公开(公告)号：US20210404348A1

公开(公告)日：2021-12-30

申请号：US17307262

申请日：2021-05-04

申请人： GE Avio S.r.l.

发明人： Alberto Buonvino ,  Luca Giacobone ,  Daniele Coutandin

IPC分类号： F01D25/12 ,  F01D11/24 ,  F01D11/02

摘要： Aspects of the disclosure generally relate to a turbine engine and method of operating, wherein a change in sealing status can be determined within a cavity between an outer casing and a rotor within the turbine engine. Aspects of the disclosure further relate to a supply of air to the cavity within the turbine engine.

公开(公告)号：US20210381389A1

公开(公告)日：2021-12-09

申请号：US17228778

申请日：2021-04-13

申请人： GE Avio S.r.l.

发明人： Alberto Buonvino ,  Luca Giacobone ,  Daniele Coutandin ,  Ernesto Sozio ,  Francesco Bertini

IPC分类号： F01D9/04 ,  F01D5/14

摘要： An airfoil assembly defining a primary airflow path for a turbine engine comprising a platform, an airfoil extending from the platform and into at least a portion of the primary airflow path, a secondary airflow path comprising air from the primary airflow path, and a deflector provided within the secondary airflow path.

公开(公告)号：US11473439B1

公开(公告)日：2022-10-18

申请号：US17448621

申请日：2021-09-23

申请人： General Electric Company ,  GE Avio S.r.l.

发明人： Luca Giacobone ,  Matteo Renato Usseglio ,  Andrea Depalma ,  Roberto Maddaleno ,  Darek Tomasz Zatorski

IPC分类号： F01D9/06 ,  F01D11/10 ,  F16J15/00 ,  F01D11/00 ,  F01D11/02

摘要： A gas turbine engine defining a longitudinal direction and a radial direction is provided. The gas turbine engine includes a turbine section comprising a stationary outer portion, a first rotating component, and a second rotating component, wherein the first rotating component includes an aft airfoil defining a hollow passageway and coupled to a radially extended first rotor portion, wherein the hollow passageway is in fluid communication with the stationary outer portion, wherein the second rotating component is coupled to a radially extended second rotor portion; and a seal assembly between a portion of the first rotating component and the second rotating component, the seal assembly defining a balance piston cavity therebetween, wherein the balance piston cavity is in fluid communication with the hollow passageway, wherein a flow of air is routed through the stationary outer portion and the hollow passageway to the balance piston cavity, and wherein a pressure of the flow of air within the balance piston cavity is controlled to provide an axial thrust that counteracts a thrust load on the second rotor portion.

公开(公告)号：US20210301665A1

公开(公告)日：2021-09-30

申请号：US17154153

申请日：2021-01-21

申请人： GE Avio S.r.l.

发明人： Alberto Buonvino ,  Daniele Coutandin ,  Luca Giacobone ,  Riccardo Da Soghe ,  Cosimo Bianchini

IPC分类号： F01D5/08 ,  F02C3/067 ,  F02C6/08

摘要： A turbine engine having counter-rotating rotors comprising a first rotor, rotating in a first rotational direction, defining a first rotor set of blades axially spaced to define a gap, and a second rotor, rotating in a second rotational direction counter the first rotational direction. The second rotor further including a second set of blades received within the gap of the first rotor. A plurality of fluid passages is formed in the first rotor with an outlet facing the gap.

公开(公告)号：US20210032999A1

公开(公告)日：2021-02-04

申请号：US16935458

申请日：2020-07-22

申请人： GE Avio S.r.l.

发明人： Antonio Giusseppe D'Ettole ,  Andrea Depalma ,  Roberto Maddaleno ,  Luca Giacobone ,  Matteo Renato Usseglio

IPC分类号： F01D11/12 ,  F01D5/20

摘要： A turbine engine with an outer rotor that circumscribes an inner rotor or inner stator. The outer rotor includes circumferentially arranged components with a tip and a root. The root of each of the circumferentially arranged components can terminate at an inner platform, where the collection of inner platforms can define an inner band.