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公开(公告)号：US20210207531A1
公开(公告)日：2021-07-08
申请号：US17206073
申请日：2021-03-18
发明人： Michael P. O'Brien
摘要： A system and method of an airflow control system for a vehicle is described herein. The airflow control system (100) includes an airflow housing (120) defining an airflow passageway (125) extending between a bypass opening (122) and an intake outlet (124). The airflow housing also defines a duct opening (126) positioned between the bypass opening (122) and the intake outlet (124). The intake outlet (124) may be in fluid communication with an engine intake (12) of the vehicle such that air passes from the bypass opening (122) and/or the duct opening (126) to the engine intake (12). The airflow control system (100) also includes a movable duct (160) movably connected to the airflow housing (120) to selectively allow or prevent air passage through the duct opening (126) and into the engine intake (12), and further includes a bypass door (140) movably connected to the airflow housing (120) to selectively allow or prevent air passage through the bypass opening (122) and into the engine intake (12).
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公开(公告)号：US11053018B2
公开(公告)日：2021-07-06
申请号：US16019720
申请日：2018-06-27
申请人： Raytheon Company
发明人： Timothy F. O'Brien
摘要： An inlet for a flight vehicle engine, such as for a supersonic or hypersonic engine, includes an internal flow diverter to divert boundary layer flow. The flow diverter is configured to minimize disruption to flow outside the diverted boundary by being configured through use of a flow field that is also used to configure the walls of the inlet. The flow field that is used to configure an inlet-creating shape and a diverter-creating shape has the same flow generator, contraction ratio, compression ratio, mass capture ratio, pressure ratio between entrance and exit, and/or Mach number, for example. The internal diverter may be configured so as to allow arbitrary selection of a leading edge shape for the internal diverter, for example to use a shape that helps avoid radar detection.
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93.发明授权公开(公告)号：US11047339B2
公开(公告)日：2021-06-29
申请号：US16103329
申请日：2018-08-14
申请人： ROLLS-ROYCE plc
摘要： An aircraft gas turbine engine comprises a fan coupled to a fan drive turbine, the fan being configured to provide a bypass flow (B) and a core flow (A) in use. The engine includes a reduction gearbox which couples the fan to the fan drive turbine and a core compressor arrangement. The core compressor arrangement has a core inlet at an upstream end of a core gas flow passage (A) defined by radially inner and outer walls, and at least a first compressor rotor blade provided at an upstream end of the compressor arrangement. The radially inner wall of the core inlet defines a first diameter (DINLET), and a root leading edge of the first compressor rotor blade defines a second diameter (DCOMP). A first ratio (DINLET:DCOMP) of the first diameter (DCOMP) to the second diameter (DCOMP) is greater than or equal to 1.4.
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公开(公告)号：US20210189959A1
公开(公告)日：2021-06-24
申请号：US16719096
申请日：2019-12-18
发明人： Thomas Oliver HUDSON
摘要： Aspects of the invention regard an aircraft including: a gas turbine engine, the gas turbine engine including an intake, a nacelle, and gas turbine engine components located radially inside the nacelle; and an aircraft structure. The intake of the gas turbine engine is mounted to the aircraft structure in a manner such that its position can be adjusted. The nacelle and the gas turbine engine components located radially inside the nacelle are rigidly mounted to the aircraft structure. Other aspects of the invention regard a gas turbine engine and a method for adjusting the input of air flowing into a gas turbine engine.
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公开(公告)号：US11040767B2
公开(公告)日：2021-06-22
申请号：US15860280
申请日：2018-01-02
发明人： Trevor Howard Wood , Kishore Ramakrishnan , Davide Giacché , Angela Knepper , Nicholas Bown , Rathakrishnan Bhaskaran
摘要： An aircraft assembly includes an engine, and intake, and a propeller assembly. The engine is mounted to at least one of a wing or fuselage of an aircraft. The intake is configured to provide air to the engine. The intake includes a body having an engine inlet through which air enters the intake. The propeller assembly includes propeller blades coupled to and driven by the engine. The propeller assembly is spaced an axial distance from the inlet opening of the intake wherein air passing by the propeller blades enters the intake. The propeller assembly has a propeller configuration that is at least one of sized or shaped to optimize performance of the propeller assembly based on an interaction between the propeller assembly and the intake.
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公开(公告)号：US20210179393A1
公开(公告)日：2021-06-17
申请号：US17188520
申请日：2021-03-01
申请人： Safran Nacelles
发明人： Patrick BOILEAU
摘要： A handling assembly of a propulsion assembly includes a nacelle and an aircraft turbojet engine. The handling assembly also includes a handling envelope covering at least half of the circumference of an outer wall of an air inlet of the nacelle, when the propulsion assembly is mounted on said handling assembly, and at least two interfaces for attaching slings, the slings being connected to a hoisting system which is external to said handling assembly. A method for handling a propulsion assembly is also disclosed.
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公开(公告)号：US20210179284A1
公开(公告)日：2021-06-17
申请号：US16893894
申请日：2020-06-05
申请人： Zhenkun Wang
发明人： Zhenkun Wang
摘要： This instant invention provides an airplane design mainly to eject rearward the high-speed exhaust gas from the engine of the airplane to flow through the upper surface of the wing, such that the forward propulsion forcing can be obtained via rearward ejecting the high-speed exhaust gas to push the air rearward, and also larger uplift forcing induced by a larger velocity difference vertically across the wing can be obtained to ascend the airplane at the same time. This velocity difference is generated because the air over the wing is accelerated by the ejected high-speed exhaust gas, but the air below the wing stays the same velocity, such that a bigger velocity difference is directly produced vertically across the wing, and thus more uplift forcing can be provided to ascend the airplane.
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公开(公告)号：US11034460B2
公开(公告)日：2021-06-15
申请号：US15836034
申请日：2017-12-08
申请人： The Boeing Company
发明人： Zachary B. Renwick , Brandon L. Bertolucci , Eric Herrera , Michael William Hayes , John C. Waldrop, III , Matthew Scott Thompson
IPC分类号： B64D33/02 , B33Y80/00 , B33Y10/00 , G10K11/172 , B29C64/106 , B29D99/00 , B33Y30/00 , G10K11/168 , B29K701/12 , B29L7/00
摘要： Systems and methods are provided for septa for acoustic cells. One embodiment is a method that includes fabricating a septum of a cell of an acoustic panel, by heating a material into a molten material, depositing the molten material to form a lower chamber of the septum that extends vertically upwards and includes an entry, iteratively depositing layers of the molten material, each layer comprising a filament at the entry that includes overhangs with respect to vertically adjacent layers, and forming openings at locations of the overhangs.
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公开(公告)号：US11028774B2
公开(公告)日：2021-06-08
申请号：US16321426
申请日：2017-07-28
申请人： SAFRAN
发明人： Nicola Piccirelli
摘要： An acoustic panel for a turbomachine, in particular for an aircraft, includes two skins that are substantially parallel and between which extend cavities forming Helmholtz resonators, one of the skins being perforated by orifices opening into the cavities and forming necks of the Helmholtz resonators, vibrating masses being provided in at least some of the cavities and connected to cavity walls by an elastic junction housed in the cavity.
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公开(公告)号：US20210163147A1
公开(公告)日：2021-06-03
申请号：US17267797
申请日：2019-08-06
发明人： Laurent FAYOLLE , Guillaume GALZIN
摘要： The invention relates to a system for cooling a fluid of a circuit (20) for lubricating a propulsion engine (10) of an aircraft, the engine comprising a nacelle (11) which extends in a longitudinal direction (X) between an air inlet opening (12) and an ejection nozzle (13), a turbomachine (14) having a casing (15) secured inside said nacelle by rectifier arms (16), and a fan (17) arranged at said air inlet opening (12) of said nacelle, upstream of said turbomachine (14), and designed to be able to generate a primary air flow feeding said turbomachine and a secondary air flow feeding a channel, referred to as a secondary channel (18), formed between said nacelle (11) and said casing (15) of said turbomachine, characterized in that said cooling system comprises a skin exchanger (30) which is arranged on an inner wall of said nacelle (11), longitudinally between said air inlet opening (12) of said nacelle and said rectifier arms (16), said skin exchanger being in fluid communication with said fluid circuit and designed to be able to provide heat exchanges between said lubricating fluid and the air flowing through said secondary channel.
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