The paper discusses heat transfer analysis carried out to estimate steady state and transient thermal response of aero gas turbine Convergent-Divergent (CD) nozzle flaps. Empirical correlations available in literature were used to estimate the convective heat transfer coefficients, film cooling effectiveness and adiabatic wall temperatures. A cooling design model based on one dimensional (ID) heat transfer was used to estimate the cooling flow requirement to maintain the nozzle flap temperatures within safe limit. Detailed three dimensional (3D) steady state finite element heat transfer analysis was carried out on nozzle flaps for life estimation, growth calculation and weight optimization studies. Three dimensional transient finite element heat transfer analysis was also carried out to estimate the thermal response of nozzle flaps.
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