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：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.