US 12,392,290 B2
Gas turbine engine
Daniel Alan Niergarth, Norwood, OH (US); Jorge de Luis, Cincinnati, OH (US); Douglas Downey Turner, West Chester, OH (US); Michael Macrorie, Winchester, MA (US); Keith W. Wilkinson, Portsmouth, NH (US); Arthur William Sibbach, Boxford, MA (US); and Vincenzo Martina, Turin (IT)
Assigned to General Electric Company, Evendale, OH (US); and GE Avio S.r.l., Rivalta di Torino (IT)
Filed by General Electric Company, Evendale, OH (US); and GE Avio S.r.l., Rivalta di Torino (IT)
Filed on Mar. 18, 2025, as Appl. No. 19/083,171.
Application 19/083,171 is a continuation in part of application No. 18/976,748, filed on Dec. 11, 2024.
Application 18/976,748 is a continuation of application No. 18/650,586, filed on Apr. 30, 2024, granted, now 12,196,131, issued on Jan. 14, 2025.
Application 18/650,586 is a continuation in part of application No. 18/500,517, filed on Nov. 2, 2023, granted, now 12,078,107, issued on Sep. 3, 2024.
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, abandoned.
Prior Publication US 2025/0215829 A1, Jul. 3, 2025
Int. Cl. F02C 7/18 (2006.01)
CPC F02C 7/185 (2013.01) [F05D 2260/213 (2013.01)] 20 Claims
OG exemplary drawing
 
1. A gas turbine engine comprising:
a turbomachine comprising a stage of inlet guide vanes, 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 and the turbine section having a drive turbine defining a drive turbine exit area (ADTExit) in square inches, the turbomachine further comprising a drive turbine shaft coupled to the drive turbine;
wherein the gas turbine engine defines a maximum exhaust gas temperature (EGT) in degrees Celsius, a maximum drive turbine shaft torque (TOUT) in Newton meters, and a corrected specific power (CSP) in Newtons squared times degrees Celsius over meters squared, wherein the corrected specific power is determined as follows:

OG Complex Work Unit Math
wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91;
wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius;
wherein an overall pressure ratio for the compressor section is at least 15:1; and
wherein the gas turbine engine generates less than 2,000 horsepower at maximum rated power.