Turbine blades mounted to a rotating disc in a gas turbine engine are exposed to a gas stream that is at T=1200C and maintains a convection coefficient of h=200W/m2K over the blade. The blades, which are fabricated from Inconel, k20W/mK, have a length of L=50mm. The blade profile has a uniform cross-sectional area of Ac=6104m2 and a perimeter of P=110mm. A proposed blade-cooling scheme, which involves routing air through the supporting disc, is able to maintain the base of each blade at a temperature of Tb=300C (a) If the maximum allowable blade temperature is 1050C 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 rate at which heat is transferred from each blade to the coolant, W? qb= W