GAS TURBINE ENGINE

Abstract: a gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section, the compressor section having a high-pressure compressor defining a high-pressure compressor exit area (a) in square inches. the high-pressure compressor includes a high-pressure compressor flowpath and a plurality of stages. a bleed system includes a plurality of bleed flowpaths that direct compressed air from the high-pressure compressor flowpath. at least two of the bleed flowpaths are at successive stages of the plurality of stages. 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): Daniel Alan NIERGARTH, Jeffrey Donald CLEMENTS, 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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