Turbine blades mounted to a rotating disc in a gas turbine engine are exposed to a gas stream that is at [infinity] = 1100°C and
maintains a convection coefficient of 250 W/m2·K over the blade. The blades, which are fabricated from Inconel, 20 W/m·K, have a length of 50 mm. The blade profile has a uniform cross-sectional area of 6 × 10-4 m2 and a perimeter of 110 mm. 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 300°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?
<u><em>solution is attached in word form due to error in mathematical equation. furthermore i also attach Screenshot of solution in word due to different version of MS Office please find the attachmen</em></u>t
