公开(公告)号：US20190383331A1

公开(公告)日：2019-12-19

申请号：US16482065

申请日：2018-01-26

Applicant: GE Avio S.r.l.

Inventor： Marco Garabello ,  Paolo Altamura ,  Gian Mario Bragallini ,  Alessio Gargioli ,  Jan Biskupski

IPC: F16D3/74 ,  F02C7/36 ,  F16D7/00 ,  F16D3/12

Abstract: The present disclosure is directed to a shaft assembly (95) for a turbine engine (10), wherein the turbine engine includes a fan or propeller assembly (14) and an engine core (20), and further wherein the fan or propeller assembly includes a gearbox (45), and wherein the engine core includes one or more rotors (32). The shaft assembly (95) includes a flexible shaft (100) defining a first end (101) and a second end (102) along the axial direction, wherein the first end is connected to the engine core (20) and the second end is connected to the gearbox (45), and wherein a plurality of splines (110) is defined at the second end (102) and coupled to a spline interface (46) at the gearbox (45); and a coupling (120) extended at least partially in the radial direction and coupled to the engine core and the flexible shaft.

公开(公告)号：US12065936B2

公开(公告)日：2024-08-20

申请号：US17409943

申请日：2021-08-24

Applicant: GE Avio S.r.l.

Inventor： Cristian Lizzer ,  Maciej Slawinski ,  Wojciech Lukasz Staszynski ,  Jan Biskupski

IPC: F01D17/02 ,  F01D9/04

CPC classification number: F01D17/02 ,  F01D9/041 ,  F05D2220/323 ,  F05D2240/12 ,  F05D2260/80

Abstract: An inter-turbine duct is positioned between a high pressure turbine and a low pressure turbine of a gas turbine engine. The inter-turbine duct includes an inner annular wall and an outer annular wall spaced apart from the inner annular wall along a radial direction to define an annular flow passage. The inter-turbine duct includes a plurality of circumferentially spaced vanes positioned within the flow passage and at least one temperature probe is positioned upstream of the vanes at a circumferential location that is between thirty and seventy percent of a circumferential distance between the leading edges of adjacent vanes.

公开(公告)号：US11591969B2

公开(公告)日：2023-02-28

申请号：US16482086

申请日：2018-01-24

Applicant: GE Avio S.r.l.

Inventor： Marco Garabello ,  Paolo Altamura ,  Gian Mario Bragallini ,  Alessio Gargioli ,  Jan Biskupski

IPC: F02C7/36 ,  F16C1/02 ,  F16D3/06 ,  F02C9/00 ,  F16H1/28 ,  F16H57/00

Abstract: 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.

公开(公告)号：US20220090513A1

公开(公告)日：2022-03-24

申请号：US17409943

申请日：2021-08-24

Applicant: GE Avio S.r.l.

Inventor： Cristian Lizzer ,  Maciej Slawinski ,  Wojciech Lukasz Staszynski ,  Jan Biskupski

IPC: F01D17/02 ,  F01D9/04

Abstract: An inter-turbine duct is positioned between a high pressure turbine and a low pressure turbine of a gas turbine engine. The inter-turbine duct includes an inner annular wall and an outer annular wall spaced apart from the inner annular wall along a radial direction to define an annular flow passage. The inter-turbine duct includes a plurality of circumferentially spaced vanes positioned within the flow passage and at least one temperature probe is positioned upstream of the vanes at a circumferential location that is between thirty and seventy percent of a circumferential distance between the leading edges of adjacent vanes.

公开(公告)号：US20200248630A1

公开(公告)日：2020-08-06

申请号：US16482086

申请日：2018-01-24

Applicant: GE Avio S.r.l.

Inventor： Marco Garabello ,  Paolo Altamura ,  Gian Mario Bragallini ,  Alessio Gargioli ,  Jan Biskupski

IPC: F02C7/36 ,  F16H57/00 ,  F16H1/28 ,  F02C9/00 ,  F16C1/02 ,  F16D3/06

Abstract: 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.