Gas turbine engine

A gas turbine engine comprising:

• a turbomachine comprising a compressor section having a high-pressure compressor, a combustion section, and a turbine section having a high-pressure turbine arranged in serial flow order, the turbomachine includes an engine core including the high-pressure compressor, the combustion section, and the high-pressure turbine, the engine core having a length (LCORE) in inches, the high-pressure compressor having an exit stage diameter (DCORE) in inches, the high-pressure compressor defining a high-pressure compressor exit area (AHPCExit) in square inches, and the high-pressure compressor including a high-pressure compressor flowpath and a plurality of stages of high-pressure compressor rotor blades and high-pressure compressor stator vanes, 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);
• a power turbine in flow communication with the high-pressure turbine;
• a low-pressure shaft coupled to the power turbine;
• and
• a high-pressure shaft coupled to the high-pressure compressor and the high-pressure turbine, the high-pressure shaft characterized by a high-speed shaft rating (HSR) from 1.5 to 6.2, and a ratio of LCORE/DCORE is from 2.1 to 4.3, wherein HSR is given by:
• HSR
• =
• 1
• k
• *
• N
• ⁢
• 2
• R
• /
• L
• *
• D
• CORE
• *
• (
• L
• CORE
• D
• CORE
• )
• 2
• ,
• where N2R/L is a redline speed of the high-pressure shaft in RPM, and k is a constant with a value of 106 inch-RPM.