公开(公告)号：US20230322382A1

公开(公告)日：2023-10-12

申请号：US17658909

申请日：2022-04-12

Applicant: General Electric Company

Inventor： Mustafa Dindar ,  Timothy Richard DePuy

IPC: B64C39/10 ,  B64D33/02

CPC classification number: B64C39/10 ,  B64D33/02 ,  B64C2039/105 ,  B64D2033/0206

Abstract: A blended wing body aircraft includes a body section having an aerodynamic lifting surface. The body section includes an upper body and a lower body. The blended wing body aircraft also includes a plurality of blended wing sections further defining the body section. The blended wing body aircraft includes one or more grooves in the body section. The one or more grooves extend from the upper body towards the lower body. The blended wing body aircraft further includes one or more open-fan engines mounted at least partially within the one or more grooves. The one or more open-fan engines ingest a portion of a boundary layer of the blended wing body aircraft.

公开(公告)号：US20190210710A1

公开(公告)日：2019-07-11

申请号：US15864010

申请日：2018-01-08

Applicant: General Electric Company

Inventor： Mustafa Dindar

IPC: B64C7/02 ,  B64C21/10 ,  B64D27/18 ,  F02K3/06

CPC classification number: B64C7/02 ,  B64C21/10 ,  B64C2230/26 ,  B64D27/18 ,  F02K3/06 ,  F05D2220/323

Abstract: An engine nacelle is provided for an aircraft. The engine nacelle comprises: an inlet for receiving an air flow to generate a thrust force for the aircraft; a lip portion positioned at the inlet and surrounding the inlet; and at least one strake provided on a surface of the engine nacelle.

公开(公告)号：US11732673B2

公开(公告)日：2023-08-22

申请号：US17386065

申请日：2021-07-27

Applicant: General Electric Company

Inventor： Mustafa Dindar ,  Bernard James Renggli ,  Andrew J. Hank ,  Daniel Robert Dwyer ,  Jeffrey S. Spruill

IPC: F02K1/09 ,  F02K1/18 ,  F02K1/08 ,  B64D33/04

CPC classification number: F02K1/09 ,  B64D33/04 ,  F02K1/08 ,  F02K1/18 ,  F05D2220/323 ,  F05D2240/1281 ,  F05D2250/34

Abstract: A variable area exhaust nozzle defining an actual area ratio for a gas turbine engine that includes a shroud assembly having a fixed shroud and an adjustable cowl, an adjustable plug, a nozzle adjustment assembly, and a controller configured to receive data indicative of an operating speed of the gas turbine engine; determine a target area ratio based at least in part on received data indicative of the operating speed of the gas turbine engine; and operate the nozzle adjustment assembly to selectively adjust at least one of the adjustable cowl or the adjustable plug such that the actual area ratio is substantially equivalent to the target area ratio.

公开(公告)号：US10822100B2

公开(公告)日：2020-11-03

申请号：US15632846

申请日：2017-06-26

Applicant: General Electric Company

Inventor： Mustafa Dindar ,  Keith E J Blodgett

IPC: B64D27/24 ,  F02K5/00 ,  B64D27/02 ,  B64D27/20 ,  B64D27/10 ,  F01D15/10 ,  F01D17/10 ,  H02K7/18 ,  F02C3/04

Abstract: A propulsion system for an aircraft includes a propulsor; a turbomachine mechanically coupled to the propulsor for driving the propulsor during a combustion operating mode of the propulsion system and mechanically decoupled from the propulsor during an electric operating mode of the propulsion system; and an electrical power source. The propulsion system further includes an electric machine, the electric machine being electrically coupled to the electrical power source and mechanically coupled to the propulsor during the electric operating mode of the propulsion system such that the electric machine drives the propulsor during the electric operating mode of the propulsion system.

公开(公告)号：US20180100434A1

公开(公告)日：2018-04-12

申请号：US15291110

申请日：2016-10-12

Applicant: General Electric Company

Inventor： Mustafa Dindar ,  Joseph Donofrio ,  Richard David Cedar ,  David William Crall

IPC: F02C7/057 ,  B64D33/02 ,  F02K3/06 ,  F02C3/04

CPC classification number: F02C7/057 ,  B64D33/02 ,  B64D2033/0226 ,  F02C3/04 ,  F02C7/042 ,  F02K3/06 ,  F05D2220/323 ,  F05D2240/127 ,  F05D2260/57 ,  Y02T50/671

Abstract: The disclosure is towards an inlet cowl for a turbine engine including a surface defining an inlet with a flow path and a method towards controlling the airflow in the flow path. The inlet cowl further includes an inlet lip and inner and outer barrels. The inlet lip confronts the inner barrel at a junction defining a gap.

公开(公告)号：US11905884B1

公开(公告)日：2024-02-20

申请号：US17946708

申请日：2022-09-16

Applicant: General Electric Company

Inventor： Mustafa Dindar ,  Scott Alan Schimmels

IPC: F02C7/224 ,  F02C3/22 ,  F02K1/82 ,  F02C9/40

CPC classification number: F02C7/224 ,  F02C3/22 ,  F02C9/40 ,  F02K1/822 ,  F05D2260/213 ,  F05D2260/2214 ,  F05D2260/231 ,  F05D2260/232

Abstract: A gas turbine engine includes: a turbomachine including a combustion section and an exhaust assembly arranged in serial flow order; and a fuel system. The fuel system includes: a hydrogen fuel tank for holding a hydrogen fuel in a liquid phase; and a hydrogen delivery assembly in thermal communication with the exhaust assembly. The hydrogen delivery assembly includes: a liquid hydrogen line in fluid communication with the hydrogen fuel tank; a gaseous hydrogen line in fluid communication with the combustion section of the gas turbine engine; and a heat exchanger tubing positioned within the exhaust assembly downstream of the liquid hydrogen line and upstream of the gaseous hydrogen line.

公开(公告)号：US20180370641A1

公开(公告)日：2018-12-27

申请号：US15632846

申请日：2017-06-26

Applicant: General Electric Company

Inventor： Mustafa Dindar ,  Keith EJ Blodgett

IPC: B64D27/24 ,  B64D27/10 ,  F01D15/10 ,  F01D17/10 ,  H02K7/18

Abstract: A propulsion system for an aircraft includes a propulsor; a turbomachine mechanically coupled to the propulsor for driving the propulsor during a combustion operating mode of the propulsion system and mechanically decoupled from the propulsor during an electric operating mode of the propulsion system; and an electrical power source. The propulsion system further includes an electric machine, the electric machine being electrically coupled to the electrical power source and mechanically coupled to the propulsor during the electric operating mode of the propulsion system such that the electric machine drives the propulsor during the electric operating mode of the propulsion system.

公开(公告)号：US09995245B2

公开(公告)日：2018-06-12

申请号：US14396800

申请日：2013-04-26

Applicant: GENERAL ELECTRIC COMPANY

Inventor： Mustafa Dindar ,  Vaughn Ray Kunze

IPC: F02K1/38 ,  F02K1/46 ,  F02K1/34 ,  F02K1/48 ,  B64D33/04 ,  F02K1/82

CPC classification number: F02K1/386 ,  B64D33/06 ,  B64D2033/045 ,  F02K1/38 ,  F02K1/46 ,  F02K1/48 ,  F02K1/827 ,  F05D2230/20 ,  F05D2230/60 ,  F05D2250/184 ,  F05D2250/61 ,  F05D2250/611 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2260/96 ,  F05D2300/6033 ,  Y02T50/672 ,  Y10T29/49234

Abstract: A method of fabricating a mixer for a gas turbine engine is provided. The method includes forming a forward end and an aft end of the mixer, and forming an annularly undulating contour that defines a plurality of core immersion lobes and a plurality of bypass immersion lobes between the forward end and the aft end. The plurality of bypass immersion lobes includes a first bypass immersion lobe and a second bypass immersion lobe. The first bypass immersion lobe has a first crown contour line extending from the forward end to the aft end of the mixer, and the second bypass immersion lobe has a second crown contour line extending from the forward end to the aft end of the mixer. The first crown contour line is different than the second crown contour line.

公开(公告)号：US09810178B2

公开(公告)日：2017-11-07

申请号：US14818596

申请日：2015-08-05

Applicant: General Electric Company

Inventor： Mustafa Dindar ,  Scott Andrew Burton ,  Keith Edward James Blodgett ,  Richard David Cedar

IPC: F02K1/78 ,  F02K3/06 ,  F01D25/24 ,  F02K1/09 ,  F02K1/00 ,  F02K1/06 ,  F02K1/08

CPC classification number: F02K1/78 ,  F01D25/24 ,  F01D25/30 ,  F02K1/00 ,  F02K1/06 ,  F02K1/08 ,  F02K1/09 ,  F02K3/06 ,  F05D2250/14

Abstract: A turbofan exhaust nozzle includes: a conical inner shell disposed coaxially inside a surrounding outer shell to define an annular flow duct therebetween terminating in an outlet at a trailing edge of the outer shell and the inner shell terminates in a trailing edge aft of the outlet; and a pylon interrupting circumferentially the duct, wherein at least a portion of the trailing edge of the outer shell is vertically non-coplanar.

公开(公告)号：US20250116243A1

公开(公告)日：2025-04-10

申请号：US18982445

申请日：2024-12-16

Applicant: General Electric Company

Inventor： William Joseph Bowden ,  Keith Edward James Blodgett ,  Mustafa Dindar ,  David Cerra ,  James Hamilton Grooms ,  Brandon Wayne Miller ,  Randy M. Vondrell ,  David Marion Ostdiek ,  Craig Williams Higgins ,  Alexander Kimberely Simpson

IPC: F02K3/065 ,  F02C3/06

Abstract: A gas turbine engine includes a turbomachine having a compressor section, a combustion section, and a turbine section arranged in serial flow order. The turbomachine defines an engine inlet to an inlet duct, a fan duct inlet to a fan duct, and a core inlet to a core duct. The primary fan is driven by the turbomachine, and a secondary fan is located downstream of the primary fan within the inlet duct. One or more actuation devices operably associated with the fan duct, the one or more actuation devices actuable to increase or decrease an exit area of the fan duct.