公开(公告)号：US10829206B2

公开(公告)日：2020-11-10

申请号：US15429829

申请日：2017-02-10

Applicant: General Electric Company

Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan ,  Davide Giacché

IPC: B64C21/10 ,  B64D27/12 ,  B64C3/10 ,  B64C3/16

Abstract: An apparatus configured to reduce acoustic interactions between a propeller and a surface of an aircraft positioned downstream of the propeller includes a surface modification element of the surface of the aircraft. The surface modification element defines a modified contour of the surface. The modified contour is configured to decorrelate a phase distribution of a plurality of sound sources within a source field positioned on at least a portion of the surface.

公开(公告)号：US20190234242A1

公开(公告)日：2019-08-01

申请号：US16377736

申请日：2019-04-08

Applicant: General Electric Company

Inventor： Kishore Ramakrishnan ,  Shourya Prakash Otta

IPC: F01D25/24 ,  B64D33/02 ,  B64D29/00 ,  B64D27/12 ,  B64C30/00

CPC classification number: F01D25/24 ,  B64C30/00 ,  B64D27/12 ,  B64D29/00 ,  B64D33/02 ,  B64D2033/0226 ,  B64D2033/026 ,  B64D2033/0286 ,  F05D2220/32 ,  F05D2240/14

Abstract: An engine for mounting in or to an aircraft includes a stage of compression airfoils rotatable about a central axis; a casing surrounding the stage of compression airfoils and defining an inlet; and a low-distortion inlet assembly mounted within the inlet. The inlet assembly includes one or more structural members mounted at predetermined locations around a circumference of the central axis within the inlet, the predetermined locations defining an airflow distortion exceeding a predetermined threshold; and at least one airflow modifying element configured within the inlet so as to reduce airflow distortion entering the stage of compression airfoils.

公开(公告)号：US20180057150A1

公开(公告)日：2018-03-01

申请号：US15244032

申请日：2016-08-23

Applicant: General Electric Company

Inventor： Lawrence Chih-hui Cheung ,  Nikolai N. Pastouchenko ,  Kishore Ramakrishnan

IPC: B64C21/08 ,  B64C21/06 ,  B64D29/04

CPC classification number: B64C21/08 ,  B64C1/16 ,  B64C21/06 ,  B64D27/24 ,  B64D29/04 ,  B64D33/02 ,  B64D33/04 ,  B64D2027/026 ,  B64D2033/0226 ,  Y02T50/166 ,  Y02T50/62

Abstract: An aircraft includes a fuselage extending between a forward end and an aft end. The aircraft additionally includes a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor including an outer nacelle and the outer nacelle defining an inlet. Additionally, the aircraft includes a deployable assembly attached to at least one of the fuselage or the outer nacelle, the deployable assembly movable between a stowed position and an engaged position. The deployable assembly alters an airflow towards the propulsor or into the propulsor through the inlet defined by the outer nacelle when in the engaged position to increase an efficiency of the aft fan and/or of the aircraft.

公开(公告)号：US20170152019A1

公开(公告)日：2017-06-01

申请号：US15092255

申请日：2016-04-06

Applicant: General Electric Company

Inventor： Trevor Howard Wood ,  Kishore Ramakrishnan

IPC: B64C11/18 ,  F04D29/66 ,  F04D29/38

CPC classification number: B64C11/18 ,  F04D29/324

Abstract: An airfoil includes a proximal end and a distal end opposite the proximal end. The airfoil also includes a distal portion extending adjacent the distal end and an edge extending between the proximal end and the distal end. The airfoil further includes a surface extending between the proximal end and the distal end. The edge and the surface define a sweep and a cahedral through the distal portion and at least a portion of the intermediate portion.