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.

公开(公告)号：US11840987B2

公开(公告)日：2023-12-12

申请号：US17713597

申请日：2022-04-05

Applicant: General Electric Company

Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan ,  Justin John Gambone, Jr. ,  Darren Lee Hallman ,  Thomas Malkus ,  Jixian Yao ,  Keith Edward James Blodgett

IPC: F02K1/72 ,  F02K1/76

CPC classification number: F02K1/72 ,  F02K1/766 ,  F05D2220/323 ,  F05D2240/129 ,  F05D2240/14 ,  F05D2260/606

Abstract: A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.

公开(公告)号：US20230313754A1

公开(公告)日：2023-10-05

申请号：US17713597

申请日：2022-04-05

Applicant: General Electric Company

Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan ,  Justin John Gambone, JR. ,  Darren Lee Hallman ,  Thomas Malkus ,  Jixian Yao ,  Keith Edward James Blodgett

IPC: F02K1/72 ,  F02K1/76

CPC classification number: F02K1/72 ,  F02K1/766 ,  F05D2220/323 ,  F05D2240/14 ,  F05D2260/606 ,  F05D2240/129

Abstract: A cascade thrust reverser assembly for a gas turbine engine includes a nacelle assembly defining a bypass passage. The cascade thrust reverser assembly includes a cascade assembly configured to be at least partially enclosed by the nacelle assembly, the cascade assembly comprising one or more cascade members, the one or more cascade members movable between a stowed configuration wherein the one or more cascade members define a first radial extent and a deployed configuration wherein the one or more cascade members define a second radial extent, wherein the one or more cascade members form a cascade segment in the deployed configuration, and wherein the second radial extent is greater than the first radial extent.