Turbine blades mounted to a rotating disc in a gas turbine engine are exposed to a gas stream that is at T infinity =1200 deg. C and maintains a convection coefficient of h=250W/m 2 K over the blade....

Turbine blades mounted to a rotating disc in a gas turbine engine are exposed to a gas stream that is at T infinity =1200 deg. C and maintains a convection coefficient of h=250W/m 2 K over the blade. The blades, which are fabricated from Inconel, k=6*10 -4 m 2 and a perimeter of P=110mm. A proposed blade-cooling scheme, which involves routing air through the supporting disc, is able ot maintain the base of each blade at a temperature of T b =300 deg. C. A. If the maximum allowable blade temperature is 1050 deg. C and the blade tip may be assumed to be adiabatic, is the proposed cooling scheme satisfactory? B. For the proposed heating scheme, what is the rate at which heat is transferred from each blade to the coolant? Please show all work! Thank you!