公开(公告)号：US20210381389A1

公开(公告)日：2021-12-09

申请号：US17228778

申请日：2021-04-13

Applicant: GE Avio S.r.l.

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

IPC: F01D9/04 ,  F01D5/14

Abstract: 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：US20220178267A1

公开(公告)日：2022-06-09

申请号：US17471373

申请日：2021-09-10

Applicant: GE Avio S.r.l.

Inventor： Agostino Scialpi ,  Daniele Coutandin ,  Matteo Renato Usseglio ,  Giuseppe Greco

IPC: F01D11/24 ,  B33Y80/00 ,  F01D11/18 ,  F01D25/14

Abstract: A turbine clearance control system is provided. The turbine clearance control system includes a cooling air source and a turbine casing surrounding a portion of a turbine, wherein the turbine casing defines an integral cooling duct within the turbine casing, the integral cooling duct including apertures on an interior surface of the turbine casing.

公开(公告)号：US11566532B2

公开(公告)日：2023-01-31

申请号：US17471373

申请日：2021-09-10

Applicant: GE Avio S.r.l.

Inventor： Agostino Scialpi ,  Daniele Coutandin ,  Matteo Renato Usseglio ,  Giuseppe Greco

IPC: F01D11/24 ,  B33Y80/00 ,  F01D11/18 ,  F01D25/14

Abstract: A turbine clearance control system is provided. The turbine clearance control system includes a cooling air source and a turbine casing surrounding a portion of a turbine, wherein the turbine casing defines an integral cooling duct within the turbine casing, the integral cooling duct including apertures on an interior surface of the turbine casing.

公开(公告)号：US20210301665A1

公开(公告)日：2021-09-30

申请号：US17154153

申请日：2021-01-21

Applicant: GE Avio S.r.l.

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

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

Abstract: 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：US11905853B2

公开(公告)日：2024-02-20

申请号：US17228778

申请日：2021-04-13

Applicant: GE Avio S.r.l.

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

IPC: F01D9/04 ,  F01D5/14 ,  F01D11/00

CPC classification number: F01D9/041 ,  F01D5/14 ,  F01D5/141 ,  F01D11/001 ,  F01D11/006 ,  F05D2220/32 ,  F05D2240/12 ,  F05D2240/30

Abstract: 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：US11739643B2

公开(公告)日：2023-08-29

申请号：US17154153

申请日：2021-01-21

Applicant: GE Avio S.r.l.

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

IPC: F01D5/08 ,  F02C3/067 ,  F02C6/08 ,  F01D5/03

CPC classification number: F01D5/085 ,  F02C3/067 ,  F02C6/08 ,  F01D5/03 ,  F05D2260/232 ,  F05D2260/606

Abstract: 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：US20250146442A1

公开(公告)日：2025-05-08

申请号：US18802001

申请日：2024-08-13

Applicant: GE Avio S.r.l.

Inventor： Vincenzo Martina ,  Lucia Azzini ,  Daniele Coutandin

IPC: F02C7/18 ,  B64D27/33 ,  B64D33/08 ,  F02C7/22

Abstract: An aircraft system is provided. The aircraft system includes: a gas turbine engine; a fuel system having a fuel tank and a fuel delivery system fluidly connecting the fuel tank to the gas turbine engine; an electric drive assembly including a component module; and a thermal management system including: a thermal fluid loop; a heat source heat exchanger in thermal communication with the component module and the thermal fluid loop; an airflow heat sink heat exchanger in thermal communication with the thermal fluid loop and further configured to be in thermal communication with a cooling airflow during operation of the gas turbine engine; and a fuel heat sink heat exchanger in selective thermal communication with the thermal fluid loop, the fuel tank, or both, the fuel heat sink heat exchanger in fluid communication with the fuel tank independently of the fuel delivery system during at least a first operating condition.

公开(公告)号：US20210404348A1

公开(公告)日：2021-12-30

申请号：US17307262

申请日：2021-05-04

Applicant: GE Avio S.r.l.

Inventor： Alberto Buonvino ,  Luca Giacobone ,  Daniele Coutandin

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

Abstract: 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：US09790810B2

公开(公告)日：2017-10-17

申请号：US14407918

申请日：2013-06-14

Applicant: GE AVIO S.R.L

Inventor： Daniele Coutandin ,  Stefano Zecchi

IPC: F01D25/12 ,  F01D11/24 ,  F02C7/18 ,  F01D25/14

CPC classification number: F01D25/12 ,  F01D11/24 ,  F01D25/145 ,  F02C7/18 ,  F05D2220/32 ,  F05D2250/712 ,  F05D2260/201 ,  F05D2260/231 ,  Y02T50/672 ,  Y02T50/676

Abstract: In a gas turbine for aeronautic engines, a stator body delimited by an outer lateral surface is cooled by an air cooling device having a plurality of circumferential tubes for distributing air on the outer lateral surface; each circumferential tube having a plurality of outlets for guiding respective cooling airflows towards the outer lateral surface and into a respective circumferential channel obtained between two groups of circumferential channels adjacent to each other and lapped by the flow of air leaving the circumferential channel.

公开(公告)号：US09662603B2

公开(公告)日：2017-05-30

申请号：US14143837

申请日：2013-12-30

Applicant: GE AVIO S.r.l.

Inventor： Stefano Zecchi ,  Federico Dellavalle ,  Daniele Coutandin

IPC: B01D46/00 ,  B01D39/10 ,  B01D46/26

CPC classification number: B01D46/0056 ,  B01D39/10 ,  B01D46/26 ,  B01D2239/10

Abstract: A filtering net, in particular for a rotary separator, has a plurality of cells, which are substantially equal to one another and are defined by the replication of a base cell along two transversal directions of replication; the base cell comprises at least one intermediate filament and a first and a second end filament, arranged on opposite sides of the intermediate filament; the intermediate filament and the end filaments extend along respective longitudinal axes which are parallel; cross-sectioning the base cell with any plane orthogonal to the longitudinal axes of the filaments and joining, on said plane, the trace of each longitudinal axis with the trace of the adjacent longitudinal axis by a respective straight line, the two straight lines are incident at the trace of the longitudinal axis of the intermediate filament and form an incidence angle of between approximately 90° and 160°.