US 12,078,107 B2
Gas turbine engine
Daniel Alan Niergarth, Norwood, OH (US); Jeffrey Donald Clements, Mason, OH (US); Jeffrey S. Spruill, Hillsboro, OH (US); Erich Alois Krammer, West Chester, OH (US); Matthew Kenneth MacDonald, Austin, TX (US); and Scott Alan Schimmels, Miamisburg, OH (US)
Assigned to General Electric Company, Cincinnati, OH (US)
Filed by General Electric Company, Schenectady, NY (US)
Filed on Nov. 2, 2023, as Appl. No. 18/500,517.
Application 18/500,517 is a continuation of application No. 18/481,515, filed on Oct. 5, 2023.
Application 18/481,515 is a continuation in part of application No. 17/978,629, filed on Nov. 1, 2022.
Prior Publication US 2024/0254922 A1, Aug. 1, 2024
This patent is subject to a terminal disclaimer.
Int. Cl. F02C 7/00 (2006.01); F02C 3/113 (2006.01); F02C 6/20 (2006.01); F02C 7/18 (2006.01); F02K 3/065 (2006.01); F02K 3/115 (2006.01)
CPC F02C 7/185 (2013.01) [F02C 3/113 (2013.01); F02C 6/206 (2013.01); F02K 3/065 (2013.01); F02K 3/115 (2013.01)] 20 Claims
OG exemplary drawing
 
1. 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;
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).