公开(公告)号：US20240116625A1

公开(公告)日：2024-04-11

申请号：US18267128

申请日：2021-12-15

申请人： AMONYX APS

发明人： Allan MOLBECH

IPC分类号： B64C21/02 ,  B64C21/08

CPC分类号： B64C21/025 ,  B64C21/08

摘要： An airfoil having a leading-edge and a trailing edge as well as a suction side and a pressure side is provided. The suction side including an injector slot towards the leading edge. There may be at least one additional slot towards the trailing edge. The airfoil may be configured for an aircraft. A method of operating an aircraft using such airfoil is also provided.

公开(公告)号：US20230303264A1

公开(公告)日：2023-09-28

申请号：US17702755

申请日：2022-03-23

申请人： Rolls-Royce Corporation

发明人： Peter M. Schenk ,  Rigoberto Rodriguez ,  David Locascio

IPC分类号： B64D41/00 ,  B64D33/08 ,  B64C21/02 ,  F02K7/10

CPC分类号： B64D41/007 ,  B64D33/08 ,  B64C21/02 ,  F02K7/10 ,  F05D2220/34

摘要： The present disclosure is directed to an aircraft with an accessory system configured to be powered independent of the primary propulsion system by a ram air turbine power system. The ram air turbine power system illustratively includes an accessory generator integrated with a turbine rotor as well as other components so as to manage space claim and offer unique functionality.

公开(公告)号：US11679870B2

公开(公告)日：2023-06-20

申请号：US16958606

申请日：2018-12-13

申请人： AERO DESIGN LABS LLC

发明人： Eric A. Ahlstrom ,  Lee Sanders

IPC分类号： B64C23/06 ,  B64C7/00 ,  B64C21/02

CPC分类号： B64C23/06 ,  B64C7/00 ,  B64C21/02

摘要： A fairing assembly is provided about a duct outlet port, which is not parallel to an exterior surface of a vehicle, so as to turn fluid flow exiting the duct outlet port in a direction of surface fluid flow. The fairing assembly includes an upstream vane fairing to orient the surface flow with the angled duct flow, a downstream Coanda fairing to turn transverse duct flow in the direction of the surface flow, and a pair of vortex generators each of which is positioned at an opposing lateral side of the Coanda fairing and angled towards each other to organize the combined fluid flow downstream of the duct outlet port to thereby minimize recirculation. This fairing assembly about the duct outlet port enhances organized mixing of the duct and surface flows, and thereby reduces duct and surface recirculation, duct restriction, and overall vehicle drag.

公开(公告)号：US11634212B1

公开(公告)日：2023-04-25

申请号：US17492011

申请日：2021-10-01

申请人： Aurora Flight Sciences Corporation, a subsidiary of The Boeing Company

发明人： Francesco Giannini

IPC分类号： B64C21/08 ,  B64C29/00 ,  B64C21/02 ,  B64C9/00 ,  B64D35/04 ,  B64D29/02

摘要： An aircraft and a control system for the aircraft includes a tilt-wing defining an inlet configured to receive air and an outlet in fluid communication with the inlet such that the outlet is configured to expel the air. The control system includes a high-lift device coupled to at least one of a leading edge, and a trailing edge of the tilt-wing. The high-lift device is movable relative to the tilt-wing. The control system includes a compressor in fluid communication with the inlet and the outlet. The compressor is configured to increase pressure of the air that is expelled out of the outlet. The outlet directs the pressurized air toward at least one of the high-lift device and a center section of the tilt-wing to maintain attachment of airflow across the tilt-wing. A method of operating the control system of the aircraft occurs to maintain attachment of airflow across the tilt-wing.

公开(公告)号：US20230056996A1

公开(公告)日：2023-02-23

申请号：US17974741

申请日：2022-10-27

申请人： COFLOW JET, LLC

发明人： Gecheng Zha

IPC分类号： B64C3/14 ,  B64C21/02 ,  B64C3/10 ,  B64C3/36 ,  F15D1/00

摘要： Fluid systems are described herein. An example embodiment of a fluid system has a first body portion, a second body portion, a plurality of supports, a plurality of fluid pressurizers, and a plurality of ducts. The first body portion and the second body portion cooperatively define an injection opening, a suction opening, and a channel that extends from the injection opening to the suction opening. The fluid pressurizer is disposed within the channel cooperatively defined by the first body portion and the second body portion. Each duct of the plurality of ducts is disposed within the channel cooperatively defined by the first body portion and the second body portion.

公开(公告)号：US11524770B2

公开(公告)日：2022-12-13

申请号：US16147145

申请日：2018-09-28

申请人： Rohr, Inc.

发明人： Pablo T. Sanz Martinez ,  Johann Steven Schrell ,  Thomas Paolini

IPC分类号： B64C21/02 ,  B64C1/12 ,  B64C21/06 ,  B64D29/00 ,  B64C1/00 ,  B64D33/02

摘要： A panel for an active laminar flow control arrangement may comprise a longitudinal wall and one or more division walls extending from the longitudinal wall and extending between the first end and the second end. The panel may be coupled to a nacelle outer skin via a plurality of adhesive fasteners pre-installed onto an inner surface of the outer skin and onto stiffeners and/or stringers associated with the outer skin.

公开(公告)号：US20220363373A1

公开(公告)日：2022-11-17

申请号：US17633376

申请日：2020-08-06

申请人： Genesis Aerotech Limited

发明人： Martin LESLIE ,  Patrick MALLON ,  Michael Rice

IPC分类号： B64C27/18 ,  B64C21/02 ,  B64D27/24 ,  B64C23/02

摘要： A reaction-jet helicopter having an air compressor and a power source operable to power the compressor. The air compressor is in fluid communication with a cavity in a rotor blade of the reaction-jet helicopter. The rotor blade has one or more openings for the expulsion of compressed air from the cavity thereby resulting in rotation of the rotor blade. The reaction jet helicopter further has an arrangement for manipulating airflow between the compressor and the one or more openings. This results in reduced losses of energy as the airflow travels from the compressor to the one or more openings.

公开(公告)号：US20220363370A1

公开(公告)日：2022-11-17

申请号：US17741317

申请日：2022-05-10

申请人： The Boeing Company

发明人： Steve G. Mackin

IPC分类号： B64C21/02

摘要： Drag modification systems for aircraft and related methods. An example system for modifying drag on an aircraft includes a boundary layer intake plenum and an eductor. The eductor defines a primary inlet to receive a primary fluid, a secondary inlet in fluid communication with the intake plenum to receive a secondary fluid entrained from the intake plenum, and an outlet to exhaust a mixed flow including the primary fluid and the secondary fluid. The primary fluid is a motive fluid having flow parameters to generate a suction at the secondary inlet.

公开(公告)号：US20220348315A1

公开(公告)日：2022-11-03

申请号：US17850674

申请日：2022-06-27

申请人： Blended Wing Aircraft, Inc.

发明人： Mark Allan Page

IPC分类号： B64C21/02 ,  B64C39/10 ,  B64D29/04 ,  B64D33/02 ,  B64D33/04

摘要： Technologies are described herein for a drag recovery scheme using a boundary layer bypass duct system. In some examples, boundary layer air is routed around the intake of one or more of the engines and reintroduced aft of the engine fan in the nozzle duct in a mixer-ejector scheme. Mixer-ejectors mix the boundary layer flow to increase mass flow.

公开(公告)号：US20220194562A1

公开(公告)日：2022-06-23

申请号：US17506589

申请日：2021-10-20

申请人： The Boeing Company

发明人： Arvin Shmilovich ,  Abdollah Khodadoust ,  Christopher Colletti

IPC分类号： B64C21/02

摘要： Air acceleration at slot of aircraft wing. In one embodiment, a wing includes an air duct configured to transport air in a spanwise direction along a leading edge of the wing from an air supply source of the aircraft. The wing further includes a discharge duct configured to transport the air in an aft direction from the air duct to an aft end of the wing, and one or more nozzles disposed on the aft end of the wing and configured to accelerate air into a slot between the wing and a flap of the aircraft to increase lift and reduce drag for the wing.