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公开(公告)号：US11993362B2
公开(公告)日：2024-05-28
申请号：US17509048
申请日：2021-10-24
摘要： Systems and methods include providing an aircraft with a direct drive dual-concentric valve (D3V) having a body, an outer secondary spool coaxially located within a bore of the body and linearly displaceable relative to the body, an inner primary spool coaxially located within a bore of the secondary spool and linearly displaceable relative to the secondary spool and the body. A plurality of piezo stacks is coupled to a first end of the primary spool, and applying a voltage to at least one of the piezo stacks causes an output stroke of the plurality of the piezo strokes for displacing the primary spool. The secondary spool is displaced together with the primary spool relative to the body if displacement of the primary spool relative to the secondary spool cannot occur.
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公开(公告)号：US11982190B2
公开(公告)日：2024-05-14
申请号：US17165108
申请日：2021-02-02
发明人： Jagoda Krzywon
CPC分类号： F01D15/02 , B64C11/303 , B64C11/38 , B64C11/385 , B64C27/64 , F01D7/00 , F01D15/12 , F05D2270/64
摘要： A propeller control unit (PCU) for controlling pitch angles of blades of a propeller, has: a pitch angle actuator; a servo valve hydraulically connected to the pitch angle actuator and to a first hydraulic fluid source; and a feather valve having a body movable within a cavity, the feather valve having a first actuation port and a second actuation port both in fluid communication with the cavity, the body between the first actuation port and the second actuation port, the body being movable to selectively hydraulically connect the pitch angle actuator to the servo valve through the feather valve or to hydraulically connect the pitch angle actuator to a drain line through the feather valve, the first actuation port and the second actuation port hydraulically connected to a second hydraulic fluid source independent from the first hydraulic fluid source.
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公开(公告)号：US11905840B2
公开(公告)日：2024-02-20
申请号：US17163881
申请日：2021-02-01
发明人： Jagoda Krzywon
CPC分类号： F01D21/003 , B64C11/385 , B64C11/40 , F01D7/02 , F01D21/14 , B64D2045/0085 , F05D2220/323 , F05D2260/80 , F05D2270/02 , F05D2270/09 , F05D2270/304 , F05D2270/807
摘要： A sensor signal produced by a sensor as a feedback device rotates with a propeller about an axis and moves along the axis with adjustment of a blade angle of the propeller is received, the sensor signal indicative of a rotational speed and of the blade angle of the propeller. From the sensor signal, it is determined whether the rotational speed is within a predetermined range of a reference speed and an expected change in the blade angle has occurred in response to a command to adjust the blade angle to maintain the rotational speed at the reference speed. In response to determining that the rotational speed is within the predetermined range of the reference speed and the expected change in the blade angle has failed to occur in response to the command, inoperable movement of the feedback device along the axis is determined and an alert is output.
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公开(公告)号：US11753143B2
公开(公告)日：2023-09-12
申请号：US17626655
申请日：2020-07-16
CPC分类号： B64C11/385 , B64C11/06 , F01D7/02 , F04D29/323 , B64D2027/005 , F05B2260/74 , F05D2260/79
摘要： The invention relates to a module of a turbomachine of longitudinal axis X, the module comprising: ⋅—a rotary casing (31) that rotates about the longitudinal axis and bears a propeller (2; 20, 21, 22) which is provided with a plurality of blades (32); ⋅—a fixed casing (48) comprising a cylindrical wall (49) extending between an inner wall (40) and an outer wall (41) of the rotary casing (31); and, ⋅—a system (30) for changing the pitch of the blades of the propeller, mounted around the fixed casing and comprising: a control means (55) comprising a movable body (57) that is able to move axially on said fixed casing, at least one load transfer bearing (56) comprising an inner ring (65) that is connected to the movable body (57), and an outer ring (66); and a connection mechanism (61) for connecting the outer ring (66) to the blades of the propeller. According to the invention, the module further comprises a feathering device (70) for feathering the blades of the propeller, this device (70) comprising an annular row of springs (71) that are arranged around said fixed casing and extend axially, the springs (71) comprising first axial ends (72) that bear against a ferrule (51) of the fixed casing, and opposite second axial ends (73) that bear against said inner ring (65).
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公开(公告)号：US11530027B2
公开(公告)日：2022-12-20
申请号：US16700259
申请日：2019-12-02
发明人： Jagoda Krzywon
IPC分类号： B64C11/38
摘要： A propeller control unit (PCU) has: a pitch angle actuator; a valve operable to selectively fluidly connect the pitch angle actuator with a source of oil for controlling pitch angles of blades of a propeller and with a drain line for draining oil out of the pitch angle actuator for feathering the blades; and a bypass line having an inlet hydraulically between the valve and an inlet of the drain line, the bypass line having an outlet hydraulically between the inlet of the drain line and an outlet of the drain line.
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公开(公告)号：US11472534B2
公开(公告)日：2022-10-18
申请号：US16457116
申请日：2019-06-28
申请人： The Boeing Company
IPC分类号： B64C11/06 , B64C11/32 , B64C27/605 , B64C11/38
摘要： Rotor hubs having pitch control systems and related methods are disclosed herein. An example apparatus includes a housing including a first housing arm to support a first blade grip and a first blade spindle and a second housing arm to support a second blade grip and a second blade spindle. The example apparatus includes a first pitch link and a second pitch link. The example apparatus includes a first pitch arm coupled to the first pitch link and one of the first blade grip or the first blade spindle and a second pitch arm coupled to the second pitch link and one of the second blade grip or the second blade spindle. The second pitch arm is to extend past the first housing arm to couple with the one of the second blade grip or the second blade spindle.
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公开(公告)号：US11274676B2
公开(公告)日：2022-03-15
申请号：US16067744
申请日：2016-12-22
IPC分类号： F04D29/36 , F01D7/00 , F04D29/059 , B64C11/38 , F04D29/32 , F04D29/056 , F01D25/16 , F02K3/06
摘要： A ducted fan module with variable-pitch blades for a turbo engine includes a rotor carrying a plurality of blades, a stationary casing, and a blade pitch changing and control system. The rotor includes a central shaft and a surrounding blade support ring. A front end of the blade support ring is connected to a front end of the central shaft, creating a rearward-opening annular space between the blade support ring and the central shaft. A tubular part is connected to the stationary casing and extends into the annular space.
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公开(公告)号：US20210362838A1
公开(公告)日：2021-11-25
申请号：US16973268
申请日：2019-06-28
申请人： GE Avio S.r.l.
发明人： Pierpaolo Forte , Giuseppe Donini , Cristian Lai
摘要： A control system (50) for an electro-hydraulic servo-actuator (26) envisages: a controller (55), to generate a control current (Ic), designed to control actuation of the electro-hydraulic servo-actuator (26), implementing a position control loop based on a position error (ep), the position error (ep) being a difference between a reference position (Posref) and a measured position (Posmeas) of the electro-hydraulic servo-actuator (26); and a limitation stage (58), coupled to the controller (55) to provide a limitation of the actuator speed of the electro-hydraulic servo-actuator (26); the limitation stage (58) limits a rate of change of a driving current (Id) to be supplied to the electro-hydraulic servo-actuator (26), in order to limit the actuator speed.
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公开(公告)号：US20210009252A1
公开(公告)日：2021-01-14
申请号：US16982312
申请日：2019-03-22
申请人： GE Avio S.r.l.
摘要： An electronic control system (35) for a turbopropeller engine (2) having a gas turbine (20) and a propeller assembly (3) coupled to the gas turbine (20), the control system (35) implementing a propeller control unit (PEC) to control propeller operation based on a pilot input request, via generation of a driving quantity (Ip) for an actuation assembly (29) designed to adjust a pitch angle (β) of propeller blades (10). The control unit engages a mechanical lock determining a minimum flight value for the pitch angle during a flight operating mode, and disengages the mechanical lock and controls the pitch angle below the minimum flight value, up to a minimum ground value lower than the minimum flight value, during a ground operating mode; the propeller control unit, during a transition from the ground operating mode to the flight operating mode, engages the mechanical lock, thereby causing an increase of the pitch angle towards the minimum flight value independently from the control action. In particular, the control unit anticipates the increase of the pitch angle in a time period (T) before the mechanical lock engagement due to transition from the ground operating mode to the flight operating mode.
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公开(公告)号：US10793255B2
公开(公告)日：2020-10-06
申请号：US15228148
申请日：2016-08-04
摘要： Systems and methods are disclosed for controlling the pitch angle of a propeller and rotor assembly that selectively limit the pitch angle according to a selected mode of operation. The system includes an actuator having forward and aft chambers, an oil transfer bearing (OTB), and a fine stop collar. The fine stop collar including a first passage in fluid communication with the OTB and forward chamber during a ground-based mode of operation, and a second fluid passage being in fluid communication with the OTB and forward chamber during a flight-based mode of operation.
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