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公开(公告)号：US11077957B2
公开(公告)日：2021-08-03
申请号：US15878075
申请日：2018-01-23
摘要： An air intake system (AIS) has a plenum and an inlet barrier filter associated with the plenum, through which air can selectively enter the plenum. The AIS also has an inlet duct associated with the plenum, through which air can selectively enter the plenum. The AIS also has a bypass door associated with the inlet duct, the bypass door being configured to selectively change an amount of air allowed to pass through the inlet duct. The AIS also has a filter airflow change device configured to change an amount of airflow allowed through the inlet barrier filter.
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公开(公告)号：US20200017229A1
公开(公告)日：2020-01-16
申请号：US16035340
申请日：2018-07-13
摘要： Systems and methods include providing an aircraft with a fuselage and a convertible engine disposed within the fuselage. The convertible engine is operable as a turbofan engine in a thrust mode and a turboshaft engine in a shaft power mode. The convertible engine includes a housing, an engine core having a low pressure turbine shaft, and a bypass fan system. The bypass fan system includes a bypass fan having a fan clutch. The fan clutch selectively couples at least a portion of the bypass fan to the low pressure turbine shaft when the convertible engine is operated in the thrust mode and decouples at least a portion of the bypass fan from the low pressure turbine shaft when the convertible engine is operated in the shaft power mode.
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公开(公告)号：US10377479B2
公开(公告)日：2019-08-13
申请号：US15172811
申请日：2016-06-03
摘要： The present invention includes an anti-torque assembly for a helicopter comprising a plurality of fixed blade pitch motors mounted on one or more pivots on the tail boom of the helicopter, wherein the plurality of fixed blade pitch motors on the one or more pivots are adapted to be oriented substantially in-plane with a tail boom of a helicopter during a first mode of operation that comprises a hover mode and wherein the fixed blade pitch motors are adapted to be oriented substantially off-plane from the tail boom of the helicopter during a second mode of helicopter operation that is different from the first mode.
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公开(公告)号：US10731553B2
公开(公告)日：2020-08-04
申请号：US15673762
申请日：2017-08-10
IPC分类号： F02B77/10 , A62C3/08 , F02B77/04 , F01P1/06 , F01P11/12 , F16N31/00 , F01P1/00 , A62C2/06 , B64D45/00
摘要： The present invention achieves technical advantages as an engine compartment drainage system that allows fluid on an engine deck to exit an engine compartment, while shielding fluid from airflow. A fluid drainage apparatus utilizes a funnel member to direct fluid to an external drain line. A drain shield circumscribes the top end of the funnel member and upwardly extending therefrom and directs airflow away from the funnel member. A plurality of deck holes are disposed in the drain shield, such that fluid on the deck can enter the funnel member and exit the engine compartment. A fluid drainage system, disposes the fluid drainage apparatus in an engine deck to allow fluid on the deck to enter a funnel member of the apparatus and direct it toward the external drain line.
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公开(公告)号：US20200023988A1
公开(公告)日：2020-01-23
申请号：US16042024
申请日：2018-07-23
发明人： Thomas Dewey Parsons , Angel David Rosado , Robert Paul Reynolds , David Frank Haynes , William Mathisen Gons
摘要： A boundary layer utilization apparatus for intake of air to a high speed aircraft, comprises a first air inlet adjacent an exterior surface of a fuselage of the aircraft and offset from the fuselage enough to integrate a second air inlet in the offset space to ingest and divert the boundary layer air flowing next to the fuselage into the aircraft for a useful purpose such as cooling the engine compartment. The second air inlet is disposed aft of the first air inlet to minimize hot gas re-ingestion.
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公开(公告)号：US20200003295A1
公开(公告)日：2020-01-02
申请号：US16025147
申请日：2018-07-02
IPC分类号： F16H57/04
摘要： A drive system for a tiltrotor aircraft operable to transition between rotary and non rotary flight modes. The drive system includes an engine to provide rotational energy and a proprotor assembly to receive rotational energy from the engine when the tiltrotor aircraft is in the rotary flight mode. The proprotor assembly is disengaged from the engine in the non rotary flight mode. The drive system includes a proprotor gearbox including one or more gears mechanically interposed between the engine and the proprotor assembly. The proprotor gearbox transfers rotational energy from the engine to the proprotor assembly when the tiltrotor aircraft is in the rotary flight mode. The drive system includes a lubricant operable to reduce friction between the gears and a lubrication management system to affect a temperature of the lubricant to enhance lubrication between the gears in the proprotor gearbox in the rotary flight mode.
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7.发明申请公开(公告)号：US20190084688A1
公开(公告)日：2019-03-21
申请号：US15710622
申请日：2017-09-20
发明人： Thomas Dewey Parsons
IPC分类号： B64D33/02
摘要： The present invention achieves technical advantages as a rotorcraft engine inlet configuration to optimize performance in both hover and high-speed flight. A rotorcraft fuselage with a ram air intake and a side air intake allows airflow into the engine inlet plenum. A door can be operably coupled to the fuselage, wherein the door is in an open position when the airspeed is below a first threshold and is in a closed position when the airspeed exceeds a second threshold. Additionally, control logic, compares the rotorcraft airspeed with a stored airspeed to operate an actuator to open and close the door to modulate the airflow into the engine inlet plenum. The present invention realizes the advantages of eliminating the inlet spillage drag due to inlet ram airflow in forward flight and increasing the available engine power by mitigating the loss of inlet air pressure recovery.
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公开(公告)号：US10787253B2
公开(公告)日：2020-09-29
申请号：US16183035
申请日：2018-11-07
IPC分类号： B64C27/82
摘要： The present invention includes an anti-torque assembly for a helicopter comprising a plurality of fixed blade pitch motors mounted on one or more pivots on the tail boom of the helicopter, wherein the plurality of fixed blade pitch motors on the one or more pivots are adapted to be oriented substantially in-plane with a tail boom of a helicopter during a first mode of operation that comprises a hover mode and wherein the fixed blade pitch motors are adapted to be oriented substantially off-plane from the tail boom of the helicopter during a second mode of helicopter operation that is different from the first mode.
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公开(公告)号：US10703471B2
公开(公告)日：2020-07-07
申请号：US15458525
申请日：2017-03-14
摘要： The present invention includes an a plurality of first variable speed motors arranged in a first matrix pattern and mounted on a tail boom of the helicopter; one or more fixed pitch blades attached to each of the plurality of first variable speed motors; and wherein a speed of one or more of the plurality of first variable speed motors is varied to provide an anti-torque thrust.
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公开(公告)号：US20200047911A1
公开(公告)日：2020-02-13
申请号：US16059655
申请日：2018-08-09
发明人： Thomas Dewey Parsons
摘要： Embodiments are directed to systems and methods for managing electrical load in an aircraft comprising a generator coupled to an aircraft engine, and a power distribution controller configured to monitor current engine operating parameters and to reduce an electrical load on the generator when the engine operating parameters reach a limit during specified aircraft operating conditions. The system may further comprise a non-essential electrical bus coupled to the generator, wherein the electrical load on the generator is reduced by disconnecting the non-essential bus from the generator. The generator may be coupled to the aircraft engine via an accessory gearbox or a transmission gearbox. The monitored current engine operating parameters comprise one or more of an engine torque, a gas generator RPM, and a temperature. The aircraft operating conditions may comprise one or more of a takeoff, a landing, or an engine failure.
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