公开(公告)号：US20250091721A1

公开(公告)日：2025-03-20

申请号：US18966208

申请日：2024-12-03

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Keith Edward James Blodgett ,  William J. Bowden ,  Egbert Geertsema

IPC: B64D27/14 ,  B64C1/26 ,  B64D27/40 ,  B64D29/06 ,  B64D35/02

Abstract: An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to: h L .

公开(公告)号：US20240317412A1

公开(公告)日：2024-09-26

申请号：US18734223

申请日：2024-06-05

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Keith Edward James Blodgett ,  William J. Bowden ,  Egbert Geertsema

IPC: B64D27/14 ,  B64C1/26 ,  B64D27/40 ,  B64D29/06 ,  B64D35/02

CPC classification number: B64D27/14 ,  B64C1/26 ,  B64D27/40 ,  B64D29/06 ,  B64D35/02

Abstract: An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to: h/L.

公开(公告)号：US12030652B2

公开(公告)日：2024-07-09

申请号：US17835280

申请日：2022-06-08

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Keith Edward James Blodgett ,  William J. Bowden ,  Egbert Geertsema

IPC: B64D27/14 ,  B64C1/26 ,  B64D27/40 ,  B64D29/06 ,  B64D35/02

CPC classification number: B64D27/14 ,  B64C1/26 ,  B64D27/40 ,  B64D29/06 ,  B64D35/02

Abstract: An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to:





h
L

.

公开(公告)号：US20230399114A1

公开(公告)日：2023-12-14

申请号：US17835280

申请日：2022-06-08

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Keith Edward James Blodgett ,  William J. Bowden ,  Egbert Geertsema

IPC: B64D27/14 ,  B64D29/06 ,  B64D27/26 ,  B64D35/02 ,  B64C1/26

CPC classification number: B64D27/14 ,  B64D29/06 ,  B64D27/26 ,  B64D35/02 ,  B64C1/26

Abstract: An aircraft comprising a fuselage and an unducted turbine engine. The fuselage having a divot with an upstream edge and a downstream edge. The divot is defined by a straight reference line having a length (L) and a maximum depth (h) relative to the straight reference line. The unducted turbine engine having an engine core, a nacelle, and a set of blades. A first flow ratio (FR1) is equal to: h/L.