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公开(公告)号：US12168506B2
公开(公告)日：2024-12-17
申请号：US18375540
申请日：2023-10-01
Applicant: JETZERO, INC.
Inventor： Mark Allan Page
Abstract: An apparatus for ingesting boundary layer flow on an aircraft, the apparatus includes a blended wing body, wherein the blended wing body is characterized by having no clear dividing line between wings and main body of the aircraft, wherein the blended wing body includes a nacelle located aft of a leading edge of the blended wing body, wherein the nacelle includes a propulsor configured to propel the aircraft, a primary duct, and a flow augmentation arrangement, wherein the flow augmentation arrangement is configured to accelerate a boundary layer flow in the airflow, wherein the flow augmentation arrangement further includes a secondary duct, wherein the secondary duct configured to ingest the boundary layer flow in the airflow from an inlet proximal to a forward portion of the nacelle to an outlet proximal to a rear portion of the nacelle and a tertiary duct between the primary duct and the secondary duct.
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公开(公告)号：US11827369B2
公开(公告)日：2023-11-28
申请号：US16914635
申请日：2020-06-29
Applicant: General Electric Company
Inventor： Randy M. Vondrell , Anthony Austin Bouvette , Glenn David Crabtree
IPC: B64D27/24 , B60L50/16 , B64C21/06 , B64D27/12 , B64D27/18 , F02C6/20 , F02K3/04 , H02G5/10 , H02K7/18 , B64D27/02
CPC classification number: B64D27/24 , B60L50/16 , B64C21/06 , B64D27/12 , B64D27/18 , F02C6/206 , F02K3/04 , H02G5/10 , H02K7/1823 , B60L2200/10 , B64C2230/04 , B64D2027/026 , B64D2221/00 , Y02T50/10 , Y02T50/40 , Y02T50/60
Abstract: A propulsion system for an aircraft can include an electric power source and an electric propulsion assembly having an electric motor and a propulsor. The propulsor can be powered by the electric motor. An electric power bus can electrically connect the electric power source to the electric propulsion assembly. The electric power source can be configured to provide electrical power to the electric power bus. An inverter converter controller can be positioned along the electric power bus and can be electrically connected to the electric power source at a location downstream of the electric power source and upstream of the electric propulsion assembly.
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公开(公告)号：US11808161B2
公开(公告)日：2023-11-07
申请号：US17717387
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Jixian Yao , Kishore Ramakrishnan , Trevor Howard Wood , Mustafa Dindar
CPC classification number: F01D25/24 , B64C21/02 , B64C21/06 , F05D2220/323 , F05D2240/14 , F05D2260/60
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; and a nacelle that circumferentially surrounds the fan, the nacelle comprising an annular wall having an exterior surface and an interior surface, the exterior surface comprising a first exterior portion, and the interior surface comprising a first interior portion, wherein a first exterior portion is formed of a first structure defining an exterior surface porosity, and wherein a first interior portion is formed of a second structure defining an interior surface porosity.
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公开(公告)号：US20230323791A1
公开(公告)日：2023-10-12
申请号：US17717387
申请日：2022-04-11
Applicant: General Electric Company
Inventor： Jixian Yao , Kishore Ramakrishnan , Trevor Howard Wood , Mustafa Dindar
CPC classification number: F01D25/24 , B64C21/06 , F05D2220/323 , F05D2240/14 , F05D2260/60
Abstract: A turbofan engine is provided. The turbofan engine includes a fan comprising a plurality of fan blades; and a nacelle that circumferentially surrounds the fan, the nacelle comprising an annular wall having an exterior surface and an interior surface, the exterior surface comprising a first exterior portion, and the interior surface comprising a first interior portion, wherein a first exterior portion is formed of a first structure defining an exterior surface porosity, and wherein a first interior portion is formed of a second structure defining an interior surface porosity.
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公开(公告)号：US11673651B2
公开(公告)日：2023-06-13
申请号：US17277130
申请日：2019-09-18
Applicant: AIRBUS OPERATIONS GmbH
Inventor： Alexander Büscher
Abstract: A leading edge structure for a flow control system of an aircraft is disclosed having a leading edge panel that surrounds a plenum, wherein the leading edge panel has a first side portion, a second side portion opposite the first side portion, an inner surface facing the plenum and an outer surface in contact with an ambient flow, and wherein the leading edge panel comprises a plurality of micro pores forming a fluid connection between the plenum and the ambient flow, wherein the plenum is connected to an air outlet arrangement configured for causing an underpressure in the plenum, so that air from the ambient flow is drawn through the micro pores into the plenum and from there discharged through the air outlet arrangement into the ambient flow.
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公开(公告)号：US20230166832A1
公开(公告)日：2023-06-01
申请号：US17538849
申请日：2021-11-30
Applicant: The Boeing Company
Inventor： Sho Sato
IPC: B64C21/06
CPC classification number: B64C21/06
Abstract: An aircraft is equipped with multiple fans for boundary layer ingestion. The aircraft comprises a fuselage, having an exterior surface and a rearward-most end. The aircraft also comprises a plurality of fans that are fixed to and positioned about the exterior surface of the fuselage at an axial location forward of the rearward-most end of the fuselage. Each one of the plurality of fans comprises a plurality of fan blades and a fan drive configured to rotate the plurality of fan blades. The plurality of fan blades are positioned at lateral locations relative to the exterior surface of the fuselage such that when rotated by the fan drive the plurality of fans receive and accelerate fuselage boundary layer air flow, along the exterior surface of the fuselage, from a first average velocity to a second average velocity, greater than the first average velocity, when the aircraft is in flight.
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公开(公告)号：US20230075112A1
公开(公告)日：2023-03-09
申请号：US17854499
申请日：2022-06-30
Inventor： Gecheng Zha , Siena Whiteside , Beau Pollard , Michael Patterson , Xiaofan Fei , Paul Rothhaar , Kevin Antcliff , Steven Geuther
Abstract: An example of a deflected slip stream wing system with coflow jet flow control includes a wingbox, a flap, a compressor, and a propulsor. The wingbox has a root and a tip. The flap is moveably attached to the wingbox and has a leading edge, a trailing edge, an injection opening, a suction opening, and a channel. The injection opening is disposed between the leading edge and the suction opening. The suction opening is disposed between the injection opening and the trailing edge. The channel extends from the injection opening to the suction opening. The compressor is disposed within the channel. The propulsor is disposed on the wingbox between the root and the tip. The propulsor has an off state and an on state. When in the on state, the propulsor is aligned relative to the flap such that fluid accelerated by the propulsor contacts the flap.
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8.发明授权
公开(公告)号：US11584514B2
公开(公告)日：2023-02-21
申请号：US16966353
申请日：2019-01-23
Applicant: AIRBUS OPERATIONS GMBH
Inventor： Thomas Heuer , Volker Piezunka
Abstract: An airfoil for flow control is disclosed having an outer skin in contact with an ambient air flow, wherein the outer skin extends between a leading edge and a trailing edge with two opposite lateral sides, and surrounds an interior space. The outer skin comprises a porous section in the area of the leading edge, a pressure chamber arranged in the interior space and fluidly connected to the porous section, an air inlet fluidly connected to the pressure chamber, and an air outlet fluidly connected to the pressure chamber.
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公开(公告)号：US11525388B2
公开(公告)日：2022-12-13
申请号：US16210465
申请日：2018-12-05
Applicant: PRATT & WHITNEY CANADA CORP.
Inventor： Jean Thomassin , David Meisels , Richard Ullyott
IPC: F01P11/10 , B64C9/38 , B64D33/10 , B64C21/04 , B64C21/06 , B64D27/10 , F01P3/20 , F01P5/10 , B64C21/08
Abstract: A method of providing active flow control for an aircraft includes cooling a liquid coolant in a heat exchanger by circulating a cooling airflow through the heat exchanger, and providing fluid communication between the cooling airflow and a boundary layer flow of at least one flight control surface of the aircraft. The cooling airflow affects the boundary layer flow of the flight control surface(s) to provide active flow control. A method of cooling an engine core of an engine assembly includes circulating a cooling fluid through the engine core, and cooling the cooling fluid with a cooling airflow used to provide active flow control to a flight control surface of the aircraft. An active flow control system for an aircraft is also discussed.
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公开(公告)号：US11485481B2
公开(公告)日：2022-11-01
申请号：US16279244
申请日：2019-02-19
Applicant: General Electric Company
Abstract: An aircraft includes a fuselage extending between a forward end and an aft end; a propulsor mounted to the fuselage at the aft end of the fuselage, the propulsor comprising an outer nacelle, the outer nacelle defining an inlet to the propulsor; and a deployable assembly attached to at least one of the fuselage or the outer nacelle and moveable 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. The propulsor further comprises a tail cone, wherein the outer nacelle defines an exhaust with the tail cone, and wherein the plurality of nacelle panels are movable generally along the axial centerline to a position at least partially aft of the exhaust of the outer nacelle when in the engaged position.
