Abstract: A gas turbine engine includes a fan section, a heat exchanger, and inlet door. The fan section is configured to generate an airflow. The heat exchanger is configured to transfer heat from a thermal management system to the airflow. The inlet door is configured to modulate the airflow to the heat exchanger.

Abstract: A gas turbine engine includes a fan section, a heat exchanger, and inlet door. The fan section is configured to generate an airflow. The heat exchanger is configured to transfer heat from a thermal management system to the airflow. The inlet door is configured to modulate the airflow to the heat exchanger.

Abstract: A hybrid-electric aircraft propulsion system includes a gas turbine engine and an electrical assembly. The gas turbine engine includes a first rotational assembly. The first rotational assembly is rotatable about a rotational axis of the gas turbine engine. The first rotational assembly includes a first shaft, a bladed first compressor rotor, and a bladed first turbine rotor. The first shaft interconnects the bladed first compressor rotor and the bladed first turbine rotor. The electrical assembly includes a first motor-generator, a first motor control unit, a motor-generator (MG) cooling system, and a motor control unit (MCU) cooling system. The first motor-generator is coupled to the first shaft. The first motor control unit is electrically connected to the first motor-generator. The MG cooling system is connected in fluid communication with the first motor-generator. The MCU cooling system is connected in fluid communication with the first motor control unit.

Abstract: A fan is disposed at an intake of a nacelle, and a gas turbine is contained within a first portion of the nacelle. The gas turbine includes compressor, combustor, and turbine stages through which a core stream of gas passes past the fan and past the compressor, combustor, and turbine stages. A first heat exchanger is disposed in a second portion of the nacelle, where a fan stream passes through the second portion of the nacelle. A first switching valve receives gas from the fan stream and directs the received gas to a second switching valve or the turbine stage. The second switching valve directs gas to a boost compressor and receives gas from the first switching valve or a high pressure bleed from the compressor stage. A third switching valve receives gas from the boost compressor and directs compressed gas to the first heat exchanger or the turbine stage.