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公开(公告)号：US11976612B2
公开(公告)日：2024-05-07
申请号：US16209466
申请日：2018-12-04
Applicant: Judith Marie Bovankovich
Inventor： Mark Bovankovich
CPC classification number: F02K7/10 , B64D39/00 , B64G1/002 , B64G1/005 , F02C7/22 , F02K1/09 , F02K7/16 , F02K7/18 , F05D2220/80 , Y02T50/60
Abstract: A method of propulsion includes providing a high-speed-launch ramjet boost (HSLRB) stage and HSLRB engine attached to a launch aircraft providing a speed ≥1.5 Mach. The HSLRB engine includes a combustion system and inlet(s) for air flow to the fuel injectors. A variable geometry (VG) nozzle having a nozzle actuator exhausts gas from combustion. A processor receives sensing signals from sensor(s) during flight that provides control signals to the nozzle actuator for dynamically controlling an aperture size of the VG nozzle, and if the inlet is a VG inlet to an inlet actuator to dynamically control the VG inlet shape. The HSLRB engine is ignited while attached to the aircraft at 1.5 to 1.99 Mach if assisting the aircraft to accelerate to 2.0 Mach, or at a speed of ≥2.0 Mach if the aircraft can accelerate to 2.0 Mach autonomously, then the HSLRB stage is separated from the aircraft.
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公开(公告)号：US11927150B2
公开(公告)日：2024-03-12
申请号：US17874825
申请日：2022-07-27
Applicant: ROHR, INC.
Inventor： Timothy Gormley
CPC classification number: F02K1/763 , F02C7/32 , F02K1/09 , F02K1/15 , F02K1/72 , F02K1/766 , F02K3/04 , F05D2260/4031 , F05D2260/53
Abstract: A nacelle may comprise a fixed structure and a translating structure configured to translate relative to the fixed structure. A first drive system may be operationally coupled to the translating structure. The drive system may comprise a primary actuator coupled to the fixed structure and including a primary rod and a primary gear rotationally coupled to the primary rod, a torque shaft rotationally coupled to the primary gear, and a secondary actuator operationally coupled to the primary actuator via the torque shaft.
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公开(公告)号：US11286878B2
公开(公告)日：2022-03-29
申请号：US16836065
申请日：2020-03-31
Inventor： Todd S. Taylor , David L. Sutterfield , Jack D. Petty , Andrew Sanderson , Bryan H. Lerg
Abstract: A propulsion unit includes a gas turbine engine arranged along an axis and an exhaust system coupled to the gas turbine engine. The gas turbine engine includes an engine core configured to discharge a core flow and a fan configured to be driven by the engine core to discharge a bypass flow. The exhaust system receives the mixed bypass and core flows from the gas turbine engine.
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公开(公告)号：US11220978B2
公开(公告)日：2022-01-11
申请号：US16699890
申请日：2019-12-02
Applicant: Airbus Operations SAS
Inventor： Pascal Gardes , José Goncalves , Bastian Sabathier
Abstract: A turbofan having a nacelle comprising a slider mobile in translation between an advanced and a retracted position to open a window between a duct and the exterior, a plurality of blades, each one mobile in rotation on the slider between a stowed and a deployed position, where the blades are split into groups, where each group comprises a first blade, and a maneuvering system moving each blade and comprising a cam integral with the first blade of one of the groups and having a tooth, a groove receiving the tooth, a first transmission system transmitting the movement of the first blade bearing the cam to a first blade of each other group, and, for each group, a second transmission system transmitting the movement of the blade that bears the cam or is moved by the first transmission system to each of the other blades of the group.
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公开(公告)号：US20210404416A1
公开(公告)日：2021-12-30
申请号：US17167241
申请日：2021-02-04
Applicant: SPIRIT AEROSYSTEMS, INC.
Inventor： Henry Arnold Schaefer
Abstract: A ducted fan housing for directing a duct flow includes an annular cowling and an adjustable fan duct nozzle. The nozzle includes a flexible sleeve having rigid areas arranged circumferentially around the nozzle orifice and connected by flexible areas so as to form a unitary sleeve structure. The rigid areas are radially moveable between a normal configuration in which the orifice is smaller and a dilated configuration in which the orifice is larger. A drive mechanism uses drive elements to move at least some of the rigid areas between the configurations to adjust the size of the orifice. The rigid areas may be constructed from laminated graphite and epoxy, and the flexible areas may be constructed from laminated graphite and soft resin. If the housing includes a thrust reverser, then a flexible joint area extends circumferentially around the housing and connects the flexible sleeve to a thrust reverser cowl.
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Patent Agency Ranking
公开(公告)号：US11187186B2
公开(公告)日：2021-11-30
申请号：US16719049
申请日：2019-12-18
Applicant: Rolls-Royce Deutschland Ltd & Co KG
Inventor： Predrag Todorovic , Thomas Schillinger
Abstract: An exhaust nozzle of a gas turbine engine which includes an outer nozzle wall, a flow channel which is limited radially outwards by the nozzle wall, a centerbody arranged in the flow channel, and exactly one strut connecting the centerbody to the nozzle wall. The strut is connected to the nozzle wall by means of a connecting structure that is displaceable in the axial direction of the outer nozzle wall. At least one actuator is provided interacting with the connecting structure or the outer nozzle wall for displacing the strut in the axial direction.
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公开(公告)号：US11085400B2
公开(公告)日：2021-08-10
申请号：US16254889
申请日：2019-01-23
Applicant: RAYTHEON TECHNOLOGIES CORPORATION
Inventor： Christopher A. Eckett , Gabriel L. Suciu
IPC: F02K3/075 , F02K1/72 , F02K3/06 , F02K1/76 , F02K1/09 , B64D27/26 , B64D29/06 , B64D33/04 , F01D25/24 , F02C3/04 , F02K1/70
Abstract: An integrated propulsion system according to an example of the present disclosure includes, among other things, components that include a gas turbine engine, a nacelle assembly and a mounting assembly, the system designed by a process comprising identifying two or more of internal structural loading requirements, external structural mount loading requirements, aerodynamic requirements, and acoustic requirements for the system, and interdependently designing said components to meet said requirements. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.
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公开(公告)号：US20200025147A1
公开(公告)日：2020-01-23
申请号：US16254889
申请日：2019-01-23
Applicant: United Technologies Corporation
Inventor： Christopher A. Eckett , Gabriel L. Suciu
IPC: F02K3/075 , F02K1/72 , F02K3/06 , B64D27/26 , B64D29/06 , B64D33/04 , F01D25/24 , F02C3/04 , F02K1/76 , F02K1/09
Abstract: An integrated propulsion system according to an example of the present disclosure includes, among other things, components that include a gas turbine engine, a nacelle assembly and a mounting assembly, the system designed by a process comprising identifying two or more of internal structural loading requirements, external structural mount loading requirements, aerodynamic requirements, and acoustic requirements for the system, and interdependently designing said components to meet said requirements. The nacelle assembly includes a fan nacelle and an aft nacelle, the fan nacelle arranged at least partially about a fan and the engine, and the fan nacelle arranged at least partially about a core cowling to define a bypass flow path.
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公开(公告)号：US20200025035A1
公开(公告)日：2020-01-23
申请号：US16378847
申请日：2019-04-09
Applicant: ROLLS-ROYCE plc
Inventor： Richard PEACE , Lucian INGLEY
Abstract: A gas turbine engine for an aircraft is provided. The gas turbine engine comprises an engine core comprising a compressor, a combustor, a turbine, and a core shaft connecting the turbine to the compressor. The gas turbine engine further comprises a fan located upstream of the engine core, the fan comprising a plurality of fan blades, the fan generating a core airflow which enters the engine core and a bypass airflow which flows through a bypass duct surrounding the engine core. The gas turbine engine further comprises a circumferential row of outer guide vanes located in the bypass duct rearwards of the fan, the outer guide vanes extending radially outwardly from an inner ring which defines a radially inner surface of the bypass duct.
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公开(公告)号：US10378479B2
公开(公告)日：2019-08-13
申请号：US14886466
申请日：2015-10-19
Applicant: General Electric Company
Inventor： Matthew Timothy Franer , Brandon Wayne Miller
Abstract: A turbofan engine is provided having a fan and a core in flow communication with the fan. The turbofan engine also includes a nacelle assembly enclosing the fan and at least a portion of the core to define a bypass passage with the core. The nacelle assembly includes a fan cowl extending around the fan and a thrust reverser system. The thrust reverser system is movable between a fully stowed position, a partially deployed position, and a fully deployed position. The thrust reverser system is configured to be held in the partially deployed position to allow an additional amount of airflow to exit from the bypass passage.
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