Patent ID: 11939925
Assignee: RTX CORPORATION
Field: Transport (Mechanical engineering)
Classification: CPC F  B  Y | IPC B  F

Claim 8:
9. A method for operating a gas turbine engine comprising:
generating thrust at least in part by operating a gas turbine engine core at a maximum temperature during a first mode of operation;
generating no thrust from said gas turbine engine core in a descent mode of operation; wherein the gas turbine engine has:
a core including a compressor section with a first compressor and a second compressor, a turbine section with 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 gas turbine engine; and
wherein the at least one additional mode of operation includes a cruise mode of operation and controlling by the controller a flow rate through the gas turbine engine such that a turbine inlet temperature of the second turbine is at a maximum 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 of the gas turbine engine in at least one of the takeoff mode of operations and the top of climb mode of operations.