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公开(公告)号：US20190002118A1
公开(公告)日：2019-01-03
申请号：US15635356
申请日：2017-06-28
CPC分类号： B64D33/04 , B64D27/16 , B64D29/06 , F02K1/70 , F02K1/72 , F02K1/763 , F02K1/766 , F02K3/06 , F05D2220/323 , F05D2260/50
摘要： A thrust reverser assembly and a method of operating an aircraft during a taxi mode of operation are provided. The thrust reverser assembly includes one or more actuator assemblies configured to modulate a position of a moveable portion over a continuous range of travel between a fully stowed position and a fully deployed position, such that an air flow through said thrust reverser bleed passage is correspondingly varied. The thrust reverser assembly also includes a throttle device that includes a first, ground idle power level position and a second, forward thrust mode position. Movement into the second position may be actuated separately and differently from movement into the first position. An actuator intermediate lock may inhibit actuation of the intermediate forward thrust mode of operation until a plurality of preconditions is met.
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公开(公告)号：US20230021836A1
公开(公告)日：2023-01-26
申请号：US17382467
申请日：2021-07-22
发明人： David Baker Riddle , Keith Edward James Blodgett , Timothy Richard DePuy , William Joseph Bowden
IPC分类号： B64D27/12
摘要： An aircraft includes a fuselage, a wing connected to and extending outward from the fuselage, and an engine mounted to the wing. The engine includes turbomachine defining a centerline axis, a fan, and an exhaust section with an outlet nozzle. The turbomachine defines a centerline axis. The fan is connected to and is disposed upstream from the turbomachine. The fan is disposed to rotate about the centerline axis. During operation of the engine, an exhaust stream is expelled from the outlet nozzle of the exhaust section. The exhaust stream defines a mean direction of flow in the downstream direction from the exhaust section. The mean direction of flow defines a first angle with the centerline axis of the turbomachine that is greater than zero such that the centerline axis is oriented downwardly along the vertical direction relative to the mean direction of flow of the exhaust stream.
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公开(公告)号：US10343786B2
公开(公告)日：2019-07-09
申请号：US15635356
申请日：2017-06-28
摘要： A thrust reverser assembly and a method of operating an aircraft during a taxi mode of operation are provided. The thrust reverser assembly includes one or more actuator assemblies configured to modulate a position of a moveable portion over a continuous range of travel between a fully stowed position and a fully deployed position, such that an air flow through said thrust reverser bleed passage is correspondingly varied. The thrust reverser assembly also includes a throttle device that includes a first, ground idle power level position and a second, forward thrust mode position. Movement into the second position may be actuated separately and differently from movement into the first position. An actuator intermediate lock may inhibit actuation of the intermediate forward thrust mode of operation until a plurality of preconditions is met.
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公开(公告)号：US20240060430A1
公开(公告)日：2024-02-22
申请号：US17889927
申请日：2022-08-17
CPC分类号： F01D25/24 , F01D25/28 , F05D2220/323 , F05D2240/14 , F05D2250/72 , F05D2250/38 , F05D2260/30
摘要： A gas turbine engine defining a radial direction, an axial direction, a circumferential direction, and a longitudinal axis is provided. The gas turbine engine includes: a fan rotatable about the longitudinal axis; a turbomachine; and a housing surrounding the turbomachine and having an upper outer surface portion and a lower outer surface portion, the housing defining a first distance extending radially from the longitudinal axis to a first point located at the upper outer surface portion, the housing further defining a second distance extending radially from the longitudinal axis to a second point located at the lower outer surface portion, and the second distance is greater than the first distance.
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公开(公告)号：US09810178B2
公开(公告)日：2017-11-07
申请号：US14818596
申请日：2015-08-05
CPC分类号： F02K1/78 , F01D25/24 , F01D25/30 , F02K1/00 , F02K1/06 , F02K1/08 , F02K1/09 , F02K3/06 , F05D2250/14
摘要： A turbofan exhaust nozzle includes: a conical inner shell disposed coaxially inside a surrounding outer shell to define an annular flow duct therebetween terminating in an outlet at a trailing edge of the outer shell and the inner shell terminates in a trailing edge aft of the outlet; and a pylon interrupting circumferentially the duct, wherein at least a portion of the trailing edge of the outer shell is vertically non-coplanar.
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公开(公告)号：US20240317412A1
公开(公告)日：2024-09-26
申请号：US18734223
申请日：2024-06-05
摘要： An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to: h/L.
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公开(公告)号：US10119495B1
公开(公告)日：2018-11-06
申请号：US15635384
申请日：2017-06-28
摘要： Thrust reverser assemblies and a method of operating an aircraft during a landing approach mode of operation are provided. The thrust reverser assembly includes a moveable portion that is moveable over a continuous range of travel between a fully stowed position and a fully deployed position. Movement away from the fully stowed position opens a bleed passage. An actuator assembly coupled to the moveable portion is operable in an intermediate forward thrust mode to modulate a position of the moveable portion along the continuous range of travel, such that an air flow through the bleed passage is correspondingly varied. A throttle device includes a first position associated with deployment of, and a second position associated with engagement of, the intermediate forward thrust mode of operation. A drag flap assembly may extend from the bleed passage during the intermediate forward thrust mode of operation.
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公开(公告)号：US12030652B2
公开(公告)日：2024-07-09
申请号：US17835280
申请日：2022-06-08
摘要： An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to:
h
L
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公开(公告)号：US20230399114A1
公开(公告)日：2023-12-14
申请号：US17835280
申请日：2022-06-08
摘要： An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to: h/L.
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公开(公告)号：US11840987B2
公开(公告)日：2023-12-12
申请号：US17713597
申请日：2022-04-05
发明人： Trevor Howard Wood , Kishore Ramakrishnan , Justin John Gambone, Jr. , Darren Lee Hallman , Thomas Malkus , Jixian Yao , Keith Edward James Blodgett
CPC分类号： F02K1/72 , F02K1/766 , F05D2220/323 , F05D2240/129 , F05D2240/14 , F05D2260/606
摘要： A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.
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