GAS TURBINE ENGINE

Abstract: a gas 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 high pressure compressor defining a high pressure compressor exit area (a) in square inches; a fan; a gearbox; and an engine correlation parameter of 0.17-0.83, where the engine correlation parameter equals d/n/gr, d is the blade tip diameter measured in feet, n is the stage count of the low-pressure turbine, and gr is the gear ratio of the gearbox. 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): Timothy Richard DePuy, Trevor Goerig, Jeffrey Donald Clements, Syed Arif Khalid, Daniel Alan Niergarth, Jeffrey S. Sprull, Erich Alois Krammer, Matthew Kenneth MacDonald, Scott Alan Schimmels

CPC Classification: F02C7/18 (GAS-TURBINE PLANTS; AIR INTAKES FOR JET-PROPULSION PLANTS; CONTROLLING FUEL SUPPLY IN AIR-BREATHING JET-PROPULSION PLANTS (construction of turbines ; jet-propulsion plants ; construction of compressors or fans ; generating combustion products of high pressure or high velocity ; using gas turbines in compression refrigeration plants ))

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