公开(公告)号：US10370110B2

公开(公告)日：2019-08-06

申请号：US15271776

申请日：2016-09-21

Applicant: General Electric Company

Inventor： Kishore Ramakrishnan ,  Jixian Yao ,  Nikolai N. Pastouchenko ,  Ivan Malcevic

IPC: B64D27/14 ,  B64C5/06 ,  B64C21/00 ,  B64C1/16 ,  B64D27/20 ,  B64C21/08 ,  B64C1/00

Abstract: An aircraft is provided including a fuselage that extends along a longitudinal direction between a forward end and an aft end. A boundary layer ingestion fan is mounted to the fuselage at the aft end and is configured for ingesting boundary layer airflow off the surface of the fuselage. The fuselage defines a profile proximate the boundary layer ingestion fan that is optimized for ingesting a maximum amount of boundary layer air and improving propulsive efficiency of the aircraft. More specifically, the fuselage defines a cross sectional profile upstream of the boundary layer ingestion fan that has more cross sectional area in a top half relative to a bottom half as defined relative to a centerline of the boundary layer ingestion fan.

公开(公告)号：US10220952B2

公开(公告)日：2019-03-05

申请号：US15245286

申请日：2016-08-24

Applicant: General Electric Company

Inventor： Jixian Yao ,  Nikolai N. Pastouchenko ,  Ivan Malcevic

IPC: B64D29/04 ,  B64C21/06 ,  B64D27/20 ,  B64D27/24

Abstract: An aircraft is provided including a fuselage extending between a forward end and an aft end. An aft engine is mounted to the aft end of the fuselage and defines a centerline. The aft engine further includes a nacelle having a forward transition duct at the forward end of the nacelle. The forward transition duct also defines a centerline and the centerline of the forward transition duct is angled downward relative to the centerline of the aft engine.

公开(公告)号：US10047620B2

公开(公告)日：2018-08-14

申请号：US14572119

申请日：2014-12-16

Applicant: General Electric Company

Inventor： Davide Giacché ,  John David Stampfli ,  Ramakrishna Venkata Mallina ,  Vittorio Michelassi ,  Giridhar Jothiprasad ,  Ajay Keshava Rao ,  Rudolf Konrad Selmeier ,  Sungho Yoon ,  Ivan Malcevic

IPC: F01D11/00 ,  F04D29/52 ,  F04D29/68 ,  F04D27/02

Abstract: A compressor for a gas turbine engine including one or more endwall treatments for controlling leakage flow and circumferential flow non-uniformities in the compressor. The compressor includes a casing, a hub, a flow path formed between the casing and the hub, a plurality of blades positioned in the flow path, and one or more circumferentially varying end-wall treatments formed in an interior surface of at least one of the casing or the hub. Each of the one or more circumferentially varying endwall treatments circumferentially varying based on their relative position to an immediately adjacent upstream bladerow. Each of the one or more endwall treatments is circumferentially varied in at least one of placement relative to the immediately adjacent upstream bladerow or in geometric parameters defining each of the plurality of circumferentially varying endwall treatments. Additionally disclosed is an engine including the compressor.

公开(公告)号：US20180086437A1

公开(公告)日：2018-03-29

申请号：US15275610

申请日：2016-09-26

Applicant: General Electric Company

Inventor： Nikolai N. Pastouchenko ,  Ivan Malcevic

IPC: B64C21/04 ,  B64C21/06 ,  B64D27/18 ,  F02C9/18

CPC classification number: B64C21/04 ,  B64C21/06 ,  B64C2230/04 ,  B64D27/20 ,  Y02T50/166

Abstract: An air injection assembly for an aircraft is provided. The aircraft includes a fuselage extending between a forward end and an aft end along a longitudinal direction and a boundary layer ingestion fan mounted to the fuselage at the aft end of the fuselage. The air injection assembly includes a plurality of injection ports defined on a surface of the fuselage at a location upstream of the boundary layer ingestion fan. A supplemental airflow is provided through a fluid passageway to the injection ports where it is ejected to displace at least a portion of relatively higher velocity boundary layer airflow. In this manner, the airflow entering boundary layer ingestion fan is more uniform, has less swirl distortion, and has a lower average velocity.

公开(公告)号：US20180086436A1

公开(公告)日：2018-03-29

申请号：US15275901

申请日：2016-09-26

Applicant: General Electric Company

Inventor： Nikolai N. Pastouchenko ,  Ivan Malcevic

IPC: B64C21/02 ,  B64C5/02

CPC classification number: B64C21/025 ,  B64C1/16 ,  B64C1/26 ,  B64C5/02 ,  B64C21/06 ,  B64C2230/04 ,  B64D27/20 ,  Y02T50/166

Abstract: An aircraft is provided including a fuselage that extends along a longitudinal direction between a forward end and an aft end. A stabilizer assembly and a boundary layer ingestion fan is mounted to the fuselage at the aft end and is configured for ingesting boundary layer airflow off the surface of the fuselage. The stabilizer assembly includes a stabilizer and a root fillet extending between the stabilizer and the fuselage. The root fillet defines a flow directing surface configured for urging a flow of boundary layer air upward along the vertical direction. In addition, an airflow modifying element may protrude from a surface of the fuselage or the root fillet, the airflow modifying element being configured for directing or reducing swirl in the flow of boundary layer air.