Turbine engine with inverse Brayton cycle

An engine system of an aircraft, the engine system comprising:

• a turbine engine comprising a compressor section, a combustor section having a burner, a turbine section, and a nozzle in an open-loop configuration configured to produce thrust for the aircraft, wherein the compressor section and the turbine section are mechanically coupled by a first shaft;
• a bottoming-cycle apparatus;
• an exhaust heat exchanger downstream of the turbine section of the turbine engine configured to reject heat from the turbine engine to the bottoming-cycle apparatus and create a cooled turbine exhaust stream in the turbine engine from a turbine exhaust stream of the turbine section;
• an exhaust compressor arranged downstream of the exhaust heat exchanger and upstream of an inlet of the nozzle of the turbine engine configured to compress the cooled turbine exhaust stream and increase a pressure of the cooled turbine exhaust stream prior to exiting the nozzle of the turbine engine;
• a motor configured to drive rotation of the exhaust compressor;
• and
• a controller configured to control an electric power input into the motor to regulate one or more parameters of the turbine engine or the bottoming-cycle apparatus.