-
公开(公告)号：US20240280049A1
公开(公告)日：2024-08-22
申请号：US18650586
申请日：2024-04-30
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Daniel Alan Niergarth , Jorge de Luis , Douglas Downey Turner , Michael Macrorie , Keith W. Wilkinson , Arthur William Sibbach , Vincenzo Martina
CPC classification number: F02C6/06 , F02C7/185 , F05D2260/213
Abstract: A gas turbine engine is provided having 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 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:
(
T
O
U
T
A
D
T
E
x
i
t
)
2
*
E
G
T
A
H
P
C
E
x
i
t
*
1
0
-
1
1
;
wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.-
公开(公告)号：US12196131B2
公开(公告)日：2025-01-14
申请号：US18650586
申请日：2024-04-30
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Daniel Alan Niergarth , Jorge de Luis , Douglas Downey Turner , Michael Macrorie , Keith W. Wilkinson , Arthur William Sibbach , Vincenzo Martina
Abstract: A gas turbine engine is provided having 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 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: ( T O U T A D T E x i t ) 2 * E G T A H P C E x i t * 1 0 - 1 1 ; wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.
-
公开(公告)号：US20250146442A1
公开(公告)日：2025-05-08
申请号：US18802001
申请日：2024-08-13
Applicant: GE Avio S.r.l.
Inventor： Vincenzo Martina , Lucia Azzini , Daniele Coutandin
Abstract: An aircraft system is provided. The aircraft system includes: a gas turbine engine; a fuel system having a fuel tank and a fuel delivery system fluidly connecting the fuel tank to the gas turbine engine; an electric drive assembly including a component module; and a thermal management system including: a thermal fluid loop; a heat source heat exchanger in thermal communication with the component module and the thermal fluid loop; an airflow heat sink heat exchanger in thermal communication with the thermal fluid loop and further configured to be in thermal communication with a cooling airflow during operation of the gas turbine engine; and a fuel heat sink heat exchanger in selective thermal communication with the thermal fluid loop, the fuel tank, or both, the fuel heat sink heat exchanger in fluid communication with the fuel tank independently of the fuel delivery system during at least a first operating condition.
-
公开(公告)号：US20250101919A1
公开(公告)日：2025-03-27
申请号：US18976748
申请日：2024-12-11
Applicant: General Electric Company , GE Avio S.r.l.
Inventor： Daniel Alan Niergarth , Jorge de Luis , Douglas Downey Turner , Michael Macrorie , Keith W. Wilkinson , Arthur William Sibbach , Vincenzo Martina
Abstract: A gas turbine engine is provided having 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 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: ( T OUT A DTExit ) 2 * EGT A HPCExit * 1 0 - 1 1 ; wherein CSP is greater than 0.0001194×EGT2−0.103×EGT+22.14 and less than 0.0003294×EGT2−0.306×EGT+77.91; and wherein EGT is greater than 525 degrees Celsius and less than 1250 degrees Celsius.
-
-
-
Search Results
4
records
(took 0.011 seconds)
