discrete hole wall cooling for gas turbine combustion chamber wall cooling is described. A low temperature test condition of 750 K mainstream temperature and 300 K coolant temperature was used to investigate the influence of coolant flow rate at a constant cross flow Mach number. Practical combustion conditions of 2100 K combustor temperature and 700 K coolant temperature are investigated to establish the validity of applying the low temperature results to practical conditions. For both situations a heat balance programme, taking into account the heat tranfer within the wall was used to compute the film heat transfer coefficients. The mixing of the coolant air with the mainstream gases was studied through boundary layer temperature and CO2 profiles. It was shown that entrainment of hot flame gases between the injection holes resulted in a very low 'adiabatic' film cooling effectiveness.
- Publication:
-
29th International Gas Turbine Conference and Exhibit
- Pub Date:
- June 1984
- Bibcode:
- 1984gatu.confS....A
- Keywords:
-
- Boundary Layer Combustion;
- Heat Transfer Coefficients;
- Porous Walls;
- Sweat Cooling;
- Turbine Blades;
- Wall Temperature;
- Aerodynamics;
- Film Cooling;
- Mach Number;
- Mass Flow Rate;
- Thick Plates;
- Fluid Mechanics and Heat Transfer