Descent operation for an aircraft parallel hybrid gas turbine electric propulsion system

An aircraft including a gas turbine engine comprising:

• a core including a compressor section having a first compressor and a second compressor, a turbine section having a first turbine and a second turbine, and a primary flowpath fluidly connecting the compressor section and the turbine section;
• the first compressor is connected to the first turbine via a first shaft;
• the second compressor is connected to the second turbine via a second shaft;
• a motor connected to the first shaft such that rotational energy generated by the motor is translated to the first shaft;
• wherein the gas turbine engine includes a takeoff mode of operation, a top of climb mode of operation, and at least one additional mode of operation;
• a controller configured to control the mode of operation of the at least one gas turbine engine;
• and
• wherein the at least one additional mode of operation includes a cruise mode of operation and a geometry of the gas turbine engine is physically sized such that a turbine inlet temperature of the second turbine is at a maximum temperature for the top of climb mode of operations while said engine is in said cruise mode of operation, and wherein the maximum turbine inlet temperature corresponds to a maximum thrust output of the core and the maximum thrust output of the core is less than an aircraft thrust requirement on the gas turbine engine in at least one of the takeoff mode of operations and the top of climb mode of operations.