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公开(公告)号：US12030647B2
公开(公告)日：2024-07-09
申请号：US17675889
申请日：2022-02-18
申请人： The Boeing Company
发明人： Gregory M. Santini , Kevin R. Tsai
摘要： Thermal anti-icing systems are disclosed. An example anti-icing system includes a housing defining an inner recess, a first support fitting, a second support fitting spaced away from the first support fitting. The housing is positioned between the first support fitting and the second support fitting. The first support fitting, the second support fitting and an outer wall of the housing define a heating chamber that is fluidly separated from the inner recess.
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公开(公告)号：US20240166356A1
公开(公告)日：2024-05-23
申请号：US18505667
申请日：2023-11-09
申请人： EMBRAER S.A.
IPC分类号： B64D13/08 , B60L50/70 , B64D15/04 , B64D27/24 , H01M8/04007 , H01M8/04014
CPC分类号： B64D13/08 , B60L50/70 , B64D15/04 , B64D27/24 , H01M8/04014 , H01M8/04074 , B64D2013/0607
摘要： Air systems for a fuel cell powered aircraft include at least one compressor for supplying heated compressed air, at least one heat exchange system for receiving the heated compressed air and from the at least one compressor and discharging cooled compressed air, and at least one turbine for receiving the cooled compressed air from the heat exchange system and directing the cooled compressed air to on-board aircraft cabin pressurization and temperature control systems. At least one shaft operatively interconnects the at least one compressor and the at least one turbine. An electric motor is provided and adapted to being powered by electrical power supplied by an on-board fuel cell of the aircraft, the electric motor being operatively connected to the shaft interconnecting the at least one compressor and the at least one turbine so as to operatively cause the shaft to drive the at least one compressor and the at least one turbine.
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公开(公告)号：US20240076044A1
公开(公告)日：2024-03-07
申请号：US17929550
申请日：2022-09-02
摘要： A gas turbine engine including a core air passage, a combustor, and a steam line. The combustor is located in the core air passage and combusts hydrogen fuel producing combustion gases. The steam line is fluidly coupled to the core air passage at a position downstream of the combustor to receive a portion of the combustion gases. A conduit thermally coupled to an external surface of an aircraft may be fluidly coupled to the steam line to receive the combustion gases and to heat the external surface. The gas turbine engine may also include a water vapor condenser fluidly connected to the steam line to receive the combustion gases and to condense the water vapor of the combustion gases. At least one nozzle may be fluidly coupled to the water vapor condenser to inject the condensed water into the core air passage.
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公开(公告)号：US20230383694A1
公开(公告)日：2023-11-30
申请号：US18310747
申请日：2023-05-02
申请人： ROLLS-ROYCE plc
发明人： Chloe Jo PALMER
摘要： A hydrogen-fuelled gas turbine engine has a fuel input path from a fuel input of the engine to a combustor, the engine further comprising a heat-exchanger located in the fuel input path and a fuel turbine located in the fuel input path between the heat-exchanger and the combustor. The heat-exchanger is arranged to receive waste heat from the engine core in order to heat hydrogen fuel introduced at the fuel input prior to input thereof to the combustor. The engine further comprises an air compressor arranged to be driven by the fuel turbine. The engine provides for most of the waste heat of combustion to be recovered and used without the need for heavy electrical or mechanical apparatus and is therefore particularly advantageous in aeronautical applications.
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公开(公告)号：US20230312110A1
公开(公告)日：2023-10-05
申请号：US17856334
申请日：2022-07-01
申请人： GOODRICH CORPORATION
IPC分类号： B64D15/04
CPC分类号： B64D15/04
摘要： Ice may form along the leading edge of an aircraft wing. A pneumatic deicing system may be configured to crack and dislodge ice along the leading edge of the wing. The pneumatic deicing system may comprise a deicing boot assembly having a deicing boot attached to the leading edge, and a gas generator fluidly coupled to the deicing boot assembly. The gas generator may comprise a propellant and may decompose the propellant, liberating a compressed gas. The compressed gas may be directed to the deicing boot assembly, inflating the deicing boot, which may crack and dislodge the ice.
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公开(公告)号：US20230264820A1
公开(公告)日：2023-08-24
申请号：US17675889
申请日：2022-02-18
申请人： The Boeing Company
发明人： Gregory M. Santini , Kevin R. Tsai
摘要： Thermal anti-icing systems are disclosed. An example anti-icing system includes a housing defining an inner recess, a first support fitting, a second support fitting spaced away from the first support fitting. The housing is positioned between the first support fitting and the second support fitting. The first support fitting, the second support fitting and an outer wall of the housing define a heating chamber that is fluidly separated from the inner recess.
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公开(公告)号：US11697503B2
公开(公告)日：2023-07-11
申请号：US17498470
申请日：2021-10-11
发明人： Paul Julian Wells
CPC分类号： B64D15/04 , B64D33/02 , F01D17/141 , F01D25/02 , F01D25/24 , F02C7/047 , F16K17/02 , B64D2033/0233 , F05D2220/323
摘要： A pressure regulating valve assembly includes: a valve having an upstream side receiving an input flow and a downstream side providing an output flow, an actuator for opening and closing the valve, including partially opening the valve, and a regulator controlling the actuator to open, close or partially open the valve. The regulator includes a sense pressure port, wherein pressure at the port is maintained constant by the regulator. A chamber has a first entry orifice, a second entry orifice and an exit orifice. The first entry orifice is connected to the upstream side, the second entry orifice is connected to the downstream side, and the exit orifice is connected to the port. The exit orifice provides that the pressure at the exit orifice lies between the pressure at the first entry orifice and the pressure at the second entry orifice.
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公开(公告)号：US11649058B2
公开(公告)日：2023-05-16
申请号：US17462751
申请日：2021-08-31
申请人： Goodrich Corporation
CPC分类号： B64D15/12 , B64D15/04 , F02C7/047 , F05D2220/323
摘要： Disclosed is an ice protection system for an aerodynamic surface of an aircraft, a surface having a flow facing side and an inwardly facing side that opposes the flow facing side, the system having: a perforated sheet configured for disposal in the surface; a heating source connected to the perforated sheet; and a suction source disposed to draw ice melted by the heating source through the perforated sheet and heating source.
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公开(公告)号：US11591960B2
公开(公告)日：2023-02-28
申请号：US17427548
申请日：2020-01-22
申请人： SAFRAN NACELLES
发明人： Sébastien Laurent Marie Pascal , Jean-Michel Paul Ernest Nogues , Marc Versaevel , François Chauveau
摘要： The invention relates to an air intake of an aircraft turbojet engine nacelle, extending along an axis X, in which an air flow circulates from upstream to downstream, the air intake extending circumferentially around the axis X and comprising an inner wall, which faces the axis X in order to guide an inner air flow, and an outer wall, which is opposite the inner wall, for guiding an external air flow, the walls being connected by a leading edge and an inner partition so as to delimit an annular cavity. The air intake comprises means for injecting at least one hot air flow into the inner cavity and at least one ventilation orifice formed in the outer wall in order to allow the hot air flow to escape after heating the internal cavity, the air intake comprising at least one disruption member of the external air flow, positioned upstream of the ventilation orifice, which extends outwardly from the outer wall.
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公开(公告)号：US11577844B2
公开(公告)日：2023-02-14
申请号：US17128049
申请日：2020-12-19
申请人： ROHR, INC.
摘要： A piccolo tube for an anti-icing system may comprise an annular tube and a plurality of openings formed along a circumference of the annular tube. The annular tube may comprise a first cross-sectional diameter at an inlet point and a second cross-sectional diameter at a distal point. The second cross-sectional diameter is less than first cross-sectional diameter. The distal point may be 180° from the inlet point.
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