| 摘要 |
With regard to cooling turbine blades in a gas turbine engine a compromise has to be made between convective cooling within the inner cavity (43) defining a flow path for coolant and the blow rates for developing film cooling on an outer surface of the aerofoil (39). By providing a chamber (46) between the flow cavity (43) and external apertures (49) reconciliation between the necessary flow rates for convective cooling within the cavity (43) defining the pathway for coolant flow within the aerofoil (39) and the necessary coolant blowing rate for film development can be achieved. |
