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;
• a first stage of composite airfoils having a first airfoil comprising:
• a first composite body extending chordwise from a first body leading edge to a first body trailing edge;
• a first leading edge protector having a first protector leading edge different from, and receiving at least a portion of, the first body leading edge,
• wherein a first leading length (FLL) extends chordwise from the first protector leading edge to a first end of the first leading edge protector, and a first chord length (FCL) extends chordwise from the first protector leading edge to the first body trailing edge;
• and
• a second stage of composite airfoils downstream of the first stage of composite airfoils and having a second airfoil comprising:
• a second composite body extending chordwise from a second body leading edge to a second body trailing edge;
• a second leading edge protector having a second protector leading edge different from, and receiving at least a portion of, the second body leading edge,
• wherein a second leading length (SLL) extends chordwise from the second protector leading edge to a second end of the second leading edge protector, and a second chord length (SCL) extends chordwise from the second protector leading edge to the second body trailing edge;
• and
• wherein the gas turbine engine defines a stage protection factor (SPF, wherein
• SPF
• =
• (
• FLL
• /
• FCL
• )
• (
• SLL
• /
• SCL
• )
• and SPF is greater than or equal to 0.7 and less than or equal to 4 (0.7<SPF<4),
• 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).