General Electric Company

Matthew Kenneth MacDonald

Jeffrey Donald Clements

Scott Alan Schimmels

Erich Alois Krammer

Jeffrey S Spruill

Daniel Alan Niergarth

Nicholas Joseph Kray

Arthur William Sibbach

A gas turbine engine is provided. The 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; wherein 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).

Gas turbine engine

Growing community of inventors

Austin, TX, United States of America

Matthew Kenneth MacDonald