During transient operation, the steel nozzle of a rocket engine must not exceed a maximum allowable operating temperature of 1500 K when exposed to combustion gases characterized by a temperature of 2300 K and a convection coefficient of 5000 W/m²K. To extend the duration of engine operation, it is proposed that a ceramic thermal barrier coating (k = 10 W/m-K, a = 6 x 10-6 m²/s) be applied to the interior surface of the nozzle. (a) If the ceramic coating is 10 mm thick and at an initial temperature of 300 K, obtain a conservative estimate of the maximum allowable duration of engine operation, in s. The nozzle radius is much larger than the combined wall and coating thickness. (b) Determine the inner (x = 0) and outer(x = L) surface temperatures, in °C, of the coating at time t = 30 seconds.
During transient operation, the steel nozzle of a rocket engine must not exceed a maximum allowable operating temperature of 1500 K when exposed to combustion gases characterized by a temperature of 2300 K and a convection coefficient of 5000 W/m²K. To extend the duration of engine operation, it is proposed that a ceramic thermal barrier coating (k = 10 W/m-K, a = 6 x 10-6 m²/s) be applied to the interior surface of the nozzle. (a) If the ceramic coating is 10 mm thick and at an initial temperature of 300 K, obtain a conservative estimate of the maximum allowable duration of engine operation, in s. The nozzle radius is much larger than the combined wall and coating thickness. (b) Determine the inner (x = 0) and outer(x = L) surface temperatures, in °C, of the coating at time t = 30 seconds.
Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)
8th Edition
ISBN:9781305387102
Author:Kreith, Frank; Manglik, Raj M.
Publisher:Kreith, Frank; Manglik, Raj M.
Chapter8: Natural Convection
Section: Chapter Questions
Problem 8.13P
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