公开(公告)号：US10731553B2

公开(公告)日：2020-08-04

申请号：US15673762

申请日：2017-08-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Thomas Dewey Parsons ,  Chris James Ludtke ,  Andrew Jordan Birkenheuer ,  Eric Christopher Terry

IPC: F02B77/10 ,  A62C3/08 ,  F02B77/04 ,  F01P1/06 ,  F01P11/12 ,  F16N31/00 ,  F01P1/00 ,  A62C2/06 ,  B64D45/00

Abstract: 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.

公开(公告)号：US20200023988A1

公开(公告)日：2020-01-23

申请号：US16042024

申请日：2018-07-23

Applicant: Bell Helicopter Textron Inc.

Inventor： Thomas Dewey Parsons ,  Angel David Rosado ,  Robert Paul Reynolds ,  David Frank Haynes ,  William Mathisen Gons

IPC: B64D33/08 ,  B64D33/02 ,  F15D1/00

Abstract: 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.

公开(公告)号：US20200003295A1

公开(公告)日：2020-01-02

申请号：US16025147

申请日：2018-07-02

Applicant: Bell Helicopter Textron Inc.

Inventor： Thomas Dewey Parsons ,  Troy Cyril Schank

IPC: F16H57/04

Abstract: 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.

公开(公告)号：US20190084688A1

公开(公告)日：2019-03-21

申请号：US15710622

申请日：2017-09-20

Applicant: Bell Helicopter Textron Inc.

Inventor： Thomas Dewey Parsons

IPC: B64D33/02

Abstract: 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.

公开(公告)号：US10829239B2

公开(公告)日：2020-11-10

申请号：US16059655

申请日：2018-08-09

Applicant: Bell Helicopter Textron Inc.

Inventor： Thomas Dewey Parsons

IPC: B64D41/00 ,  B60R16/03 ,  H02B1/20 ,  B64C27/04 ,  H02P101/30

Abstract: 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.

公开(公告)号：US20190071173A1

公开(公告)日：2019-03-07

申请号：US16183035

申请日：2018-11-07

Applicant: Bell Helicopter Textron Inc.

Inventor： Thomas Dewey Parsons ,  Carlos Alexander Fenny ,  Erik John Oltheten

IPC: B64C27/82

Abstract: 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.

公开(公告)号：US20190048795A1

公开(公告)日：2019-02-14

申请号：US15673762

申请日：2017-08-10

Applicant: Bell Helicopter Textron Inc.

Inventor： Thomas Dewey Parsons ,  Chris James Ludtke ,  Andrew Jordan Birkenheuer ,  Eric Christopher Terry

IPC: F02B77/10 ,  F01P11/12 ,  F01P1/06 ,  F02B77/04

Abstract: 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.