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公开(公告)号：US12103695B2
公开(公告)日：2024-10-01
申请号：US17948870
申请日：2022-09-20
发明人： Michel Labrecque , Kevin Nguyen
摘要： An exhaust nozzle assembly for a propulsion system include a primary nozzle, an outer shroud, an ejector nozzle, and an actuator. The primary nozzle extends along an exhaust centerline. The primary nozzle includes a downstream axial end. The outer shroud surrounds the primary nozzle. The ejector nozzle extends axially between a first axial end and a second axial end. The second axial end forms a nozzle exit plane for the exhaust nozzle assembly. The ejector nozzle converges in a direction from the first axial end to the second axial end. The ejector nozzle forms a mixing cross-sectional area between the primary nozzle and the ejector nozzle at the downstream axial end. The actuator is mounted on the ejector nozzle. The actuator is configured to move the ejector nozzle between a first position and a second position, relative to the outer shroud, to control an area of the mixing cross-sectional area.
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公开(公告)号：US20240318611A1
公开(公告)日：2024-09-26
申请号：US18189360
申请日：2023-03-24
发明人： Michel BOUSQUET , Johnny VINSKI
CPC分类号： F02F11/007 , F02B55/10 , F02B2053/005 , F02B55/00 , F02B55/08 , F02F11/00 , F04C29/04 , F04C2240/80 , F05C2201/021 , F05C2203/08 , F05C2203/0886 , F05C2251/02 , F05C2253/16
摘要： A housing assembly for a rotary engine, has: a rotor housing extending around an axis, the rotor housing having an inner face facing a rotor cavity; side housings secured to opposite sides of the rotor housing, the rotor cavity bounded axially between the side housings; and a seal received within a groove at an interface between the rotor housing and a first side housing, the groove annularly extending around the axis, located outwardly of the inner face, and overlapping a peripheral section of the first side housing, the seal having: an elastomeric member compressed between the peripheral section and the rotor housing; and a shield disposed inwardly of the elastomeric member, the shield having a melting point above a temperature of combustion gases, the shield in contact with both of the peripheral section of the first side housing and the rotor housing.
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公开(公告)号：US20240308350A1
公开(公告)日：2024-09-19
申请号：US18123266
申请日：2023-03-18
发明人： Raphael Gariepy , Simon Lam , Remi Robache , Antwan Shenouda , Richard Freer , Ninad Joshi
CPC分类号： B60L3/04 , B60L3/0046 , B64D27/24 , B64D2221/00
摘要： An assembly for an aircraft includes an aircraft electrical distribution bus, a battery, and a control system. The battery includes a plurality of battery strings. Each battery string includes a string contactor. The control system is in signal communication with the string contactor of each battery string. The control system is configured to control a position of the string contactor of each battery string in a closed string position or an open string position. The control system is configured to: detect a fault in a faulted first battery string of the plurality of battery strings and position the string contactor of the faulted first battery string in the open string position, in response to the detected fault in the faulted first battery string and maintain the string contactor of at least one unfaulted second battery string of the plurality of battery strings in the closed string position.
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公开(公告)号：US12078069B2
公开(公告)日：2024-09-03
申请号：US17938736
申请日：2022-10-07
发明人： Marc Tardif , Alexandre Seguin , Sylvain Vignola
CPC分类号： F01D11/008 , F01D5/3007 , F01D11/006 , F01D5/22 , F05D2220/323 , F05D2240/55 , F05D2240/80
摘要： A rotor assembly has: blades having airfoils and roots protruding from platform segments; a rotor disc having a peripheral face defining recesses, and slots, a recess located between two adjacent ones of the slots and bounded by a step; feather seals located radially between the peripheral face and the platform segments, a feather seal having a core extending from a trailing end to a leading end and overlapping a gap defined between two platform segments and tabs protruding from the core, the tabs including: trailing tabs positioned axially outside the recess; and leading tabs, a leading tab extending from a root to a tip and having one or more of: the tip axially positioned outside of the recess; and a fillet at an intersection between the tip and an edge of the leading tab, the edge extending between the tip and the core, and facing the step.
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公开(公告)号：US12072104B1
公开(公告)日：2024-08-27
申请号：US18371887
申请日：2023-09-22
发明人： Jakub Strzepek
摘要： A fuel delivery apparatus is provided for a gas turbine engine. This fuel delivery apparatus includes a fuel injector. The fuel injector includes a plurality of fuel passages, a guide passage, a plurality of air passages, a mixing cavity and a fuel injector outlet. The fuel passages extend along an axis to the guide passage. The fuel passages converge radially inwards towards the axis as the fuel passages spiral about the axis towards the guide passage. The guide passage turns radially outwards away from the axis as the guide passage extends from the fuel passages to the mixing cavity. The air passages converge radially inwards towards the axis as the air passages extend axially to the mixing cavity. The mixing cavity fluidly couples the guide passage and the air passages to the fuel injector outlet.
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公开(公告)号：US12071252B1
公开(公告)日：2024-08-27
申请号：US18333696
申请日：2023-06-13
CPC分类号： B64D27/24 , B64C11/305 , B64C11/44
摘要： The aircraft can include a rotary airfoil device having an output shaft rotatable around an airfoil rotation axis; an electric engine having a source shaft drivingly coupled to the output shaft; a controller in communication with the electric engine; a low voltage electric system operable to power the controller; a high voltage electric system having a high voltage battery operable to power the electric engine, the high voltage battery further operable to power the low voltage electric system via a voltage converter; and an electromagnetic generator having a generator shaft coupled to the output shaft, the electromagnetic generator operable to power the low voltage electric system.
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公开(公告)号：US12070811B2
公开(公告)日：2024-08-27
申请号：US17200988
申请日：2021-03-15
发明人： Daniel Lecuyer , Robert Huszar
CPC分类号： B23H9/10 , B23P15/008 , B23P15/04 , F01D5/3007 , F01D11/006 , F05D2230/12 , F05D2240/55 , F05D2240/80 , F05D2260/30 , Y10T29/4932 , Y10T29/49336
摘要： A blade for mounting on a rotor disc of a gas turbine engine includes platform segments between a airfoil and blade root and extending laterally from the blade, the platform segment having a curved profile defining a platform recess on a root side of the platform segment, the recess configured to cooperate with recesses of adjacent blades to define a blade pocket. A recessed region is defined in a rear surface of the blade root, and is configured to receive a complementary projection of the rotor disc upon mounting the blade on the rotor disc. The recessed region has a surface configured to abut a corresponding surface on the projection of the rotor disc to form a face seal. Methods of manufacturing such a rotor disc and of sealing a circumferential joint between such blades and the rotor disc are also disclosed.
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公开(公告)号：US20240280030A1
公开(公告)日：2024-08-22
申请号：US18582174
申请日：2024-02-20
发明人： Hien Duong , Vijay Kandasamy
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F05D2240/122 , F05D2240/80
摘要： A vane array structure for a gas turbine engine includes a first platform, a second platform, a plurality of vanes and a flowpath. Each of the vanes extends across the flowpath between the first platform and the second platform. The vanes include a first vane and a second vane disposed longitudinally next to the first vane along the flowpath. The first vane includes a first airfoil and a first recess. The first airfoil extends spanwise between a first end at the first platform and a second end at the second platform. The first airfoil extends chordwise between a leading edge and a trailing edge. The first airfoil extends laterally between a first side and a second side. The first recess projects spanwise into the first airfoil from the first end. The first recess projects chordwise into the first airfoil from the trailing edge.
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公开(公告)号：US12066083B2
公开(公告)日：2024-08-20
申请号：US17977158
申请日：2022-10-31
发明人： Jonathan Hodgson , Vlastislav Fric
IPC分类号： B60K17/16 , B60K17/02 , B60K23/04 , B64D35/00 , F02B39/04 , F02B41/10 , F16H3/72 , F16H48/22 , F16H48/36 , F16H3/66
CPC分类号： F16H3/72 , B64D35/00 , F16H3/666 , F16H2200/2007
摘要： An epicyclic gear system includes an input sun gear configured to receive rotational input from a turbine of a turbo charger. A first set of planet gears is distributed around and meshes with the input sun gear. A carrier holds the first set of planet gears and defines a rotational axis about which the carrier rotates. A second set of planet gears is mounted to the carrier. An output sun gear is included, wherein the second set of planet gears are distributed around and mesh with the output sun. The output sun gear is configured to deliver rotational power to an internal combustion engine. The carrier is configured to selectively be driven by a variable speed drive to regulate output to the output sun over a range of input rotational speeds of the input sun gear.
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公开(公告)号：US20240271575A1
公开(公告)日：2024-08-15
申请号：US18645585
申请日：2024-04-25
CPC分类号： F02C9/22 , F04D27/001 , F05D2220/323 , F05D2260/81 , F05D2270/301 , F05D2270/304 , F05D2270/306 , F05D2270/71
摘要： A system and a method for configuring at least one variable geometry mechanism (VGM) of an aircraft engine are provided. Pass-off testing data for the aircraft engine is obtained, the pass-off testing data indicative of an actual value of at least one operating parameter of the aircraft engine. Based on the pass-off testing data, at least one trim value to be used to adjust a setting of the at least one VGM to bring the actual value of the at least one operating parameter towards a target value is determined, a running line of the aircraft engine being substantially constant when the actual value of the at least one operating parameter is at the target value. The setting of the at least one VGM is adjusted, during pass-off testing of the aircraft engine, using the at least one trim value.
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