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,
• the turbomachine further comprising:
• a rotor,
• an array of rotor blades extending radially outward from a flowpath surface of the rotor, wherein the individual ones of the array of rotor blades have a root, a tip, a leading edge, and a trailing edge, and
• an array of splitter blades alternating with the rotor blades, wherein individual ones of the array of splitter blades have a root, a tip, a leading edge, and a trailing edge;
• wherein both a chord dimension of the individual ones of the splitter array of splitter blades at the roots thereof and a span dimension of individual ones of the array of splitter blades are less than corresponding dimensions of the rotor blades;
• 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).