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公开(公告)号：US12126161B2
公开(公告)日：2024-10-22
申请号：US18180550
申请日：2023-03-08
发明人： Antwan Shenouda
CPC分类号： H02H1/0023 , H01H85/22 , H02B1/18 , H02H7/22 , H01H2083/201
摘要： An arc detection assembly is provided and includes first and second conductors including first and second terminal ends, respectively, which are engageable to form an electrical connection and an arc detection system. The arc detection system includes a fusible link disposed proximate to one of the first and second terminal ends and configured to break in response to an arcing condition between the first and second terminal ends and a monitoring circuit coupled to the fusible link and configured to determine when breakage of the fusible link occurs and to thereby determine that the arcing condition has occurred.
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公开(公告)号：US12123314B2
公开(公告)日：2024-10-22
申请号：US17081055
申请日：2020-10-27
发明人： Guy Lefebvre , Remy Synnott
CPC分类号： F01D25/18 , F02C7/20 , F16L15/02 , F16L27/1274 , F05D2260/60 , F05D2260/98 , F16L27/12751
摘要： A gas turbine engine has a service tube assembly including an adjustable joint having a flange axially movable along an end fitting having a male/female connection with a mating part. The flange is threadably engaged with the end fitting to provide for the adjustment of the position of the flange along the end fitting.
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公开(公告)号：US20240343405A1
公开(公告)日：2024-10-17
申请号：US18298481
申请日：2023-04-11
IPC分类号： B64D33/00
摘要： A component for an aircraft engine. The component is mountable externally to a core of the aircraft engine. The component includes an enclosure having a wall circumscribing a sealed inner chamber. The wall has an inner surface and an outer surface. The wall has a first wall portion welded to a second wall portion along a weld line extending about a perimeter of the enclosure. A mounting bracket is disposed on the outer surface for mounting the component to the core. A protrusion protrudes from one or more of the outer surface and the inner surface and extends along one or more of the outer surface and the inner surface concentrically with the weld line. Sn additional protrusion protrudes from one or more of the outer surface and the inner surface. The additional protrusion extends from the protrusion to the mounting bracket.
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公开(公告)号：US12116898B2
公开(公告)日：2024-10-15
申请号：US18160117
申请日：2023-01-26
CPC分类号： F01D11/24 , F01D11/18 , F05D2220/323 , F05D2240/11 , F05D2240/55 , F05D2260/201
摘要： Turboprop engines include a housing, a propeller arranged at a forward end of the housing, and a rotor assembly arranged within the housing, the rotor assembly comprising at least one rotor having a plurality of rotor blades. A blade shroud is arranged radially outward from the rotor assembly and positioned relative to the rotor blades such that a tip clearance is defined between tips of the rotor blades and an inner diameter surface of the blade shroud. A shroud cooling duct is defined radially outward from the blade shroud and radially inward from the housing and an air scoop is configured to direct a shroud cooling flow into the shroud cooling duct to pick up heat from the blade shroud and provide cooling thereto.
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公开(公告)号：US12115623B2
公开(公告)日：2024-10-15
申请号：US17983815
申请日：2022-11-09
发明人： Bernard Chow , Gerard Theriault
CPC分类号： B25B13/48 , F02C7/20 , F16B43/00 , F05D2230/60 , F05D2260/31
摘要： An assembly method is provided during which a first component is arranged with a second component. The first component is secured to the second component using a fastener assembly. The fastener assembly includes a fastener element and a washer. The fastener element includes a wrenching feature. The washer has a full-hoop annular body with a cylindrical outer surface. The securing includes: mating a socket device with the fastener element and the washer, the socket device engaging the wrenching feature and the cylindrical outer surface; and rotating the fastener element about an axis using the socket device to tighten the fastener assembly and clamp the washer axially between the first component and the fastener element. The socket device centers the washer to the fastener element during the rotating.
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公开(公告)号：US12110796B1
公开(公告)日：2024-10-08
申请号：US18221645
申请日：2023-07-13
发明人： Johnny Vinski , Jean-Philippe Simoneau , David Gagnon-Martin , Vincent Savaria , Bruno Villeneuve , Stephane Berube , Frederic Roy , Sebastien Bolduc
CPC分类号： F01C19/005 , F01C1/3442 , F01C21/06 , F04C2240/30
摘要： An engine housing includes a rotor housing and a side housing assembly. The rotor housing includes a rotor housing body. The rotor housing body extends about an axis to form a rotor cavity of the engine housing. The rotor housing body extends between and to a first axial end and a second axial end. The side housing assembly includes a side housing body, a side plate, and a seal assembly. The side housing body is disposed at the first axial end. The side plate is disposed axially between the rotor housing body and the side housing body. The side plate includes an inner side, an outer side, and a perimeter edge. The seal assembly includes a support ring and a sealing ring. The support ring is disposed at the perimeter edge and the first axial end. The support ring circumscribes the side plate. The sealing ring extends between and to a first axial sealing ring end and a second axial sealing ring end. The first axial sealing ring end is disposed at the support ring and the outer side.
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公开(公告)号：US20240333007A1
公开(公告)日：2024-10-03
申请号：US18435601
申请日：2024-02-07
发明人： Remi Robache , Antwan Shenouda , Richard Freer , Simon Lam , Raphael Gariepy , Fraz Ahmad Kharal
CPC分类号： H02J7/0063 , B64D41/00 , H02J7/0014 , H02J7/0031 , B64D2221/00 , H02J2310/44
摘要： An assembly for an aircraft includes an aircraft electrical distribution bus, a battery, and a battery monitoring system. The battery includes a plurality of battery strings and a main battery contactor. The plurality of battery strings are electrically connected in parallel. Each battery string includes a string contactor. The string contactor is positionable in a closed string position or an open string position. The main battery contactor is electrically connected in series with the string contactor of each battery string. The main battery contactor is positionable in a closed battery position or an open battery position. The battery monitoring system is configured to control a position of the string contactor of each battery string. Control of a position of the main battery contactor in the closed battery position and the open battery position is independent of the battery monitoring system.
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公开(公告)号：US20240332915A1
公开(公告)日：2024-10-03
申请号：US18191181
申请日：2023-03-28
发明人： Sarmad KHAN
摘要： The igniter can have a first conductor having a tip extending along an axis and forming a positive terminal; a second conductor having a tip surrounding the tip of the first conductor around the axis and forming a negative terminal; an insulator filling a space between the first conductor and the second conductor, a spark path extending radially, relative the axis, between the tip of the first conductor and the tip of the second conductor, from the positive terminal to the negative terminal; at least one magnet operable to generate a magnetic field B, the magnetic field B having a magnetic field orientation extending circumferentially around the axis, the at least one magnet disposed radially, relative the axis, between the first conductor and the second conductor, the at least one magnet embedded within the insulator.
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公开(公告)号：US20240328352A1
公开(公告)日：2024-10-03
申请号：US18129609
申请日：2023-03-31
发明人： Hugues Pellerin
IPC分类号： F02C7/06
CPC分类号： F02C7/06 , F05D2260/98
摘要： An aircraft engine lubrication system for an aircraft engine having a first component (FC) and a second component (SC) is provided. The system includes a lubricant tank (LT), a first pump (FP), a second pump (SP), and a de-aerator (DA). The LT outlet is in fluid communication with a FP inlet. The FP outlet is in fluid communication with a SP inlet. The SP outlet is in fluid communication with a FC inlet and the SC inlet. The SC outlet is in fluid communication with a LT first inlet. The DA gas outlet is in fluid communication with a LT second inlet. The DA liquid outlet is in fluid communication with a SP inlet.
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公开(公告)号：US12104537B1
公开(公告)日：2024-10-01
申请号：US18193109
申请日：2023-03-30
发明人： Kashif Mohammed
摘要： A fire protection device for an accessory of an aircraft engine includes a baffle located within an airflow passage in communication with the accessory, the baffle having fire shield elements made of a shape memory alloy. The fire shield elements are deformable between a deformed state and a natural state, wherein in the natural state the fire shield elements extend at least partially across the airflow passage to protect the accessory from flames, and in the deformed state the fire shield elements is bent to define one or more gaps between the fire shield elements in the air flow passage thereby allowing airflow through the baffle.
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