Internally cooled gas turbine aerofoil

摘要

Within aerofoils (50, 150, 250, 350), and in particular nozzle guide vane aerofoils in gas turbine engines problems can occur with regard to coolant flows (56, 57; 156, 157; 256, 257; 356, 357) from respective inlets at opposite ends of a cavity (60, 160, 260, 360) within the aerofoil (50, 150, 250, 350). The cavity (60, 160, 260, 360) generally defines a hollow core and unless care is taken coolant flow can pass directly across the internal cavity. Previously baffle plates were inserted within the cavity to prevent such direct jetting across the cavity. Such baffle plates are subject to additional costs as well as potential unreliability problems. Baffles (55, 155, 255, 355) formed integrally with a wall (54, 154, 254, 35) within the aerofoil (50, 150, 250, 350) allow more reliability with regard to positioning as well as consistency of performance. The baffles (55, 155, 255, 355) can be perpendicular, upward or downwardly orientated or have a compound angle.