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

IPC: B64C11/30 ,  F02C9/58 ,  G05B13/02 ,  F04D29/56 ,  B63H3/10 ,  B64D33/02

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.

公开(公告)号：US11204087B2

公开(公告)日：2021-12-21

申请号：US16482011

申请日：2018-01-26

Applicant: GE Avio S.r.l.

Inventor： Marco Garabello ,  Simone Castellani

IPC: F16H55/17 ,  F16H55/06 ,  F02C3/107 ,  G01L3/10

Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), the shaft assembly (95) defining an axial direction and a radial direction, wherein the turbine engine (10) includes a fan or propeller assembly (14) and an engine core (20) and further wherein the fan or propeller assembly (14) includes a gearbox (45). The shaft (assembly 95) includes a coupling shaft (100) defining a plurality of coupling shaft teeth (105) extended in the axial direction, wherein each coupling shaft tooth (105) is in circumferential arrangement along the coupling shaft (100). The coupling shaft (100) includes a first material (103) and the plurality of coupling shaft teeth (105) include a second material (104) different from the first material (103).

公开(公告)号：US11199138B2

公开(公告)日：2021-12-14

申请号：US16482024

申请日：2018-01-24

Applicant: GE Avio S.r.l.

Inventor： Marco Garabello ,  Paolo Altamura ,  Gian Mario Bragallini

IPC: F02C7/32 ,  F16C19/26 ,  F16C33/58 ,  F16C35/063 ,  F16D1/06 ,  F01D5/02 ,  F02C7/36

Abstract: A turbine engine defines an axial direction and a radial direction and includes a shaft assembly, a fan or propeller assembly, an engine core, a coupling shaft, a spacer, a sleeve, and a nut The coupling shaft defines an annular surface extended along the axial direction and a groove extended in a circumferential direction. The spacer defines a first portion disposed in the groove of the coupling shaft. The sleeve defines a threaded portion that extends along the axial direction and is disposed outward of the spacer in the radial direction. The nut defines a plurality of nut threads configured to mate with the plurality of sleeve threads of the sleeve. The nut defines a radial portion adjacent to at least a portion of the sleeve and at least a portion of the spacer in the axial direction.

公开(公告)号：US11155334B2

公开(公告)日：2021-10-26

申请号：US16293771

申请日：2019-03-06

Applicant: GE AVIO S.R.L

Inventor： Andrea Donnini ,  Davide Lercara ,  Alessandro Bordoni

IPC: B64C11/02 ,  B64C11/04 ,  B64D35/00 ,  F01D5/02 ,  F01D11/00 ,  B64C27/32

Abstract: A fan blade support assembly for an aircraft is generally disclosed. The fan blade support assembly includes a fan assembly having a plurality of fan blades, a power shaft extending between the fan assembly and an engine of the aircraft, and a housing assembly positioned around the power shaft. The housing assembly includes a convergent housing and a sealing shroud. The convergent housing includes a cap, a base, and a middle portion extending therebetween. The base defines a first diameter, and the cap defines a second diameter less than the first diameter. The sealing shroud is positioned between the convergent housing and the power shaft. A gap is defined between the sealing shroud and the power shaft.

公开(公告)号：US20210310417A1

公开(公告)日：2021-10-07

申请号：US17168368

申请日：2021-02-05

Applicant: GE Avio S.r.l.

Inventor： Juraj Hrubec ,  Ivan Golovin ,  Davide Lauria

IPC: F02C7/36 ,  F16H1/46 ,  F16H57/08

Abstract: A gearbox for an engine includes a rotating element and a turbomachine, the turbomachine includes a shaft, and the rotating element is driven by the shaft across the gearbox. The gearbox includes a ring gear, a first sun gear and a second sun gear each configured to be driven by the shaft of the turbomachine, a first planet gear comprising a first gear portion and a second gear portion, and a second planet gear comprising a first gear portion and a second gear portion.

公开(公告)号：US20210088114A1

公开(公告)日：2021-03-25

申请号：US17020262

申请日：2020-09-14

Applicant: GE Avio S.r.l.

Inventor： Juraj Hrubec ,  Michele Gravina ,  Leonardo Coviello

IPC: F16H1/48 ,  F16H57/08 ,  F01D15/12

Abstract: An apparatus and method for reducing planet gear misalignment of planet gears mounted on a planet-carrier in an epicyclic gearing. The apparatus and method of the present disclosure specifically provide for a stiffness-reducing feature, a pillar, and a side-plate, each with a respective stiffness. In several embodiments, the feature stiffness is less than the pillar stiffness which is at least 10% less than the side-plate stiffness. The stiffness-reducing feature and the pillar may make up a pylon which has an axis. The pylon axis may form an angle with the side plate which is less than 90° and greater than 20°.

公开(公告)号：US20210087939A1

公开(公告)日：2021-03-25

申请号：US16936567

申请日：2020-07-23

Applicant: GE Avio S.r.l.

Inventor： Antonio Giusseppe D'Ettole ,  Andrea Depalma ,  Roberto Maddaleno ,  Matteo Renato Usseglio

IPC: F01D5/22 ,  F01D11/12

Abstract: A turbine engine with an outer rotor that circumscribes an inner rotor or inner stator. The outer rotor includes circumferentially arranged components with a radial outer end and radial inner end. Inner ends of confronting sides of adjacent components include at least one damper element to dampen the relative motion of the components or to provide at least a partial seal between adjacent components.

公开(公告)号：US20210047933A1

公开(公告)日：2021-02-18

申请号：US16988817

申请日：2020-08-10

Applicant: GE Avio S.r.l.

Inventor： Matteo Renato Usseglio ,  Antonio Giuseppe D'Ettole ,  Andrea Depalma

IPC: F01D5/20 ,  F01D5/32

Abstract: A blade for a turbomachine includes a blade root portion for securing the blade to a rotatable annular outer drum rotor. The blade root portion includes one or more radial retention features for radially retaining each of the blade root portions within the rotatable annular outer drum rotor. Further, at least one of the radial retention feature(s) includes at least one sealing member integrated therewith.

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

IPC: F02C9/58 ,  F02C9/28

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).

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

IPC: B64D31/06 ,  B64C11/30 ,  B64C11/34 ,  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.