公开(公告)号：US20180238235A1

公开(公告)日：2018-08-23

申请号：US15439728

申请日：2017-02-22

Applicant: Bell Helicopter Textron Inc.

Inventor： Zachary Edwin Dailey ,  Frank Bradley Stamps ,  Martin Peryea

IPC: F02C7/141 ,  B64D27/14 ,  B64C27/12 ,  B64C29/00 ,  B64D31/04 ,  B64D33/08 ,  B64D33/02 ,  F02C7/36 ,  F02C7/232 ,  F02C9/40 ,  F02C7/16

CPC classification number: F02C7/141 ,  B64C27/006 ,  B64D33/08 ,  B64D2033/024 ,  F02C3/30 ,  F02C7/143 ,  F02C7/16 ,  F02C7/22 ,  F02C7/232 ,  F02C7/36 ,  F02C9/28 ,  F02C9/40 ,  F05D2220/329 ,  F05D2260/212 ,  Y02T50/671 ,  Y02T50/675

Abstract: A rotorcraft has a low density altitude flight mode and a high density altitude flight mode. The rotorcraft includes a turboshaft engine forming a gas path in sequence through an air inlet section, a compressor section, a combustor section, a turbine section and an exhaust section. A drive system is coupled to the engine and is operable responsive to rotation of at least a portion of the turbine section. A rotor is coupled to the drive system and is operable to receive torque and rotational energy therefrom. A fuel injection system supplies fuel to the combustor section. An oxidizer injection system and a coolant injection system are used to selectively inject an oxidizer and a coolant into the gas path when it is desired to operate the rotorcraft in the high density altitude flight mode, thereby increasing the altitude density ceiling of the rotorcraft for maneuvers including takeoffs and landings.

公开(公告)号：US10800518B2

公开(公告)日：2020-10-13

申请号：US16272091

申请日：2019-02-11

Applicant: Bell Helicopter Textron Inc.

Inventor： Timothy Kent Ledbetter ,  Thomas Parham ,  Dalton T. Hampton ,  Frank Stamps ,  Zachary Edwin Dailey ,  Robert L. Milliken

IPC: B64C27/35 ,  B64C27/46

Abstract: An example of a hub for a tail rotor includes a body configured to couple to a mast of a rotor system, a trunnion disposed within the body, first and second shafts disposed on opposite sides of the trunnion, first and second end plates secured to the body, and first and second end bearings, the first end bearing disposed between the first shaft and the first end plate and the second end bearing disposed between the second shaft and the second end plate.

公开(公告)号：US20200255133A1

公开(公告)日：2020-08-13

申请号：US16272091

申请日：2019-02-11

Applicant: Bell Helicopter Textron Inc.

Inventor： Timothy Kent LEDBETTER ,  Thomas Parham ,  Dalton T. Hampton ,  Frank Stamps ,  Zachary Edwin Dailey ,  Robert L. Milliken

IPC: B64C27/35 ,  B64C27/46

Abstract: An example of a hub for a tail rotor includes a body configured to couple to a mast of a rotor system, a trunnion disposed within the body, first and second shafts disposed on opposite sides of the trunnion, first and second end plates secured to the body, and first and second end bearings, the first end bearing disposed between the first shaft and the first end plate and the second end bearing disposed between the second shaft and the second end plate.

公开(公告)号：US20200130823A1

公开(公告)日：2020-04-30

申请号：US16173064

申请日：2018-10-29

Applicant: Bell Helicopter Textron Inc.

Inventor： Andrew Paul HALDEMAN ,  Zachary Edwin Dailey ,  Aaron Alexander Acee ,  Dalton T. Hampton

IPC: B64C27/605 ,  B64C27/06 ,  B64C27/00 ,  B64C27/72 ,  B64C13/04 ,  B64C13/40

Abstract: An exemplary rotorcraft includes a power train with an engine coupled to a gearbox, a main rotor blade having a mast coupled to the power train, a control input linkage in communication between a pilot input device and the main rotor blade configured to communicate a control input force from the pilot input device to the main rotor blade, and a counterweight system in connection with the control input linkage and the power train to apply a centrifugal force to the control input linkage.

公开(公告)号：US20190329878A1

公开(公告)日：2019-10-31

申请号：US15967220

申请日：2018-04-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Andrew Paul Haldeman ,  Zachary Edwin Dailey ,  Charles Owen Black ,  Dalton T. Hampton ,  Aaron Alexander Acee

IPC: B64C27/52 ,  B64C27/12

Abstract: A transmission tilt control device includes a transmission rotatably coupled to an airframe of a helicopter, a rotor mast coupled to the transmission, and an actuator coupled between the transmission and the airframe. The actuator being configured to rotate the transmission fore and aft about a tilt axis that is perpendicular to an axis of rotation of the rotor mast.

公开(公告)号：US10940944B2

公开(公告)日：2021-03-09

申请号：US15967220

申请日：2018-04-30

Applicant: Bell Helicopter Textron Inc.

Inventor： Andrew Paul Haldeman ,  Zachary Edwin Dailey ,  Charles Owen Black ,  Dalton T. Hampton ,  Aaron Alexander Acee

IPC: B64C27/52 ,  B64C27/12

Abstract: A transmission tilt control device includes a transmission rotatably coupled to an airframe of a helicopter, a rotor mast coupled to the transmission, and an actuator coupled between the transmission and the airframe. The actuator being configured to rotate the transmission fore and aft about a tilt axis that is perpendicular to an axis of rotation of the rotor mast.

公开(公告)号：US10752349B2

公开(公告)日：2020-08-25

申请号：US16173064

申请日：2018-10-29

Applicant: Bell Helicopter Textron Inc.

Inventor： Andrew Paul Haldeman ,  Zachary Edwin Dailey ,  Aaron Alexander Acee ,  Dalton T. Hampton

IPC: B64C27/605 ,  B64C27/06 ,  B64C27/00 ,  B64C13/04 ,  B64C13/40 ,  B64C27/72

Abstract: An exemplary rotorcraft includes a power train with an engine coupled to a gearbox, a main rotor blade having a mast coupled to the power train, a control input linkage in communication between a pilot input device and the main rotor blade configured to communicate a control input force from the pilot input device to the main rotor blade, and a counterweight system in connection with the control input linkage and the power train to apply a centrifugal force to the control input linkage.

公开(公告)号：US10513982B2

公开(公告)日：2019-12-24

申请号：US15439728

申请日：2017-02-22

Applicant: Bell Helicopter Textron Inc.

Inventor： Zachary Edwin Dailey ,  Frank Bradley Stamps ,  Martin Peryea

IPC: B64D33/08 ,  F02C7/36 ,  F02C7/141 ,  F02C7/232 ,  F02C9/40 ,  F02C7/16 ,  F02C3/30 ,  F02C7/22 ,  F02C7/143 ,  F02C9/28 ,  B64C27/00 ,  B64D33/02

Abstract: A rotorcraft has a low density altitude flight mode and a high density altitude flight mode. The rotorcraft includes a turboshaft engine forming a gas path in sequence through an air inlet section, a compressor section, a combustor section, a turbine section and an exhaust section. A drive system is coupled to the engine and is operable responsive to rotation of at least a portion of the turbine section. A rotor is coupled to the drive system and is operable to receive torque and rotational energy therefrom. A fuel injection system supplies fuel to the combustor section. An oxidizer injection system and a coolant injection system are used to selectively inject an oxidizer and a coolant into the gas path when it is desired to operate the rotorcraft in the high density altitude flight mode, thereby increasing the altitude density ceiling of the rotorcraft for maneuvers including takeoffs and landings.