Gas turbine engine

A method of operating a gas turbine engine, comprising:

• operating the gas turbine engine at a takeoff power level, the gas turbine engine having a turbomachine with a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches, the gas turbine engine defining a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) greater than or equal to 25,000 pounds and less than or equal to 45,000 pounds, and a corrected specific thrust;
• wherein the corrected specific thrust is greater than or equal to 42 and less than or equal to 90, the corrected specific thrust determined as follows:
• FnTotal×EGT/(AHPCExit×1000),
• wherein the gas turbine engine further comprises a primary fan comprising at least 18 fan blades and up to 26 fan blades, a fan duct enclosing the fan blades, and a gear assembly, the turbomachine drivingly coupled to the primary fan across the gear assembly, the gear assembly defining a gear ratio between 3.0 and 4.5,
• wherein the compressor section comprises a high pressure compressor with a total of at least eight and up to nine stages of high pressure compressor rotor blades and a low pressure compressor with a total of at least three and up to four stages of low pressure compressor rotor blades.