-
公开(公告)号：US11865382B2
公开(公告)日：2024-01-09
申请号：US17158496
申请日：2021-01-26
Applicant: Bell Textron Inc.
Inventor： Thomas Dewey Parsons , Keith David Weaver , Chris James Ludtke , Paul Madej , Andrew Jordan Birkenheuer
CPC classification number: A62C3/08 , A62C31/02 , A62C35/023 , A62C35/68
Abstract: Embodiments are directed to a rotorcraft comprising an airframe having an engine compartment, an engine disposed within the engine compartment, at least one fire bottle configured to hold a fire extinguishing agent, at least one agent tube coupled to the fire bottle and configured to carry the fire extinguishing agent to the engine compartment, and a nozzle on the at least one agent tube, the nozzle positioned above the engine and oriented in a downward-facing direction. The nozzle has at least one opening and is configured to allow liquid to drain out of the at least one opening instead of allowing the liquid to flow into the at least one agent tube. The nozzle may have a chamfer opening that faces downward.
-
公开(公告)号：US11898500B2
公开(公告)日：2024-02-13
申请号：US17130358
申请日：2020-12-22
Applicant: Bell Textron Inc.
Inventor： Thomas Dewey Parsons
CPC classification number: F02C9/20 , F02C7/057 , F02C7/26 , F02C7/262 , F05D2220/323 , F05D2260/85 , F05D2270/02 , F05D2270/09
Abstract: Embodiments are directed to systems and methods for controlling an aircraft engine inlet comprises determining a required engine RPM for an engine in-flight restart based upon current aircraft parameters, detecting a command to initiate the engine in-flight restart, and managing a position of an engine inlet barrier to control a volume of air entering an engine intake, wherein the ram air causes an engine turbine to achieve the required engine RPM. The required engine RPM may be an N1 gas generator RPM. The engine inlet barrier may be a hinged door positioned within the engine inlet or a series of inlet variable guide vanes that are configured to rotate between a closed position and an opened position. The position of the engine inlet barrier may be controlled by a flight control computer or an engine control computer.
-
公开(公告)号：US20220233898A1
公开(公告)日：2022-07-28
申请号：US17158496
申请日：2021-01-26
Applicant: Bell Textron Inc.
Inventor： Thomas Dewey Parsons , Keith David Weaver , Chris James Ludtke , Paul Madej , Andrew Jordan Birkenheuer
Abstract: Embodiments are directed to a rotorcraft comprising an airframe having an engine compartment, an engine disposed within the engine compartment, at least one fire bottle configured to hold a fire extinguishing agent, at least one agent tube coupled to the fire bottle and configured to carry the fire extinguishing agent to the engine compartment, and a nozzle on the at least one agent tube, the nozzle positioned above the engine and oriented in a downward-facing direction. The nozzle has at least one opening and is configured to allow liquid to drain out of the at least one opening instead of allowing the liquid to flow into the at least one agent tube. The nozzle may have a chamfer opening that faces downward.
-
公开(公告)号：US11975860B2
公开(公告)日：2024-05-07
申请号：US17569996
申请日：2022-01-06
Applicant: Bell Textron Inc.
Inventor： Thomas Dewey Parsons
CPC classification number: B64D31/06 , F02C9/42 , F05D2220/329 , F05D2270/093 , F05D2270/13
Abstract: Various implementations described herein are directed to an aircraft having a multi-engine configuration with multiple engines. The aircraft may have a flight control system coupled to the multiple engines with a multi-engine interface. The flight control system may be configured to shutdown at least one engine of the multiple engines during reduced-engine operation by continuously calculating altitude for the reduced-engine operation based on one or more of an aircraft descent rate of the aircraft and an engine restart time of the at least one engine.
-
Patent Agency Ranking
公开(公告)号：US20230211876A1
公开(公告)日：2023-07-06
申请号：US17569996
申请日：2022-01-06
Applicant: Bell Textron Inc.
Inventor： Thomas Dewey Parsons
CPC classification number: B64C27/12 , B64D31/12 , B64D31/10 , B64D45/04 , F02C9/42 , F05D2220/329 , F05D2270/093 , F05D2270/13
Abstract: Various implementations described herein are directed to an aircraft having a multi-engine configuration with multiple engines. The aircraft may have a flight control system coupled to the multiple engines with a multi-engine interface. The flight control system may be configured to shutdown at least one engine of the multiple engines during reduced-engine operation by continuously calculating altitude for the reduced-engine operation based on one or more of an aircraft descent rate of the aircraft and an engine restart time of the at least one engine.
-
公开(公告)号：US20220195946A1
公开(公告)日：2022-06-23
申请号：US17130358
申请日：2020-12-22
Applicant: Bell Textron Inc.
Inventor： Thomas Dewey Parsons
IPC: F02C9/20
Abstract: Embodiments are directed to systems and methods for controlling an aircraft engine inlet comprises determining a required engine RPM for an engine in-flight restart based upon current aircraft parameters, detecting a command to initiate the engine in-flight restart, and managing a position of an engine inlet barrier to control a volume of air entering an engine intake, wherein the ram air causes an engine turbine to achieve the required engine RPM. The required engine RPM may be an N1 gas generator RPM. The engine inlet barrier may be a hinged door positioned within the engine inlet or a series of inlet variable guide vanes that are configured to rotate between a closed position and an opened position. The position of the engine inlet barrier may be controlled by a flight control computer or an engine control computer.
-
公开(公告)号：US20220073197A1
公开(公告)日：2022-03-10
申请号：US17511724
申请日：2021-10-27
Applicant: Bell Textron Inc.
Inventor： Carlos Fenny , Thomas Dewey Parsons , Erik John Oltheten
Abstract: The present invention includes an a plurality of first variable speed motors 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.
-
公开(公告)号：US11242798B2
公开(公告)日：2022-02-08
申请号：US16294266
申请日：2019-03-06
Applicant: Bell Textron Inc.
Inventor： David Haynes , Thomas Dewey Parsons , Shahryar Fotovati
Abstract: An aircraft includes a fuselage and an engine housed in the fuselage. A ram-air engine inlet is formed on an exterior of the fuselage. The ram-air engine inlet is defined, at least in part, by a cowling door. The cowling door is moveable between a closed position and an open position. An intake duct fluidly couples the ram-air engine inlet to the engine. A filter is disposed across the intake duct. A bypass duct is formed in the ram-air engine inlet aft of the intake duct. The bypass duct is operable to be selectively opened and closed.
-
公开(公告)号：US20210403168A1
公开(公告)日：2021-12-30
申请号：US16915002
申请日：2020-06-29
Applicant: Bell Textron Inc.
Inventor： Thomas Dewey Parsons , James E. Sobel , Alan Hisashi Steinert , David Henderson Loe
Abstract: A hybrid propulsion system for a tiltrotor aircraft comprises one or more engines that provide thrust whenever the tiltrotor aircraft is in a first forward flight mode, one or more electrical or hydraulic power sources, and two or more pylon assemblies. Each pylon assembly houses one or more electric or hydraulic motors connected to the one or more electrical or hydraulic power sources and a proprotor. All or part of each pylon assembly is rotatable. The proprotors provide lift whenever the tiltrotor aircraft is in a vertical takeoff and landing mode and a hover mode, and provide thrust whenever the tiltrotor aircraft is in a second forward flight mode.
-
-
-
-
-
-
-
-
Search Results
9
records
(took 0.014 seconds)
