GAS TURBINE ENGINE

Abstract: a turbine engine includes: a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order, the compressor section having a hpc defining a hpc exit area (a) in square inches, the turbine section having a lpt; a fan; a gearbox; and a decp 0.10-0.50, where decp equals 10*d/gr/n/n, d is the fan blade tip diameter, gr is the gear ratio of the gearbox, nis the stage count of the lpt, and nis the stage count of the hpc. the gas turbine engine defines a redline exhaust gas temperature (egt) in degrees celsius, a total sea level static thrust output (fn) 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 determined as follows: fn�egt/(a�1000).

Inventor(s): Jeffrey Donald Clements, Daniel Alan Niergarth, Jeffrey S. Spruill, Erich Alois Krammer, Matthew Kenneth MacDonald, Scott Alan Schimmels

CPC Classification: F02K3/06 (JET-PROPULSION PLANTS (features of jet-propulsion plants common to gas-turbine plants, air intakes or fuel supply control of air-breathing jet-propulsion plants , ))

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