公开(公告)号：US11976612B2

公开(公告)日：2024-05-07

申请号：US16209466

申请日：2018-12-04

申请人： Judith Marie Bovankovich

发明人： Mark Bovankovich

IPC分类号： F02K7/10 ,  B64D39/00 ,  B64G1/00 ,  F02C7/22 ,  F02K1/09 ,  F02K7/16 ,  F02K7/18

CPC分类号： F02K7/10 ,  B64D39/00 ,  B64G1/002 ,  B64G1/005 ,  F02C7/22 ,  F02K1/09 ,  F02K7/16 ,  F02K7/18 ,  F05D2220/80 ,  Y02T50/60

摘要： 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.

公开(公告)号：US11781507B2

公开(公告)日：2023-10-10

申请号：US17853691

申请日：2022-06-29

申请人： ATRX, Inc.

发明人： John A Bossard ,  John L Bergmans

IPC分类号： F02K7/16 ,  F02K3/10 ,  F01D9/04 ,  F02K9/78 ,  F02K9/48 ,  F02K9/08 ,  F02K9/30 ,  F02K9/42 ,  F02K3/12 ,  F02K9/26 ,  F02K9/97 ,  F02K7/18 ,  F02K9/76

CPC分类号： F02K7/16 ,  F01D9/041 ,  F02K3/10 ,  F02K3/12 ,  F02K7/18 ,  F02K9/08 ,  F02K9/26 ,  F02K9/30 ,  F02K9/42 ,  F02K9/48 ,  F02K9/76 ,  F02K9/78 ,  F02K9/97 ,  F05D2220/74 ,  F05D2240/128 ,  F05D2240/35

摘要： A turbojet engine capable of operation in an Air Turbo Rocket (ATR) mode includes a compressor, a rotatable turbine wheel comprising turbine blades, a non-rotating guide vane ring comprising guide vanes, a turbine shaft configured to power said compressor, a combustor, a gas generator, and a main combustor. The main combustor is configured to combust hot, fuel rich gas from the gas generator in air compressed by the compressor. Hot, fuel rich gas from the gas generator is directed towards the turbine blades by a directing means.

公开(公告)号：US09810153B2

公开(公告)日：2017-11-07

申请号：US14296624

申请日：2014-06-05

申请人： Reaction Engines Ltd

发明人： Alan Bond ,  Richard Varvill

IPC分类号： F02C3/04 ,  F02C7/228 ,  F02C7/04 ,  F02C7/143 ,  F02K7/18 ,  F02K9/78 ,  F02C7/08

CPC分类号： F02C7/228 ,  F02C3/04 ,  F02C7/04 ,  F02C7/08 ,  F02C7/143 ,  F02K7/18 ,  F02K9/78 ,  F05D2220/70 ,  F05D2240/35 ,  F05D2260/20 ,  F05D2260/213

摘要： The present disclosure relates to an engine having two modes of operation—air breathing and rocket—that may be used in aerospace applications such as in an aircraft, flying machine, or aerospace vehicle. The engine's efficiency can be maximized by using a precooler arrangement to cool intake air in air breathing mode using cold fuel delivery systems used for the rocket mode. By introducing the precooler and certain other engine cycle components, and arranging and operating them as described, problems such as those associated with higher fuel and weight requirements and frost formation can be alleviated.

公开(公告)号：US20160326986A1

公开(公告)日：2016-11-10

申请号：US14965718

申请日：2015-12-10

申请人： 8801541 CANADA INC.

发明人： LUC LAFOREST ,  Timothy Stephen Rupcich

IPC分类号： F02K7/18 ,  F02K9/62 ,  F23R3/02

CPC分类号： F02K7/18 ,  F02K9/62 ,  F05B2220/10 ,  F23R3/02

摘要： The jet engine comprising a ramjet air path extending from an intake, into a combustion chamber, and out an exhaust nozzle, a fuel inlet leading into the combustion chamber, an oxidizer inlet leading into the combustion chamber and a partition being operable to selectively close the ramjet air path upstream of the combustion chamber to allow operation of the jet engine in rocket mode and open the ramjet air path to allow operation of the jet engine in ramjet mode.

摘要翻译： 喷气式发动机包括从进气口延伸到燃烧室中并且排出喷嘴的冲压喷气式空气路径，通向燃烧室的燃料入口，通向燃烧室的氧化剂入口和可操作地选择性地关闭 冲压喷气式空气路径在燃烧室的上游，以允许喷气发动机在火箭模式下操作并且打开冲压喷气式空气路径以允许喷射发动机以冲压喷射模式操作。

公开(公告)号：US09371800B2

公开(公告)日：2016-06-21

申请号：US14002292

申请日：2012-02-29

申请人： Mark Grollo

发明人： Mark Grollo

IPC分类号： F02K1/00 ,  F02K7/18 ,  F02K1/12 ,  F02K9/78 ,  F02K9/86 ,  F02K9/97

CPC分类号： F02K7/18 ,  F02K1/1223 ,  F02K9/78 ,  F02K9/86 ,  F02K9/972

摘要： This invention relates to an engine (2) for use in aerial vehicle (1) including a rocket (9) and ram jet engine formed from an intake (8) and a combustion chamber (10). The rocket engine (9) includes an oxidiser combustion chamber (21) which exhausts through the combustion chamber (10). The engine also includes a nozzle (12). Both the intake (8) and nozzle (12) include rectilinear ducts which are defined in part by baffles (16) and panels (33) respectively. Both the baffles (16) and panels (33) are adjustable to adjust the airflow characteristics therethrough.

摘要翻译： 本发明涉及一种用于飞行器（1）的发动机（2），其包括由进气口（8）和燃烧室（10）形成的火箭（9）和冲程喷气发动机。 火箭发动机（9）包括通过燃烧室（10）排出的氧化剂燃烧室（21）。 发动机还包括喷嘴（12）。 进气口（8）和喷嘴（12）都包括分别由挡板（16）和面板（33）部分限定的直线导管。 挡板（16）和面板（33）都是可调节的，以调节通过其的气流特性。

公开(公告)号：US08344304B2

公开(公告)日：2013-01-01

申请号：US12964798

申请日：2010-12-10

申请人： Chris E. Geswender

发明人： Chris E. Geswender

IPC分类号： F41G7/00 ,  F42B15/01 ,  G06F19/00

CPC分类号： F02K7/10 ,  F02K7/105 ,  F02K7/18 ,  F42B10/38 ,  F42B15/10

摘要： Methods and apparatus for delivering a missile may operate in conjunction with a missile comprising an outer skin. The missile may be configured in a closed position and an open position. In the open position, an aperture is opened in the outer skin, for example to supply air to an air-breathing engine. In the closed position, the aperture is closed.

摘要翻译： 用于传送导弹的方法和装置可以与包括外部皮肤的导弹一起操作。 导弹可以配置在关闭位置和打开位置。 在打开位置时，在外皮中开孔，例如将空气供给到空气呼吸引擎。 在关闭位置，孔关闭。

公开(公告)号：US07762077B2

公开(公告)日：2010-07-27

申请号：US11633836

申请日：2006-12-05

申请人： Robert J. Pederson ,  Stephen N. Schmotolocha ,  William W. Follett

发明人： Robert J. Pederson ,  Stephen N. Schmotolocha ,  William W. Follett

IPC分类号： F02K7/08

CPC分类号： B64C30/00 ,  B64D33/02 ,  B64D33/04 ,  B64D2033/026 ,  F02K7/14 ,  F02K7/16 ,  F02K7/18 ,  Y02T50/671

摘要： A single-stage hypersonic vehicle is comprised of a low-speed and a high-speed propulsion system. The low-speed propulsion system propels the single-stage vehicle to a threshold velocity, after which the high-speed propulsion system then takes over. The low-speed propulsion system includes a combined-cycle engine featuring a swirl generator that is integrated into a turbojet engine to provide a compact turbojet and swirl afterburner-ramjet propulsion system. The high-speed propulsion system includes a hypersonic engine that is operable at the threshold takeover velocity and beyond. In various embodiments, the high-speed propulsion system comprises a scramjet, rocket, or scramjet/rocket engine depending requirements. Benefits of the swirl generator design include its ability to rapidly and efficiently atomize, vaporize, mix and burn the fuel and oxidizer for the low speed propulsion system, significantly reduce length, weight, cooling requirements and complexity for both propulsion systems, while maintaining high propulsion performance and reducing propulsion and launch costs.

摘要翻译： 单级超音速车辆由低速和高速推进系统组成。 低速推进系统推动单级车辆达到阈值速度，此后高速推进系统接管。 低速推进系统包括一个组合循环发动机，其特征在于涡轮发生器被集成到涡轮喷气发动机中，以提供紧凑的涡轮喷气和涡流后燃烧器 - 冲压喷气推进系统。 该高速推进系统包括一个超音速发动机，其可以以阈值收购速度和超出速度操作。 在各种实施例中，高速推进系统包括依照要求的冲压喷气发动机，火箭或冲击式/火箭发动机。 涡流发生器设计的优点包括其快速有效地雾化，蒸发，混合和燃烧低速推进系统的燃料和氧化剂的能力，显着降低推进系统的长度，重量，冷却要求和复杂性，同时保持高推进 性能和减少推进和发射成本。

公开(公告)号：US20090120057A1

公开(公告)日：2009-05-14

申请号：US11995112

申请日：2006-07-20

申请人： Aryeh Yaakov Kohn

发明人： Aryeh Yaakov Kohn

IPC分类号： F02K9/00

CPC分类号： F02K9/78 ,  F02K7/18

摘要： A propulsion system for a combined aircraft/spacecraft including: a jet engine having a longitudinal axis defined in a direction from a front end at an air intake to a rear end at a jet exhaust: a front end at an air intake to a rear end at the jet exhaust; a rocket engine having a longitudinal axis defined normal to a rear end at a rocket exhaust; a common engine housing having an elongated shape and wherein the jet engine and the rocket engine are configured substantially coaxially and with respective rear ends facing the same direction when the rocket engine is operated.

摘要翻译： 一种用于组合的飞行器/航天器的推进系统，包括：喷气发动机，其具有沿着从进气口的前端到喷气排气口的后端的方向限定的纵向轴线：进气口的前端到后端 在喷气排气; 火箭发动机具有垂直于火箭尾气的后端的纵向轴线; 具有细长形状的通用发动机壳体，并且其中喷气发动机和火箭发动机基本同轴地配置，并且当火箭发动机运转时相应的后端面向相同的方向。

公开(公告)号：US20080128547A1

公开(公告)日：2008-06-05

申请号：US11633837

申请日：2006-12-05

申请人： Robert J. Pederson ,  Stephen N. Schmotolocha ,  William W. Follett

发明人： Robert J. Pederson ,  Stephen N. Schmotolocha ,  William W. Follett

IPC分类号： B64D27/02 ,  F02K7/10 ,  B64D27/16 ,  B64D27/10 ,  F02K3/10

CPC分类号： B64C30/00 ,  F02K7/14 ,  F02K7/16 ,  F02K7/18 ,  F05D2220/80 ,  F23R3/16 ,  F23R3/20 ,  Y02T50/671

摘要： The present invention is directed toward a two-stage hypersonic vehicle, comprising a first-stage vehicle and a second stage vehicle. The first-stage vehicle includes a combined-cycle engine and a swirl generator for propelling the first-stage vehicle and the second-stage vehicle to a threshold velocity, which in one embodiment is about Mach 6. In one embodiment, the first-stage combined-cycle engine integrates a swirl generator into a gas turbine engine, providing a highly compact afterburner and a ramjet engine within the gas turbine engine. One benefit of the integrated swirl generator is the ability to significantly reduce overall first-stage gas turbine and afterburner-ramjet size and weight, while retaining high performance. The second-stage vehicle is detachably secured to the first-stage vehicle and includes a hypersonic engine. In various embodiments, the hypersonic engine may comprise one of the following engine configurations: scramjet, rocket, or scramjet/rocket depending on the mission profile and requirements.

摘要翻译： 本发明涉及一种包括第一级车辆和第二级车辆的两级超音速车辆。 第一级车辆包括联合循环发动机和用于将第一级车辆和第二级车辆推进到阈值速度的旋转发生器，在一个实施例中，该阈值速度约为马赫数6.在一个实施例中，第一级车辆 联合循环发动机将涡流发生器集成到燃气涡轮发动机中，在燃气涡轮发动机内提供高度紧凑的加力燃烧器和冲压喷气发动机。 集成涡流发电机的一个好处是能够在保持高性能的同时显着降低整体的第一级燃气轮机和后燃机冲压喷气机的尺寸和重量。 第二级车辆可拆卸地固定到第一级车辆并且包括超音速发动机。 在各种实施例中，超音速发动机可以包括以下发动机配置之一：取决于任务简档和要求的冲压喷气发动机，火箭或冲击式喷气式火箭/火箭。

公开(公告)号：US20070119149A1

公开(公告)日：2007-05-31

申请号：US11290330

申请日：2005-11-30

申请人： Leonard Marandiuc

发明人： Leonard Marandiuc

IPC分类号： F02K7/10

CPC分类号： F02K7/02 ,  F02K7/10 ,  F02K7/16 ,  F02K7/18 ,  F05D2220/10 ,  F05D2220/80

摘要： The present invention provides a hypersonic jet engine able to start in air-breathing mode, on its own, from zero speed without a compressor. The hypersonic jet engine, known herein as the hyperjet is also able to fly an aircraft at and faster than Mach 6 without using the scramjet method of combustion, while maintaining a fuel economy superior to that of a aircraft utilizing a turbofan engine. The present invention is operable in a pulsejet mode, a ramjet mode, and chemical rocket mode, and utilizes front and back airflow gates driven by DC motors or electromagnetic fields.

摘要翻译： 本发明提供了一种超音速喷气发动机，能够在没有压缩机的情况下以零速度自己开始呼吸模式。 超音速喷气发动机在这里被称为高速喷气发动机还能够在不使用冲击式燃烧方式的情况下飞行飞行器而不使用马赫数6，同时维持比使用涡轮风扇发动机的飞机的燃料经济性更好的燃料经济性。 本发明可以在脉冲喷射模式，冲压喷射模式和化学火箭模式下操作，并且利用由直流电动机或电磁场驱动的前后气流门。