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公开(公告)号：US11920539B1
公开(公告)日：2024-03-05
申请号：US17964097
申请日：2022-10-12
CPC分类号： F02K1/48 , F01D25/30 , F05D2220/323 , F05D2240/128 , F05D2260/96
摘要： An exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end. Each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root. At least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip. The inner wall extends along the first segment, the second segment, and third the segment. The first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment.
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公开(公告)号：US12055094B1
公开(公告)日：2024-08-06
申请号：US18171698
申请日：2023-02-21
摘要： An engine includes a fan section having an open fan defining an axial centerline and a rotor. The rotor includes a plurality of fan blades mounted to a hub and being rotatable about the axial centerline. The engine also includes a turbomachine downstream of the fan section. The turbomachine includes a core cowl that defines an engine inlet and encloses turbomachinery. Further, the engine includes an airflow diverting assembly downstream of the fan section and upstream of the engine inlet. The airflow diverting assembly includes at least one fluid passageway formed into at least a portion of the hub for diverting at least a portion of a boundary layer on a surface of the hub away from the surface of the hub to reduce distortion caused by the boundary layer in the turbomachinery.
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公开(公告)号：US20240280051A1
公开(公告)日：2024-08-22
申请号：US18171698
申请日：2023-02-21
摘要： An engine includes a fan section having an open fan defining an axial centerline and a rotor. The rotor includes a plurality of fan blades mounted to a hub and being rotatable about the axial centerline. The engine also includes a turbomachine downstream of the fan section. The turbomachine includes a core cowl that defines an engine inlet and encloses turbomachinery. Further, the engine includes an airflow diverting assembly downstream of the fan section and upstream of the engine inlet. The airflow diverting assembly includes at least one fluid passageway formed into at least a portion of the hub for diverting at least a portion of a boundary layer on a surface of the hub away from the surface of the hub to reduce distortion caused by the boundary layer in the turbomachinery.
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公开(公告)号：US20230167783A1
公开(公告)日：2023-06-01
申请号：US17539401
申请日：2021-12-01
IPC分类号： F02K1/46
CPC分类号： F02K1/46 , F05D2250/711 , F05D2250/712 , F05D2220/323 , F05D2240/128 , F05D2250/11 , F05D2250/75
摘要： A propulsion system is provided. The propulsion system defines a radial direction and includes a rotating element; a stationary element; an inlet assembly defining an inlet positioned between the rotating element and the stationary element and positioned inward of the stationary element along the radial direction, the inlet assembly comprising an inlet duct located downstream of the inlet; and a ducted fan comprising a plurality of fan blades positioned at least partially in the inlet duct; wherein the inlet duct divides into a first duct and a second duct separate from the first duct, wherein the first duct is a core duct downstream of the ducted fan, wherein the second duct is a fan duct downstream of the ducted fan, and wherein the second duct includes an exhaust nozzle having a plurality of chevrons disposed at an aft end of the exhaust nozzle to define an exhaust outlet.
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公开(公告)号：US20240229741A1
公开(公告)日：2024-07-11
申请号：US18428254
申请日：2024-01-31
CPC分类号： F02K1/48 , F01D25/30 , F05D2220/323 , F05D2240/128 , F05D2260/96
摘要： An exhaust nozzle for a gas turbine engine. The exhaust nozzle comprises a nozzle body having an upstream end axially spaced from a downstream end with respect to an axial centerline of the nozzle body, and a plurality of chevrons circumferentially spaced apart and extending downstream from the downstream end. Each chevron includes an inner wall radially spaced from an outer wall, a root and a tip axially spaced from the root. At least one chevron of the plurality of chevrons includes a first segment extending axially downstream from the root, a second segment extending axially downstream from the first segment, and a third segment extending axially downstream from the second segment to the tip. The inner wall extends along the first segment, the second segment, and third the segment. The first segment is distinguishable from the second segment and the second segment is distinguishable from the third segment.
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公开(公告)号：US11927134B1
公开(公告)日：2024-03-12
申请号：US18160375
申请日：2023-01-27
CPC分类号： F02C7/12 , F01D25/12 , F01D25/14 , F05D2220/323 , F05D2240/14 , F05D2260/213
摘要： A gas turbine engine is provided, having a turbomachine and a rotor assembly driven by the turbomachine and operable at a first blade passing frequency (f1) greater than or equal to 2,500 hertz and less than or equal to 5,000 hertz during a high power operating condition; a heat exchanger positioned within an annular duct and extending substantially continuously along the circumferential direction, wherein an effective transmission loss (ETL) for the heat exchanger positioned within the annular duct is between 5 decibels and 1 decibels for a high power operating condition, and wherein the heat exchanger comprises a heat transfer section defining an acoustic length (Li), and wherein an Operational Acoustic Reduction Ratio (OARR) is greater than or equal to 0.75 to achieve the ETL at the high power operating condition, the OARR equal to:
sin
(
2
×
π
×
f
1
a
1
×
L
i
)
2
wherein a1 is equal to 13,200 inches per second during the high power operating condition.
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