公开(公告)号：US20250163868A1

公开(公告)日：2025-05-22

申请号：US19033042

申请日：2025-01-21

Applicant: General Electric Company

Inventor： Daniel Alan NIERGARTH ,  Jeffrey Donald CLEMENTS ,  Jeffrey S. SPRUILL ,  Erich Alois KRAMMER ,  Matthew Kenneth MACDONALD ,  Scott Alan SCHIMMELS

IPC: F02K3/06

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 (AHPCExit) 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 (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 determined as follows: FnTotal×EGT/(AHPCExit2×1000).

公开(公告)号：US20240218828A1

公开(公告)日：2024-07-04

申请号：US18481515

申请日：2023-10-05

Applicant: General Electric Company

Inventor： Daniel Alan NIERGARTH ,  Jeffrey Donald CLEMENTS ,  Jeffrey S. SPRUILL ,  Daniel Endecott OSGOOD ,  Erich Alois KRAMMER ,  Matthew Kenneth MACDONALD ,  Scott Alan SCHIMMELS

IPC: F02C6/06 ,  F02C7/18

CPC classification number: F02C6/06 ,  F02C7/185 ,  F05D2260/213

Abstract: 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 (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 determined as follows: FnTotal×EGT/(AHPCExit2×1000).