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：US11821334B2

公开(公告)日：2023-11-21

申请号：US17388143

申请日：2021-07-29

Applicant: GE Avio S.r.l.

Inventor： Massimiliano Airaudo ,  Paolo Calza ,  Francesco Bertini ,  Matteo Renato Usseglio ,  Cristian Lizzer ,  Ernesto Sozio ,  Matteo Furfaro ,  Marco Thiene

IPC: F01D5/14 ,  F01D5/18

CPC classification number: F01D5/187 ,  F01D5/143 ,  F05D2240/307 ,  F05D2250/185 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: A turbine blade including an airfoil portion extending between a leading edge and a trailing edge, a base portion positioned below the airfoil portion, the base portion including an outwardly-extending wing positioned below the airfoil portion, and an aero-brake feature positioned between the outwardly-extending wing and the airfoil portion and extending outward from the base portion, where the aero-brake feature is structurally configured to disrupt axial airflow across the turbine blade.

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：US20220098987A1

公开(公告)日：2022-03-31

申请号：US17388143

申请日：2021-07-29

Applicant: GE Avio S.r.l.

Inventor： Massimiliano Airaudo ,  Paolo Calza ,  Francesco Bertini ,  Matteo Renato Usseglio ,  Cristian Lizzer ,  Ernesto Sozio ,  Matteo Furfaro ,  Marco Thiene

IPC: F01D5/18 ,  F01D5/14

Abstract: A turbine blade including an airfoil portion extending between a leading edge and a trailing edge, a base portion positioned below the airfoil portion, the base portion including an outwardly-extending wing positioned below the airfoil portion, and an aero-brake feature positioned between the outwardly-extending wing and the airfoil portion and extending outward from the base portion, where the aero-brake feature is structurally configured to disrupt axial airflow across the turbine blade.