Turbine blades mounted to a rotating disc in a gas turbine engine are exposed to a gas stream that is at T1200°C and maintains a convection coefficient of h =250

W/m K over the blade. The blades, which are fabricated from Inconel, k =20 W/m · K, have a length of L = 50 mm. The blade profile has a uniform cross-sectional area of A, = 6 x10 m² and a perimeter of P = 110 mm. A proposed blade-cooling scheme, which involves routing air through the supporting disc, is able to maintain the each blade at a temperature of T = 300°C (a) If the maximum allowable blade tempera1050°C and the blade tip may be assumed to be adiabatic, is the proposed cooling scheme satisfactory? (b) For the proposed cooling scheme, what is the fate which heat is transferred from each blade to the coolant?