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1.发明授权公开(公告)号：US11927143B2
公开(公告)日：2024-03-12
申请号：US16982289
申请日：2019-03-22
Applicant: GE Avio S.r.l.
Inventor： Giuseppe Donini , Stefano Ettorre , Pierpaolo Forte
CPC classification number: F02C9/58 , F02C9/28 , F05D2220/324 , F05D2220/325 , F05D2270/021
Abstract: An electronic control system (35) for a turbopropeller (2) having a gas turbine engine (20) and a propeller assembly (3) coupled to the gas turbine engine (20), the control system (35) having: a propeller control stage (35a), implementing a closed loop control for controlling operation of the propeller assembly (3) based on a scheduled propeller speed reference (Nrref) and a propeller speed measure (Nr); a gas turbine control stage (35b), implementing a closed loop control for controlling operation of the gas turbine engine (20) based on a scheduled reference (Ngdotref) and at least a feedback quantity. The control system (35) further envisages an auxiliary control stage (35c), coupling the propeller control stage (35a) and the gas turbine control stage (35b) and determining a limitation of the operation of the gas turbine engine (20), if a propeller speed overshoot is detected, with respect to the propeller speed reference (Nrref).
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公开(公告)号：US11286867B2
公开(公告)日：2022-03-29
申请号：US16479797
申请日：2018-01-19
Applicant: GE Avio S.r.l.
Inventor： Stefano Ettorre , Pierpaolo Forte , Giuseppe Donini
IPC: F02C9/30
Abstract: In a fuel control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4): a main fuel regulator (12) determines a demand (Wfdem) of fuel flow (Wf) to be introduced in the gas turbine engine (1), based on an input request (PLA); and a first limiter stage (14), operatively coupled to the main fuel regulator (12), causes an adjustment of the fuel flow (Wf) based on engine safety operating limits. The first limiter stage (14) is provided with a Ngdot limiter (20) to cause an adjustment of the fuel flow (Wf) when the gas generator speed rate of change (Ngdot) is determined to overcome acceleration/deceleration scheduled safety limits; the Ngdot limiter (20) implements a predictor (23), to perform a prediction (Wfdot) of the fuel flow rate of change (Wfdot), or fuel flow (Wf), allowing the gas generator speed rate of change (Ngdot) to track a scheduled reference value (Ngdotref).
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公开(公告)号：US11332234B2
公开(公告)日：2022-05-17
申请号：US16973268
申请日：2019-06-28
Applicant: GE Avio S.r.l.
Inventor： Pierpaolo Forte , Giuseppe Donini , Cristian Lai
Abstract: 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：US11287781B2
公开(公告)日：2022-03-29
申请号：US16485031
申请日：2018-02-16
Applicant: GE Avio S.r.l.
Inventor： Simone Castellani , Giuseppe Donini , Pierpaolo Forte , Cristian Lai
Abstract: An electronic control system (30) for a turbopropeller engine (1) having a gas turbine (2, 4, 5, 6) and a propeller (7), coupled to the gas turbine, the control system (10) having a propeller control unit (14) and a turbine control unit (15) to jointly control engine power output based on an input request (PLA), wherein the propeller control unit (14) has a first reference generator (16), to determine a reference propeller speed (Npref) based on the input request (PLA), and a first regulator (19), to regulate a propeller speed (Np). The propeller control unit (14) has a reference correction stage (31) to apply a correction to the reference propeller speed (Npref) and generate thereby a corrected reference propeller speed (I), and the first regulator (19) regulates the propeller speed (Np) based on the corrected reference propeller speed (I) to achieve optimized efficiency.
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5.发明申请公开(公告)号：US20210017915A1
公开(公告)日：2021-01-21
申请号：US16982289
申请日：2019-03-22
Applicant: GE Avio S.r.l.
Inventor： Giuseppe Donini , Stefano Ettorre , Pierpaolo Forte
Abstract: An electronic control system (35) for a turbopropeller (2) having a gas turbine engine (20) and a propeller assembly (3) coupled to the gas turbine engine (20), the control system (35) having: a propeller control stage (35a), implementing a closed loop control for controlling operation of the propeller assembly (3) based on a scheduled propeller speed reference (Nrref) and a propeller speed measure (Nr); a gas turbine control stage (35b), implementing a closed loop control for controlling operation of the gas turbine engine (20) based on a scheduled reference (Ngdotref) and at least a feedback quantity. The control system (35) further envisages an auxiliary control stage (35c), coupling the propeller control stage (35a) and the gas turbine control stage (35b) and determining a limitation of the operation of the gas turbine engine (20), if a propeller speed overshoot is detected, with respect to the propeller speed reference (Nrref).
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Patent Agency Ranking
公开(公告)号：US20210009278A1
公开(公告)日：2021-01-14
申请号：US16982334
申请日：2019-03-22
Applicant: GE Avio S.r.l.
Inventor： Pierpaolo Forte , Stefano Ettorre , Giuseppe Donini
Abstract: An electronic control system (30) for a turbopropeller engine (12) having a gas turbine (20) and a propeller assembly (13) coupled to the gas turbine (20), controls 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 (2) of the propeller assembly (13). The control system (30) envisages: a propeller speed regulator (39), receiving at its input a propeller speed error (ep), indicative of a difference between a propeller speed measure (Nr) and a propeller speed demand (Nrref), and generating at its output, based on the propeller speed error (ep), a first control quantity (Outi); a propeller pitch regulator (42), receiving at its input a propeller pitch error (ep), indicative of a difference between a propeller pitch demand ( ) and a pitch position measure (β), and generating at its output, based on the propeller pitch error (ep), a first control quantity (Out2); and a priority selection stage (45), configured to implement a priority selection between the first and the second control quantities, for providing at the output the driving quantity (IP), based on the priority selection between the first and the second control quantities.
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公开(公告)号：US11788475B2
公开(公告)日：2023-10-17
申请号：US17699850
申请日：2022-03-21
Applicant: GE Avio S.r.l.
Inventor： Stefano Ettorre , Pierpaolo Forte , Giuseppe Donini
IPC: F02C9/30
CPC classification number: F02C9/30 , F05D2220/32 , F05D2270/05 , F05D2270/309
Abstract: In a fuel control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4): a main fuel regulator (12) determines a demand (Wfdem) of fuel flow (Wf) to be introduced in the gas turbine engine (1), based on an input request (PLA); and a first limiter stage (14), operatively coupled to the main fuel regulator (12), causes an adjustment of the fuel flow (Wf) based on engine safety operating limits. The first limiter stage (14) is provided with a Ngdot limiter (20) to cause an adjustment of the fuel flow (Wf) when the gas generator speed rate of change (Ngdot) is determined to overcome acceleration/deceleration scheduled safety limits; the Ngdot limiter (20) implements a predictor (23), to perform a prediction (Wfdot) of the fuel flow rate of change (Wfdot), or fuel flow (Wf), allowing the gas generator speed rate of change (Ngdot) to track a scheduled reference value (Ngdotref).
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公开(公告)号：US11780600B2
公开(公告)日：2023-10-10
申请号：US16982334
申请日：2019-03-22
Applicant: GE Avio S.r.l.
Inventor： Pierpaolo Forte , Stefano Ettorre , Giuseppe Donini
CPC classification number: B64D31/06 , B64C11/301 , B64C11/305 , B64C11/44 , F02C9/58
Abstract: An electronic control system (30) for a turbopropeller engine (12) having a gas turbine (20) and a propeller assembly (13) coupled to the gas turbine (20), controls 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 (2) of the propeller assembly (13). The control system (30) envisages: a propeller speed regulator (39), receiving at its input a propeller speed error (ep), indicative of a difference between a propeller speed measure (Nr) and a propeller speed demand (Nrref), and generating at its output, based on the propeller speed error (ep), a first control quantity (Outi); a propeller pitch regulator (42), receiving at its input a propeller pitch error (ep), indicative of a difference between a propeller pitch demand ( ) and a pitch position measure (β), and generating at its output, based on the propeller pitch error (ep), a first control quantity (Out2); and a priority selection stage (45), configured to implement a priority selection between the first and the second control quantities, for providing at the output the driving quantity (IP), based on the priority selection between the first and the second control quantities.
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公开(公告)号：US11738855B2
公开(公告)日：2023-08-29
申请号：US16982312
申请日：2019-03-22
Applicant: GE Avio S.r.l.
Inventor： Pierpaolo Forte , Stefano Ettorre , Giuseppe Donini
CPC classification number: B64C11/305 , B64D31/06
Abstract: An electronic control system for a turbopropeller engine having a gas turbine and a propeller assembly coupled to the gas turbine is provided. The control system implements a propeller control unit to control propeller operation using an actuation assembly designed to adjust a pitch angle of propeller blades. 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. The control unit anticipates the increase of the pitch angle before the mechanical lock engagement when transitioning from the ground operating mode to the flight operating mode.
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公开(公告)号：US20210277837A1
公开(公告)日：2021-09-09
申请号：US16479797
申请日：2018-01-19
Applicant: GE Avio S.r.l.
Inventor： Stefano Ettorre , Pierpaolo Forte , Giuseppe Donini
IPC: F02C9/30
Abstract: In a fuel control system (10) for a gas turbine engine (1) having a gas generator (4) and a turbine (6) driven by the gas generator (4): a main fuel regulator (12) determines a demand (Wfdem) of fuel flow (Wf) to be introduced in the gas turbine engine (1), based on an input request (PLA); and a first limiter stage (14), operatively coupled to the main fuel regulator (12), causes an adjustment of the fuel flow (Wf) based on engine safety operating limits. The first limiter stage (14) is provided with a Ngdot limiter (20) to cause an adjustment of the fuel flow (Wf) when the gas generator speed rate of change (Ngdot) is determined to overcome acceleration/deceleration scheduled safety limits; the Ngdot limiter (20) implements a predictor (23), to perform a prediction (Wfdot) of the fuel flow rate of change (Wfdot), or fuel flow (Wf), allowing the gas generator speed rate of change (Ngdot) to track a scheduled reference value (Ngdotref).
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