Gas turbine engine

A gas turbine engine comprising:

• a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a high pressure compressor defining a high pressure compressor exit area (AHPCExit) in square inches and having a stage count (NHPC) defined by a number of rows of rotating blades of the high-pressure compressor, the turbine section having a low pressure turbine comprising a stage count (NLPT) defined by a number of rows of rotating blades of the low-pressure turbine;
• a ducted fan driven by the turbomachine, the fan having a plurality of blades arranged in a single row and defining a blade tip diameter (D) in inches;
• a gearbox coupled to the low pressure turbine and the fan, the gearbox having a gear ratio (GR);
• and
• a ducted engine correlation parameter that is greater than or equal to 0.10 and less than or equal to 0.50, wherein the ducted engine correlation parameter equals 10*D/GR/NLPT2/NHPC;
• wherein the gas turbine engine defines a redline exhaust gas temperature (EGT) in degrees Celsius, a total sea level static thrust output (FnTotal) in 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/(AHPCExit2×1000).