公开(公告)号：US20240318615A1

公开(公告)日：2024-09-26

申请号：US18609726

申请日：2024-03-19

Applicant: AGENCY FOR DEFENSE DEVELOPMENT

Inventor： Juhyun Bae ,  Sangwook Jin ,  Haeseung Jeong ,  Minchan Kwon ,  Seokjin Oh

IPC: F23R3/28 ,  F02K7/10

CPC classification number: F23R3/283 ,  F02K7/10 ,  F23R3/286

Abstract: Disclosed is a dual-mode ramjet engine including: a combustor through which air flowing in from the front passes; a sliding injector configured to perform a sliding operation from an upper surface of the combustor along a height direction perpendicular to an air flow direction; and a cavity-type flame holder formed behind the sliding injector on the upper surface of the combustor and having a cavity that is concavely recessed, wherein the sliding injector includes: a plurality of fuel injection holes formed on both sides and configured to inject fuel; a fuel injection passage passing through the inside along the height direction to be opened downward, and configured to inject fuel; and a first sliding drive unit configured to drive the sliding injector to perform the sliding operation.

公开(公告)号：US20240229744A1

公开(公告)日：2024-07-11

申请号：US18403448

申请日：2024-01-03

Applicant: Ajay P. Kothari

Inventor： Ajay P. Kothari

IPC: F02K7/10 ,  B64C30/00 ,  B64D27/22 ,  F02K9/42 ,  G21C3/54 ,  G21D5/02

CPC classification number: F02K7/10 ,  B64D27/22 ,  F02K9/42 ,  G21D5/02 ,  B64C30/00 ,  G21C3/54

Abstract: Methods and systems for propelling an air vehicle with a molten salt reactor, a first heat exchanger, and a second heat exchanger are disclosed. A hot liquid molten salt from the molten salt reactor heats a fluid in the first heat exchanger to produce a hot fluid. The hot fluid heats air in the second heat exchanger to produce heated air which passes through a nozzle to propel the air vehicle.

公开(公告)号：US12012897B2

公开(公告)日：2024-06-18

申请号：US17263997

申请日：2020-01-15

Applicant: MITSUBISHI HEAVY INDUSTRIES, LTD.

Inventor： Shotaro Nako ,  Takuto Haniu ,  Tomohisa Wada ,  Shojiro Furuya

IPC: F02C7/224 ,  F02C7/26 ,  F02C9/44 ,  F02K7/10

CPC classification number: F02C7/224 ,  F02C7/26 ,  F02C9/44 ,  F02K7/10 ,  F05D2220/80 ,  F05D2240/36 ,  F05D2270/304

Abstract: A jet engine is provided which can efficiently pressurize fuel. A jet engine 2 includes a pump 110 that heats fuel, a heating conduit 120 that heats the pressurized fuel, a fuel turbine 130 that provides mechanical power to the pump, and an electric rotating machine 140. When a given condition is not satisfied, the electric rotating machine 140 provides mechanical power to the fuel turbine 130. When the given condition is satisfied, the fuel that has passed through the heating conduit 120 before combustion flows into the fuel turbine 130 to provide mechanical power to the fuel turbine 130.

公开(公告)号：US20240084764A1

公开(公告)日：2024-03-14

申请号：US18308603

申请日：2023-04-27

Applicant: Hypersonix IP Holdings, Inc.

Inventor： Michael Kevin SMART

IPC: F02K7/10 ,  F02C7/04 ,  F02C7/228

CPC classification number: F02K7/10 ,  F02C7/04 ,  F02C7/228 ,  B64D2033/026 ,  F05D2220/10

Abstract: Airframe integrated scramjet engines are disclosed. Scramjet engines within the scope of this disclosure may be configured to integrate smoothly with an airframe of a hypersonic flight aircraft or vehicle. The scramjet engine may include capture shape of an inlet configured to capture airflow, a combustor configured for combustion of fuel and air, and an exit shape of a nozzle configured for expansion of the combusted fuel and air to provide hypersonic thrust. In some embodiments, the scramjet engine has a fixed geometry and a transitioning cross-sectional shape over its full length. The scramjet engine is configured to be a component of launch vehicle system.

公开(公告)号：US20230392566A1

公开(公告)日：2023-12-07

申请号：US18205088

申请日：2023-06-02

Applicant: Hamilton Sundstrand Corporation

Inventor： Przemyslaw KIELCZYKOWSKI ,  Marek WIT

IPC: F02K7/10 ,  B64D41/00 ,  H01F7/14

CPC classification number: F02K7/10 ,  B64D41/007 ,  H01F7/14 ,  F05D2220/34

Abstract: An actuator release mechanism includes: a longitudinal sleeve movable along an axis between a lock and release positions; drive means for causing the longitudinal sleeve to move along the axis; and bias means to bias the longitudinal sleeve to the lock position. The drive means includes: a rotary solenoid having a first direction of rotation and a second direction of rotation; a toggle member having a toggle shaft connected to and rotatable with the rotary solenoid, and a toggle head in engagement with the longitudinal sleeve by pins extending radially inwards from the longitudinal sleeve and a helical guide rail provided on a radially outer surface of the toggle head. The longitudinal sleeve is mounted around the toggle head, such that rotation of the solenoid causes rotation of the toggle member and the guide rails which causes the pin(s) to ride along the guide rail to rotate the sleeve.

公开(公告)号：US09447731B1

公开(公告)日：2016-09-20

申请号：US13586247

申请日：2012-08-15

Applicant: Eric E. Adamson ,  Lawrence E. Fink ,  Spencer R. Fugal

Inventor： Eric E. Adamson ,  Lawrence E. Fink ,  Spencer R. Fugal

IPC: F02C7/04 ,  F02K7/10 ,  B64D33/02 ,  B64C30/00

CPC classification number: F02C7/04 ,  B64C30/00 ,  B64D33/02 ,  B64D2033/026 ,  F02K7/10 ,  F05D2220/10 ,  F05D2220/80 ,  F05D2250/14 ,  Y02T50/672

Abstract: A supersonic inlet includes a supersonic section including a cowl which is at least partially elliptical, a ramp disposed within the cowl, and a flow inlet disposed between the cowl and the ramp. The ramp may also be at least partially elliptical.

Abstract translation: 超音速入口包括超音速部分，其包括至少部分椭圆形的整流罩，设置在整流罩内的斜坡，以及设置在整流罩和斜坡之间的流动入口。 斜坡也可以至少部分为椭圆形。

公开(公告)号：US20150354592A1

公开(公告)日：2015-12-10

申请号：US14828561

申请日：2015-08-18

Applicant: Hamilton Sundstrand Corporation

Inventor： Lawrence Binek ,  Brent J. Merritt

IPC: F04D29/52 ,  F02K7/10

CPC classification number: F04D29/522 ,  F02K7/10 ,  Y10T29/49245 ,  Y10T29/49247

Abstract: A ram air fan outer housing for directing air from a ram air fan rotor and air from a ram air bypass into a ram air fan outlet. The outer housing includes an outer cylinder with a ram air fan rotor end and a ram air fan outlet end. The ram air fan rotor end and the ram air fan outlet end are at opposite ends of an axis of the outer cylinder. A plenum is joined at a joint region for directing air from the ram air bypass into the outer cylinder. The plenum includes two plenum ridges with one at each of two walls of the plenum. The two walls of the plenum are parallel to the axis of the outer cylinder. Each of the two plenum ridges includes a protruding section of the corresponding plenum wall.

Abstract translation: 冲压风扇外壳，用于将来自冲压空气风扇转子的空气和冲压空气旁路的空气引导到冲压空气风扇出口。 外壳包括具有冲压空气风扇转子端和冲压空气风扇出口端的外筒。 冲压空气风扇转子端和冲压空气风扇出口端位于外筒轴线的相对端。 在连接区域处连接有气室，用于将空气从冲压空气旁路引导到外筒中。 增压室包括两个通风隆起，在通风室的两个墙壁的每一个处有一个。 气室的两个壁平行于外筒的轴线。 两个集气室脊中的每一个包括相应的增压室壁的突出部分。

公开(公告)号：US09046035B2

公开(公告)日：2015-06-02

申请号：US13088270

申请日：2011-04-15

Applicant: Sevan Megerian ,  Chandler Clifton

Inventor： Sevan Megerian ,  Chandler Clifton

IPC: F02B27/00 ,  F02K99/00 ,  F02C7/057 ,  F02K7/10

CPC classification number: F02C7/057 ,  F02K7/10 ,  F05D2270/17 ,  Y10T137/0536

Abstract: An inlet for removal of a boundary layer from an incoming air flow of an engine is disclosed. The inlet includes at least one compression element proximate to an inlet aperture of the engine. The compression element is selectably moveable between a first position and a second position along an axis. A boundary layer removal aperture is open when the compression element is in the first position and the boundary layer removal aperture is closed when the compression element is in the second position.

Abstract translation: 公开了用于从引擎的进入空气流中移除边界层的入口。 入口包括靠近发动机的入口孔的至少一个压缩元件。 压缩元件可选地沿着轴线在第一位置和第二位置之间移动。 当压缩元件处于第一位置时，边界层去除孔开放，并且当压缩元件处于第二位置时，边界层去除孔关闭。

公开(公告)号：US20140331682A1

公开(公告)日：2014-11-13

申请号：US14069454

申请日：2013-11-01

Applicant: MARK BOVANKOVICH

Inventor： MARK BOVANKOVICH

IPC: F02C7/042 ,  F02C7/057

CPC classification number: F02K7/10 ,  F05D2220/80 ,  Y02T50/671

Abstract: A high-speed-launch ramjet boost (HSLRB) engine includes a combustion system for igniting fuel pumped by a fuel pump from a fuel tank, where the combustion system includes an igniter, fuel injectors and frame holders. An inlet provides a pathway for air to flow toward the fuel injectors. A variable geometry (VG) nozzle having a nozzle actuator is included for exhausting exhaust gas from combustion of the fuel by the combustion system. A processor is coupled to receive sensing signals from at least one of a pressure sensor and a temperature sensor during flight, wherein the processor provides control signals to the nozzle actuator for dynamically controlling an aperture size of the VG nozzle.

Abstract translation: 高速发射冲压升压（HSLRB）发动机包括用于点燃燃料泵从燃料箱泵送的燃料的燃烧系统，其中燃烧系统包括点火器，燃料喷射器和框架支架。 入口提供空气朝向燃料喷射器流动的路径。 包括具有喷嘴致动器的可变几何（VG）喷嘴，用于通过燃烧系统排出燃料燃烧废气。 处理器被耦合以在飞行期间从压力传感器和温度传感器中的至少一个接收感测信号，其中处理器向喷嘴致动器提供控制信号，以动态地控制VG喷嘴的孔径尺寸。

公开(公告)号：US20140290259A1

公开(公告)日：2014-10-02

申请号：US14126782

申请日：2012-05-25

Applicant: Jean-Sébastien Plante ,  Mathieu Picard ,  David Rarncourt

Inventor： Jean-Sébastien Plante ,  Mathieu Picard ,  David Rarncourt

IPC: F02C7/264 ,  F23R3/28 ,  F02K7/10 ,  F02C3/16

CPC classification number: F23R3/28 ,  F02C3/165 ,  F02C7/264 ,  F02K7/10 ,  F23R3/18 ,  F23R3/286 ,  F23R3/343 ,  F23R2900/00012 ,  F23R2900/03343 ,  Y02T50/672

Abstract: A combustion systems and components for rotary ramjet engines. An injection system, optionally stratified for ease of engine startup, provides an air and fuel mixture to a combustion chamber. An ignition system ignites the mixture. A flameholding system may be positioned for communication with the combustion chamber to force an ignited flow of the air and fuel mixture toward a center of rotation within the ramjet engine. The ramjet engine may have a diverging stator for improved exhaust efficiency. The ignition may take place in the engine air intake. Alternatively, the ignition may take place within the combustion chamber using a dual-hub electrically charged system. An impulse turbine may use recirculation of injected fuel to cool a rim-rotor and/or to reduce windage on the rim-rotor. A sealing system may reduce gas leaks from a fuel conduit into the engine air intake.

Abstract translation: 用于旋转冲压喷气发动机的燃烧系统和部件。 为了便于发动机起动，可选地分层的喷射系统为燃烧室提供空气和燃料混合物。 点火系统点燃混合物。 火焰保持系统可以被定位成与燃烧室连通以迫使空气和燃料混合物的点燃流动朝向冲压喷气发动机内的旋转中心。 冲压式喷气发动机可以具有发散定子，以提高排气效率。 点火可能发生在发动机进气口。 或者，可以使用双毂式带电系统在燃烧室内进行点火。 脉冲涡轮机可以使用喷射燃料的再循环来冷却轮辋转子和/或减少轮辋转子上的风向。 密封系统可以减少从燃料管道到发动机进气口的气体泄漏。