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
• a component within the turbomachine, wherein the component has a coating on an external surface of the component that is exposed to a hot gas flow path in the turbomachine, and wherein the coating comprises:
• cobalt, chromium, aluminum, yttrium, and nickel,
• 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).