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公开(公告)号：US12030660B2
公开(公告)日：2024-07-09
申请号：US17314178
申请日：2021-05-07
发明人： Reda R. Mankbadi
摘要： Systems and methods for noise suppression for aircraft are disclosed. The aircraft may include a fuselage. The aircraft may include a plurality of wings connected to or formed with the fuselage. The aircraft may include at least one engine configured to generate a propulsion force to propel the aircraft. The at least one engine may include a nozzle assembly having a nozzle body with an outlet that releases an exhaust air or a jet flow. The aircraft may include a noise suppression assembly. The noise suppression assembly may be configured to interact with the exhaust air or jet flow to substantially suppress, mitigate, reduce, or otherwise modify noise generated by the aircraft.
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公开(公告)号：US11685507B2
公开(公告)日：2023-06-27
申请号：US16555144
申请日：2019-08-29
发明人： Alain Porte , Jacques Lalane
摘要： A sound-absorbing panel includes: an inner skin traversed by holes and intended to be oriented towards a channel in which a fluid flows, a heating mat formed by strips fixed to the inner skin on the side opposite to the channel and oriented in a first direction, wherein two adjacent strips are distant from each other in order to define a slot between them, a base fixed to the strips on the side opposite to the inner skin, wherein the base includes, on the strips side, grooves extending in a second direction different from the first direction and wherein the base has, between two successive grooves, a rib, a cellular core fixed to the base on the side opposite to the strips, and an outer panel fixed to the cellular core on the side opposite to the base.
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公开(公告)号：US11542845B2
公开(公告)日：2023-01-03
申请号：US16674647
申请日：2019-11-05
发明人： Dana Tomescu , Daniel Alecu
IPC分类号： F01M11/04 , F01D25/20 , F01M11/02 , F01M1/02 , B64D33/00 , F02C7/06 , F01M1/20 , F01M11/00 , B64D27/10
摘要： A lubrication system for an aircraft engine includes an engine lubricant tank including at least a supply port hydraulically connectable to the aircraft engine, a lubricant makeup port, and an overfill port, an auxiliary lubricant tank, a lubricant makeup conduit hydraulically connecting the auxiliary lubricant tank to the lubricant makeup port. The lubricant makeup conduit includes a pump operable to move lubricant from the auxiliary lubricant tank to the lubricant makeup port, and an overfill conduit hydraulically connecting the overfill port to the auxiliary lubricant tank. A method of operating a lubrication system of an aircraft engine of an aircraft is also disclosed.
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公开(公告)号：US11370556B2
公开(公告)日：2022-06-28
申请号：US16575707
申请日：2019-09-19
发明人： Zubair Ahmed Baig , Sorin Bengea , Gary L. Miles
摘要： A power system of an aircraft includes a hybrid energy storage system with at least two energy storage subsystems each having a different power-energy density, power draw characteristics and/or dissimilar configuration. A primary power unit includes an aircraft engine coupled to an electric motor and a first generator. A secondary power unit is coupled to a second generator. A bidirectional power converter is coupled to the hybrid energy storage system and one or more controllers of the electric motor, the first generator, and the second generator. A power management controller is configured to interface with the hybrid energy storage system and the one or more controllers of the electric motor, the first generator, and the second generator and perform a model predictive control to dynamically adjust one or more electric power flows through the bidirectional power converter based on an engine propulsion power demand of the aircraft engine.
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公开(公告)号：US11300199B2
公开(公告)日：2022-04-12
申请号：US15709904
申请日：2017-09-20
摘要： A non-pressurized accessory gearbox for an aircraft includes: a housing, one or more gears disposed within the housing, an input rotating member to receive input from a main rotor gearbox via a shaft connected to the one or more gears, and one or more output rotating members in communication with the one or more gears. The gearbox is configured to utilize splash lubrication for moving a lubrication fluid within the housing.
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公开(公告)号：US11248743B2
公开(公告)日：2022-02-15
申请号：US16155208
申请日：2018-10-09
发明人： Joshua A. Emrich , Patrick Paquin , Eric C. Terry , Brent Scannell , Thomas Mast
摘要： In some examples, a drain pan comprises a composite material forming a reservoir and a drain. The composite material comprises a polymeric resin and a reinforcing fiber. The reservoir is to catch a liquid from an engine and to support a step load. The drain is to drain the liquid from the reservoir. In some examples, a method comprises attaching a drain pan to an aircraft proximate an engine. The drain pan comprises a composite material forming a reservoir and a drain. The method further comprises catching a liquid from the engine in the reservoir of the drain pan and draining the liquid from the reservoir through the drain. In addition, the method comprises supporting a step load on the reservoir of the drain pan.
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公开(公告)号：US20220034262A1
公开(公告)日：2022-02-03
申请号：US17501051
申请日：2021-10-14
发明人： Neil Terwilliger , John P. Virtue
IPC分类号： F02C7/268 , B64D27/10 , B64D27/24 , B64D31/06 , B64D33/00 , F02C9/26 , F02C9/54 , F02K5/00 , F02C6/14
摘要： An aspect includes a hybrid gas turbine engine system of a hybrid electric aircraft. The hybrid gas turbine engine system includes a gas turbine engine having a low speed spool and a high speed spool, a generator operably coupled to the low speed spool, a high spool electric motor operably coupled to the high speed spool, and a controller. The controller is configured to control the hybrid gas turbine engine system in a powered warm-up state to add heat to one or more components of the gas turbine engine by operating the gas turbine engine with a higher engine power setting above idle to drive rotation of the generator, transfer power from the generator to the high spool electric motor, and produce thrust. The gas turbine engine transitions from the powered warm-up state after reaching a target temperature of the one or more components in the powered warm-up state.
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公开(公告)号：US11181010B2
公开(公告)日：2021-11-23
申请号：US16460067
申请日：2019-07-02
发明人： Richard Kostka , David Menheere
IPC分类号： F01D25/18 , F16H57/04 , F02C7/32 , F02C7/06 , F16H57/027 , B64D33/00 , F16N39/00 , B01D45/12 , F16H57/02
摘要： The aircraft engine can have an air-oil separator having an air-oil mixture inlet, an oil outlet, an air outlet, and a pressure relief path provided fluidly in parallel with the air-oil separator, between the air-oil mixture inlet and the air outlet, the pressure relief path can have a pressure relief valve for evacuating air-oil mixture to the exhaust duct in the event of excess pressure in the auxiliary gearbox.
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公开(公告)号：US20210102492A1
公开(公告)日：2021-04-08
申请号：US16592122
申请日：2019-10-03
摘要： Heat exchangers, heat exchanger systems, and hypersonic vehicles are provided. For example, a heat exchanger is provided that comprises a first chamber for receipt of a flow of cool fluid and a second chamber for receipt of a flow of hot fluid. The heat exchanger further comprises a buffer fluid flowpath for circulation of a buffer fluid therethrough. The buffer fluid circulates within the buffer fluid flowpath disposed between the first chamber and the second chamber to transfer heat from the hot fluid to the cool fluid. In certain embodiments, a hypersonic vehicle comprises such a heat exchanger, and the cool fluid is cryogenic or near-cryogenic fuel of the hypersonic vehicle and the hot fluid is engine bleed air from a hypersonic propulsion engine of the vehicle.
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10.发明申请公开(公告)号：US20210049993A1
公开(公告)日：2021-02-18
申请号：US16987949
申请日：2020-08-07
发明人： Laurent Cazeaux , Florent Mercat , Claire Maffre
IPC分类号： G10K11/162 , B64D33/00
摘要： A double-enclosure acoustic element of small size, in particular for an aircraft acoustic panel. The acoustic element has a first enclosure with a mouth and a second enclosure with, at a front longitudinal end, a mouth and arranged inside the first enclosure, these first and second enclosures being joined together at the front. The acoustic element includes a slotting assembly system, the assembly system including at least one protruding element on the first edge of one of the first and second enclosures and at least one recess in the first edge of the other of the first and second enclosures, the protruding element and the recess having complementary shapes such that the protruding element can be slotted into the recess. Thus, the two enclosures can be assembled by quick and easy slotting.
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