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公开(公告)号：US20240151240A1
公开(公告)日：2024-05-09
申请号：US18316656
申请日：2023-05-12
Applicant: GE Avio S.r.l.
Inventor： Paolo Altamura , Giulio Zagato
CPC classification number: F04D29/323 , B64C11/32 , F05D2220/32 , F05D2260/74 , F05D2260/79
Abstract: A gas turbine engine includes a turbomachine comprising a compressor section, a combustion section, and a turbine section arranged in serial flow order; a fan defining a fan axis and comprising a plurality of fan blades rotatable about the fan axis; and a pitch change mechanism operable with the plurality of fan blades to control a pitch of the plurality of fan blades. The pitch change mechanism imparts a torque to each fan blade of the plurality of fan blades via first and second forces imparted in opposite directions to each fan blade of the plurality of fan blades.
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公开(公告)号：US11975816B2
公开(公告)日：2024-05-07
申请号：US17771825
申请日：2020-09-08
Applicant: László Kruppa
Inventor： László Kruppa
IPC: B64C11/32
CPC classification number: B64C11/32
Abstract: An improved efficiency propeller for aircraft includes a blade structure mounted onto a propeller hub, a servo unit, and a cantilevered base. A distinctive feature of the disclosure is that the blade structure includes a main mast, which is mounted onto a propeller hub and forms the spine of the leading edge of the blade structure, and at least one secondary mast aligned with the main mast, and turning spacers with struts are mounted onto the main mast, and the struts are covered by lateral pieces of a skin module, and the overlapping and flexible lateral pieces of the skin module form a skin.
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公开(公告)号：US20240051688A1
公开(公告)日：2024-02-15
申请号：US18280173
申请日：2022-03-01
Applicant: TIDAV
Inventor： Philippe VALERO , Vivien JOURDON , Cédric LEFORT
CPC classification number: B64U10/20 , B64C29/0033 , B64C11/306 , B64C5/06 , B64U30/20 , B64C11/32 , B64U2101/00
Abstract: The invention relates to a hybrid vertical take-off and landing drone comprising at least two substantially parallel fixed wings (12, 14) each comprising at least two fins (16a, 16b, 18a, 18b) distributed on either side of a roll axis (200) of the drone and individually controlled, characterized in that it comprises at least two counter-rotating rotors (20a, 20b) with a collective pitch system (24a, 24b) and a swashplate (26a, 26b), which are arranged between two wings on either side of the roll axis (200a), individually controlled and articulated so as to allow independent tilting of each rotor on a tilt axis (22a, 22b) substantially parallel to the pitch axis of the drone, the rotational axis of the blades of each rotor being substantially perpendicular to said tilt axis.
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公开(公告)号：US20240051656A1
公开(公告)日：2024-02-15
申请号：US18085112
申请日：2022-12-20
Inventor： Amit Zutshi , Rafal Sarba , James Ryan Reepmeyer , Stefan Joseph Cafaro , Inenhe Mohammed Khalid , Daniel Edward Mollmann , Arjan Johannes Hegeman
Abstract: An open rotor aeronautical engine may include a core engine, a plurality of unducted airfoils, and a pitch change assembly. The pitch change assembly may include an ensemble actuator assembly and a unitary actuator assembly. The ensemble actuator assembly may have one or more ensemble actuators and a unison ring that is movable by actuation of the one or more ensemble actuators to collectively change a pitch angle of the plurality of unducted airfoils. The unitary actuator assembly comprising a plurality of unitary actuators respectively coupled to a corresponding one of the plurality of unducted airfoils, the plurality of unitary actuators respectively movable to change the pitch angle of the corresponding one of the plurality of unducted airfoils.
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公开(公告)号：US20240035550A1
公开(公告)日：2024-02-01
申请号：US18039779
申请日：2021-11-29
Applicant: Rolls-Royce Deutschland Ltd & Co KG
Inventor： Jens WEIDAUER
CPC classification number: F16H25/205 , F16H25/24 , B64C11/44 , B64C11/32 , F16H2025/2075 , F16H2025/2084
Abstract: A control device includes a mechanical system for moving a mechanical slide. The control device further includes a first electric drive configured to receive a position target value and to drive the mechanical system to move the mechanical slide to the position target value. The control device also includes a second electric drive configured to receive the same position target value and to drive the mechanical system to move the mechanical slide to the position target value. The two electric drives are provided and configured to jointly and simultaneously drive the mechanical system and, upon the other electric drive failing, to drive the mechanical system alone and, upon their own failure, not to obstruct the mechanical system from then being driven only by the other electric drive.
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Patent Agency Ranking
公开(公告)号：US11851158B2
公开(公告)日：2023-12-26
申请号：US17991302
申请日：2022-11-21
Applicant: General Electric Company
Inventor： Daniel A. Niergarth
CPC classification number: B64C11/32 , B64C11/346 , F01D7/00 , F04D29/323 , F05D2220/36 , F05D2260/74
Abstract: A variable pitch fan assembly includes a plurality of rotating trunnion assemblies, a plurality of counterweight assemblies, a first unison ring gear engaged with the trunnion assemblies, and a second unison ring member that restricts out of synch movement of the counterweights relative to each other.
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公开(公告)号：US11548617B2
公开(公告)日：2023-01-10
申请号：US16439055
申请日：2019-06-12
Applicant: Bell Helicopter Textron Inc.
Inventor： Carlos Alexander Fenny , Nicholas Brodeur , Louis Charron , Kevin Morris
Abstract: A method of pitching rotor blades by interrupting torque applied to the hub.
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公开(公告)号：US20220355924A1
公开(公告)日：2022-11-10
申请号：US17307845
申请日：2021-05-04
Applicant: Bell Textron Inc.
Inventor： Thomas C. Parham, JR. , Frank Bradley Stamps , Jouyoung Jason Choi , Albert Gerard Brand , Michael Scott Seifert , Richard E. Rauber , John E. Brunken, JR.
Abstract: A gimbaled rotor assembly for an aircraft. The gimbaled rotor assembly including a static mast; a spherical bearing comprising an inner component and an outer component pivotable relative to each other about a bearing focus, the inner component fixedly coupled to the static mast; a rotor hub rotatably coupled to the outer component, allowing for relative rotation of the rotor hub about a rotor axis and for pivoting together with the outer component about the bearing focus; and a primary hub spring coupling the outer component to the static mast and configured for opposing pivoting of the rotor hub about the bearing focus from a neutral position.
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公开(公告)号：US11254419B2
公开(公告)日：2022-02-22
申请号：US17001391
申请日：2020-08-24
Applicant: Kitty Hawk Corporation
Inventor： Damon Vander Lind , Todd Reichert
Abstract: A propeller includes a blade free to rotate. A first stop is positioned to mechanically engage one or both of a first portion of the blade and a first structure coupled to the blade when the blade is in a first position at a first end of the rotational range of motion. A second stop is positioned to mechanically engage one or both of a second portion of the blade and a second structure coupled to the blade when the blade is in a second position at a second end of the defined rotational range. The blade rotates to the first position against the first stop when the propeller is rotated in a first direction and to the second position against the second stop when the propeller is rotated in a second direction.
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公开(公告)号：US11203426B1
公开(公告)日：2021-12-21
申请号：US16903831
申请日：2020-06-17
Applicant: Bell Textron Inc.
Inventor： Elizabeth Feeley , Karl H. Schroeder
Abstract: One embodiment is a rotor system comprising a duct ring; a hub disposed centrally to the duct ring; first and second stators each connected between the duct ring and the hub; first and second control vanes rotatably connected to the first and second stators, respectively; and a structural hoop having a first end connected to the first control vane and a second end connected to the second control vane, the structural hoop for translating rotation of the first control vane about a vane axis to the second control vane.
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