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1. 发明申请

WO2020002692A1 CONTROL SYSTEM AND METHOD FOR AN ELECTRO-HYDRAULIC SERVO-ACTUATOR, IN PARTICULAR OF A TURBOPROPELLER ENGINE 审中-公开
公开(公告)号：WO2020002692A1
公开(公告)日：2020-01-02
申请号：PCT/EP2019/067495
申请日：2019-06-28
申请人： GE AVIO S.R.L.
发明人： FORTE, Pierpaolo , LAI, Cristian , DONINI, Giuseppe
IPC分类号： B64C11/44
摘要： A control system (50) for an electro-hydraulic servo-actuator (26) envisages: a controller (55), to generate a control current (I c ), designed to control actuation of the electro-hydraulic servo-actuator (26), implementing a position control loop based on a position error (e p ), the position error (e p ) being a difference between a reference position (Pos ref ) and a measured position (Pos meas ) 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 (I d ) to be supplied to the electro-hydraulic servo-actuator (26), in order to limit the actuator speed.

2. 发明申请

WO2015015425A1 GEARBOX AND DISASSEMBLY METHOD FOR DISENGAGING A DRIVE SHAFT IN SUCH A GEARBOX 审中-公开
标题翻译：用于消除这种齿轮箱中的驱动轴的齿轮箱和拆卸方法
公开(公告)号：WO2015015425A1
公开(公告)日：2015-02-05
申请号：PCT/IB2014/063526
申请日：2014-07-29
申请人： GE AVIO S.R.L.
发明人： KOWALEWSKI, Tomasz , BORRA, Ivan , BRAGALLINI, Gian Mario , GIORDANO, Vincenzo
IPC分类号： F02C7/32 , F16D1/08
CPC分类号： F16D1/108 , F02C7/32 , F05D2230/70 , F16D1/0876 , F16D1/10 , F16H1/14
摘要： A gearbox (1) has a main unit (22) and a secondary unit (2) provided with respective casings (23,3) of respective gear transmissions and with respective hollow shafts (24,10) connected by means of a drive shaft (25); the secondary unit transfers motion between two axes forming an angle of less than 180° and which can be removed after having released the drive shaft (25); the drive shaft (25) is engaged in an angularly fixed and axially sliding manner to the hollow shafts and is axially locked, at least in one direction, by means of an axial retaining device (57), which is releasable; the axial retaining device (57) is coupled to one (24) of the hollow shafts, at an axial end (32) which is facing towards the other (10) of the hollow shafts; at least one opening may be formed between the two casings (23,3), so as to access such an axial end (32) and release the axial retaining device.
摘要翻译：齿轮箱（1）具有设置有相应齿轮传动装置的相应壳体（23,3）的主单元（22）和次级单元（2），并且具有通过驱动轴连接的相应空心轴（24,10） 25）; 次级单元在形成小于180°的角度的两个轴之间传递运动，并且可以在释放驱动轴（25）之后被移除; 驱动轴（25）以角度固定和轴向滑动的方式接合到空心轴，并且通过可释放的轴向保持装置（57）至少沿一个方向轴向锁定; 所述轴向保持装置（57）在朝向所述空心轴的另一个（10）的轴向端（32）处联接到一个（24）的所述空心轴; 可以在两个壳体（23,3）之间形成至少一个开口，以便接近这样的轴向端部（32）并且释放轴向保持装置。

3. 发明申请

WO2019180260A1 SYSTEM AND METHOD FOR PROPELLER RESPONSE ENHANCEMENT DURING TRANSITION FROM GROUND TO FLIGHT CONFIGURATION FOR A TURBOPROPELLER ENGINE 审中-公开
公开(公告)号：WO2019180260A1
公开(公告)日：2019-09-26
申请号：PCT/EP2019/057342
申请日：2019-03-22
申请人： GE AVIO S.R.L.
发明人： FORTE, Pierpaolo , ETTORRE, Stefano , DONINI, Giuseppe
IPC分类号： B64C11/30 , B64C11/06 , B64C27/57 , B64D31/06 , F02C9/58 , B64C11/32 , B64C11/44 , B64C11/38
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 (I p ) 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.

4. 发明申请

WO2019180250A1 SYSTEM AND METHOD FOR COMBINED PROPELLER SPEED AND PROPELLER PITCH CONTROL FOR A TURBOPROPELLER ENGINE 审中-公开
公开(公告)号：WO2019180250A1
公开(公告)日：2019-09-26
申请号：PCT/EP2019/057329
申请日：2019-03-22
申请人： GE AVIO S.R.L.
发明人： FORTE, Pierpaolo , ETTORRE, Stefano , DONINI, Giuseppe
IPC分类号： B64C11/30 , B64C11/34 , B64D31/06 , F02C9/58 , G05B13/02 , B64D27/00
摘要： 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 second 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.

5. 发明申请

WO2018195559A3 DUAL-WINDING SYNCHRONOUS RELUCTANCE MACHINE COMPOSED OF AN EXCITATION WINDING AND A SEPARATE POWER WINDING 审中-公开
公开(公告)号：WO2018195559A3
公开(公告)日：2018-10-25
申请号：PCT/US2018/032690
申请日：2018-05-15
申请人： GE AVIO S.R.L. , GENERAL ELECTRIC COMPANY
发明人： RONCHETTO, Davide
IPC分类号： H02K3/28 , H02K11/042 , H02P1/16 , H02P25/08
摘要： A rotating field machine (200) including a stator (140) and a rotor (150) are provided. In particular, a dual-winding rotating field machine (200) in which the stator (140) includes two separate windings can be provided. In one example implementation, the stator (140) can include an excitation winding (220) configured to control an excitation current and a power winding (230) configured to control power flow to an electrical system. The dual-winding rotating field machine (200) can further include a starting mode and a generating mode. During the starting mode, both the excitation winding (220) and the power winding (230) can be coupled to one or more switching power converters (170). During the generating mode, the power winding (230) can be coupled to a variable frequency bus and the power converter (170) can be used to manage excitation power only.

6. 发明申请

WO2018162485A1 TURBINE AIRFOIL ARRANGEMENT INCORPORATING SPLITTERS 审中-公开
公开(公告)号：WO2018162485A1
公开(公告)日：2018-09-13
申请号：PCT/EP2018/055480
申请日：2018-03-06
申请人： GENERAL ELECTRIC COMPANY , GE AVIO S.R.L.
发明人： CLEMENTS, Jeffrey Donald , MANOHARAN, Mahendran , BERTINI, Francesco , WADIA, Aspi Rustom , AVANCHA, Ravikanth Venkata , SESHADRI, Ganesh , VITT, Paul Hadley
IPC分类号： F01D5/14 , F01D9/04
摘要： A turbomachinery apparatus (10) includes: a turbine (22), including: a turbine component (36) defining at least one arcuate flowpath surface (40); an array of axial-flow turbine airfoils (46) extending from the flowpath surface, the turbine airfoils defining spaces therebetween; and a plurality of splitter airfoils (146) extending from the at least one flowpath surface, in the spaces between the turbine airfoils, each splitter airfoil having opposed pressure and suction sides extending between a leading edge and a trailing edge, wherein the splitter airfoils have a thickness ratio which is less than a thickness ratio of the turbine airfoils.

7. 发明申请

WO2018138291A1 MAGNETIC TORQUE METERING SYSTEM 审中-公开
公开(公告)号：WO2018138291A1
公开(公告)日：2018-08-02
申请号：PCT/EP2018/052007
申请日：2018-01-26
申请人： GE AVIO S.R.L.
发明人： GARABELLO, Marco , CASTELLANI, Simone
IPC分类号： F01D17/04 , F02C3/107 , G01L3/10
摘要： 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).

8. 发明申请

WO2018138155A1 METHOD AND SYSTEM OF CONNECTING A TURBINE ENGINE GEARBOX TO ENGINE CORE 审中-公开
公开(公告)号：WO2018138155A1
公开(公告)日：2018-08-02
申请号：PCT/EP2018/051738
申请日：2018-01-24
申请人： GE AVIO S.R.L.
发明人： GARABELLO, Marco , ALTAMURA, Paolo , BRAGALLINI, Gian Mario , GARGIOLI, Alessio , BISKUPSKI, Jan
IPC分类号： F02C7/36 , F01D5/02
摘要： The present disclosure is directed to a turbine engine (10) defining an axial direction and a radial direction. The turbine engine includes a fan or propeller assembly (14) comprising a gearbox; an engine core (20) comprising one or more rotors, wherein at least one of the rotors defines an axially extended annular hub; and a flexible coupling shaft (100) defining a first end and a second end along the axial direction, wherein the first end is connected to the engine core and the second end is connected to the gearbox, and further wherein the flexible coupling shaft extends from the one or more rotors to the gearbox in the axial direction and inward of the hub in the radial direction.

9. 发明申请

WO2017211744A1 TESTING APPARATUS FOR GEARS 审中-公开
标题翻译：齿轮试验装置
公开(公告)号：WO2017211744A1
公开(公告)日：2017-12-14
申请号：PCT/EP2017/063561
申请日：2017-06-02
申请人： GE AVIO S.R.L.
发明人： GRAVINA, Michele , PERONA, Elio , ROCCA, Guido
IPC分类号： G01M13/02 , G01N3/04 , G01N3/34
CPC分类号： G01M13/021 , G01N3/04 , G01N3/34
摘要： A test apparatus (5) for testing a gear (2) having a central axis has a force application column (35) moveable along a force application axis (F) so as to apply a force onto the flank of a tooth (3) of the gear (2), and a clamping device (12) having a clamping axis (A) orthogonal to and spaced apart from the force application axis (F); the clamping device secures the gear (2) in such a manner that the central axis of the gear coincides with the clamping axis (A); the column (35) has a first and a second end (36, 37) and one intermediate portion (38), which is elastically deformable so as to allow for a displacement of the second end (37) in relation to the first end (36) along a displacement direction (D1) orthogonal to the clamping axis (A) and to the force application axis (F).
摘要翻译：用于测试具有中心轴线的齿轮（2）的测试设备（5）具有可沿着施力轴线（F）移动的施力柱（35），以将力施加到所述齿轮（2）的齿（3）的侧面和夹紧装置（12），所述夹紧装置具有与所述施力轴线（F）正交且与所述施力轴线（F）间隔开的夹紧轴线（A）; 夹紧装置以这样的方式固定齿轮（2），使得齿轮的中心轴线与夹紧轴线（A）重合; 柱（35）具有可弹性变形的第一和第二端部（36,37）和一个中间部分（38），以允许第二端部（37）相对于第一端部（37）移位沿着与夹紧轴线（A）和施力轴线（F）正交的位移方向（D1）移动（36）。

10. 发明申请

WO2016071881A1 PROCESS FOR MANUFACTURING A PIECE HAVING A RELATIVELY BIG SIZE, IN PARTICULAR FOR MANUFACTURING A BLADE FOR A TURBINE ENGINE 审中-公开
标题翻译：制造具有相当大尺寸的特征的方法，特别是用于制造涡轮发动机的叶片
公开(公告)号：WO2016071881A1
公开(公告)日：2016-05-12
申请号：PCT/IB2015/058591
申请日：2015-11-06
申请人： GE AVIO S.R.L.
发明人： VARETTI, Mauro
IPC分类号： B23P15/04 , F01D5/14
CPC分类号： B23P15/04 , F01D5/147 , F05D2220/32 , F05D2230/233 , F05D2230/31 , F05D2230/51
摘要： According to a process for manufacturing a piece having a relatively big size, in particular a blade for a turbine engine, at least two sectors (2) are manufactured separately from each another, so that each of them comprises: a portion (15) having substantially the same shape and size of a corresponding portion of the piece to be made, at least one coupling surface (14) which is complementary to a corresponding coupling surface of the other sector (2), and a continuous outer flange (16) at each of said coupling surfaces (14); the sectors (2) are rested against each other at the coupling surfaces (14) and are then fastened to each other by means of an electron beam welding, carried out under vacuum, so as to weld the outer flanges (16) along the entire outer perimeter of the coupling surfaces (14), and by means of a subsequent hot isostatic compression; after the fastening, the flanges (16) are removed by means of a material removal machining.
摘要翻译：根据用于制造具有相对较大尺寸的件的方法，特别是用于涡轮发动机的刀片，至少两个扇区（2）彼此分离地制造，使得它们中的每一个包括：部分（15），其具有基本相同的形状和尺寸要制成的件的相应部分，与另一部分（2）的相应联接表面互补的至少一个联接表面（14）和连续的外凸缘（16）每个所述联接表面（14）; 扇区（2）在耦合表面（14）处彼此搁置，然后通过在真空下进行的电子束焊接彼此紧固，以便沿着整个焊接外部凸缘（16）耦合表面（14）的外周边，以及随后的热等静压缩; 在紧固之后，通过材料去除加工来去除凸缘（16）。

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