The present disclosure relates to a gas turbine engine and, more particularly, to a cooling architecture therefor.
Gas turbine engines, such as those that power modern commercial and military aircraft, generally include a compressor section to pressurize an airflow, a combustor section to burn a hydrocarbon fuel in the presence of the pressurized air, and a turbine section to extract energy from the resultant combustion gases.
Thermal loads within the gas turbine engine vary. Such variance may affect performance even within the bounds of material specifications.
USPTO Backgrounds
USPTO Backgrounds