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公开(公告)号：US20240352872A1
公开(公告)日：2024-10-24
申请号：US18304037
申请日：2023-04-20
摘要： An example system includes one or more heaters configured and positioned to add thermal energy to one or more portions of a gas turbine engine after the gas turbine engine was in operation, wherein the thermal energy minimizes or prevents undesired contact or seizing of a rotor of the gas turbine engine with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The system further includes a controller configured to control operation of the one or more heaters.
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公开(公告)号：US20240056007A1
公开(公告)日：2024-02-15
申请号：US17819527
申请日：2022-08-12
CPC分类号： H02P9/08 , F02C7/268 , H02P2101/25
摘要： An example system includes a power electronics system; a starter electrically connected to the power electronics system and configured to start a gas-turbine engine of an aircraft; and an energy storage system electrically connected to the power electronics system and configured to provide direct current (DC) electrical energy to the power electronics system, wherein the power electronics system is configured to deliver alternating current (AC) electrical energy to the starter to start the gas-turbine engine using the DC electrical energy from the energy storage system and AC electrical energy sourced from an AC electrical bus of the aircraft.
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公开(公告)号：US20220328914A1
公开(公告)日：2022-10-13
申请号：US17226954
申请日：2021-04-09
发明人： Michael Adam Zagrodnik , Stephen Mountain , Peter Schenk , Mathivanan Anand Prabhu , Krishnamoorthi Sivalingam , Teh Yee Siang , Chandana Jayampathi Gajanayake , Melvin Yang Yueng Yap
IPC分类号： H01M50/143 , H01M50/383 , H01M10/04 , H01M50/179 , H01M50/119
摘要： A battery housing for an aerospace battery may include a first endplate; a flange; and an elliptical cylinder extending from a first cylinder end to a second cylinder end. The first cylinder end of the elliptical cylinder may be welded to the first endplate, and the second cylinder end of the elliptical cylinder may be welded to the flange. The elliptical cylinder is formed from a sheet of material comprising a first sheet end and a second sheet end. The first sheet end may be welded to the second sheet end at a weld location that runs from the first cylinder end to the second cylinder end at a perimeter location that is calculated to experience a reduced stress during pressurization of the housing.
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公开(公告)号：US20220328913A1
公开(公告)日：2022-10-13
申请号：US17226863
申请日：2021-04-09
发明人： Michael Adam Zagrodnik , Stephen Mountain , Peter Schenk , Mathivanan Anand Prabhu , Krishnamoorthi Sivalingam , Teh Yee Siang , Chandana Jayampathi Gajanayake , Melvin Yang Yueng Yap
IPC分类号： H01M50/143 , H01M10/6556 , H01M50/249 , H01M10/6554 , H01M50/213 , H01M50/117
摘要： An aerospace battery may include a housing; a battery pack core; a ceramic felt surrounding at least part of the battery pack core; and a closed cell foam filling open space between the battery pack core, the ceramic felt, and the housing.
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公开(公告)号：US12098695B1
公开(公告)日：2024-09-24
申请号：US18361086
申请日：2023-07-28
发明人： Peter Schenk , Erik A. Munevar
CPC分类号： F02N11/0859 , F02C7/262 , F02C7/277 , F02N11/0862 , F02N11/087 , F02N2011/0874
摘要： An example system includes a common electric starter controller configured to control electric starters of a plurality of gas-turbine engines that are configured to propel an aircraft, wherein the common electric starter comprises: a driver configured to generate, using electrical energy sourced from a battery of the aircraft, power signals that control the electric starters; and a plurality of bus bars configured to directly connect the common electric starter controller to the battery and transport the electrical energy from the battery to the common electric starter controller.
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公开(公告)号：US12024308B2
公开(公告)日：2024-07-02
申请号：US17553756
申请日：2021-12-16
发明人： David Locascio , Michael Dougherty , Stephen Long , Peter Schenk
IPC分类号： B64D33/08 , B64D27/24 , F04B17/02 , F04B17/03 , H01M10/613 , H01M10/625 , B64C11/00
CPC分类号： B64D33/08 , B64D27/24 , F04B17/02 , F04B17/03 , H01M10/613 , H01M10/625 , B64C11/002
摘要： A propulsion system for an aircraft includes a propeller assembly, a controller, and a pump system. The propeller assembly includes a propeller and a power system, the power system including an electric motor and a motor converter. The controller is connected to the power system and configured to switch the power system into a power-off arrangement in response to a temperature of the motor converter being greater than a threshold temperature. The pump system includes a pump and a coolant circuit that cools the motor converter. The pump is coupled to the propeller and to the motor such that rotation of either drives the pump.
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公开(公告)号：US20220363402A1
公开(公告)日：2022-11-17
申请号：US17321146
申请日：2021-05-14
发明人： Peter Schenk , David Loder , David Trawick
摘要： A voltage controlled aircraft electric propulsion system includes an electric propulsion system. The voltage controlled aircraft electric propulsion system may include electric propulsors providing thrust for the aircraft. In hybrid systems, a gas turbine engine may also be included. The electric propulsion system may include at least one electric generator power source, at least one propulsor motor load, and at least one stored energy power source, such as a battery. The propulsor motor load may be supplied power from a power supply bus. The voltage of the power supply bus may be adjusted according to an altitude of the aircraft while maintaining a substantially constant current flow to the propulsor motor load. Due to the adjustment to lower voltages at increased altitude, insulations levels may be lower.
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公开(公告)号：US12027915B2
公开(公告)日：2024-07-02
申请号：US17444734
申请日：2021-08-09
发明人： Peter Schenk , Mathew Hill , David Loder
摘要： A rotor assembly includes a rotor core having an axial length and configured to rotate about a longitudinal axis and at least one permanent magnet disposed about a radially outer surface of the rotor core. The rotor assembly further includes an electrical insulator disposed between the radially outer surface of the rotor core and the at least one permanent magnet and configured to disrupt an electrical conduction path along the axial length of the rotor core.
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公开(公告)号：US20240352895A1
公开(公告)日：2024-10-24
申请号：US18304129
申请日：2023-04-20
CPC分类号： F02C9/00 , F01D25/08 , F01D25/10 , F02C9/18 , F05D2260/20
摘要： An example system includes a thermal energy system configured to transport thermal energy harvested from a first portion of a gas turbine engine to a second portion of the gas turbine engine after the gas turbine engine was in operation, wherein the transported thermal energy minimizes or prevents undesired contact or seizing of a rotor with another component of the gas turbine engine due to warping of the rotor due to uneven cooling of the gas turbine engine after the operation. The thermal energy system includes a cavity configured to flow a fluid, wherein the fluid is configured to transport thermal energy from the first portion to the second portion.
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10.发明公开公开(公告)号：US20240271574A1
公开(公告)日：2024-08-15
申请号：US18168947
申请日：2023-02-14
摘要： In examples, a clutch assembly includes a first clutch member disposed near a first end of a first shaft. The first clutch member defines a first surface. The first shaft includes a starter motor coupled to a second end of the first shaft. The clutch assembly includes a second clutch member disposed near a first end of a second shaft. The second clutch member defines a second surface opposing the first surface, and the second shaft includes an accessory gearbox of a gas turbine engine coupled to a second end of the second shaft. The surfaces of the first and second clutch member engage such that rotational motion is transferred between the first clutch member and the second clutch member. The first clutch member and the second clutch member are configured to passively disengage from each other and actively reengage with each other.
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