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1. 发明申请

US20140196460A1 RAMJET INCLUDING A DETONATION CHAMBER AND AIRCRAFT COMPRISING SUCH A RAMJET 有权
标题翻译： RAMJET包括一个爆炸室和包含这样一个RAMJET的飞机
公开(公告)号：US20140196460A1
公开(公告)日：2014-07-17
申请号：US14116003
申请日：2012-05-09
申请人： François Falempin , Bruno Le Naour
发明人： François Falempin , Bruno Le Naour
IPC分类号： F02K7/20
CPC分类号： F02K7/20 , F02K7/00 , F02K7/08 , F02K7/10
摘要： The invention relates to a ramjet including a detonation chamber and an aircraft comprising such a ramjet. According to the invention, the ramjet (S1) comprises an annular detonation chamber (2) having a continuous detonation wave and fuel injection means (6) for continuously injecting fuel (F2) directly into the chamber (2) just downstream of an air injection base (3). The fuel (F2) and the air (F1) are injected separately into the detonation chamber (2) in a permanent manner throughout the operation of the ramjet (S1).
摘要翻译：本发明涉及一种包括爆震室的冲压喷气发动机和包括这种冲压喷气式飞机的飞机。根据本发明，冲压喷气发动机（S1）包括具有连续爆震波的环形爆炸室（2）和燃料喷射装置（6），用于将燃料（F2）直接喷射到空气喷射器下游的腔室（2）中基地（3）。燃料（F2）和空气（F1）在整个冲压喷气机（S1）的操作过程中以永久的方式分别注入到引爆室（2）中。

2. 发明申请

US20040128977A1 Multi-mode pulsed detonation propulsion system 失效
标题翻译：多模脉冲爆震推进系统
公开(公告)号：US20040128977A1
公开(公告)日：2004-07-08
申请号：US10337920
申请日：2003-01-07
发明人： Donald R. Wilson , Frank K. Lu
IPC分类号： F02K007/10
CPC分类号： F02K7/02 , F02K7/08 , F02K7/20 , Y02T50/671
摘要： A multi-mode propulsion system for potential application to hypersonic and aerospace planes. The system can employ various propulsion modes at various points in time, with the propulsion system employed at a given point in time being selected according to the velocity of the inlet airflow. In one embodiment, the propulsion system of the present invention has an ejector-augmented pulsed detonation rocket propulsion mode, a pulsed normal detonation wave engine mode, a steady oblique detonation wave engine mode, and a pure pulsed detonation rocket mode.
摘要翻译：一种用于潜在应用于超音速和航空航天飞机的多模式推进系统。该系统可以在各个时间点采用各种推进模式，根据入口气流的速度选择在给定时间点采用的推进系统。在一个实施例中，本发明的推进系统具有喷射器增强的脉冲爆震火箭推进模式，脉冲正常爆震波发动机模式，稳定的斜引爆波发动机模式和纯脉冲爆轰火箭模式。

3. 发明授权

US06631610B1 Consumable port cover for ducted integral rocket-ramjet engine 失效
标题翻译：用于管道一体式火箭冲压喷气发动机的消耗端口盖
公开(公告)号：US06631610B1
公开(公告)日：2003-10-14
申请号：US06511075
申请日：1983-07-05
申请人： Richard A. Van Dyk
发明人： Richard A. Van Dyk
IPC分类号： F02K718
CPC分类号： F02K9/50 , F02K7/105 , F02K7/18 , F02K7/20
摘要： In an integral rocket-ramjet engine the air intake ports are covered with a port cover made of a laminate of Pd and Al. This port cover is rapidly consumed in the brief period between the end of the rocket mode and commencement of the ramjet mode to allow ingress of ram air for the ramjet engine.
摘要翻译：在整体式火箭冲压喷气发动机中，进气口覆盖有由Pd和Al的叠层制成的端口盖。在火箭模式结束和冲压喷射模式开始之间的短暂时间内，该端口盖被快速消耗，以允许冲压式喷气发动机进入冲压空气。

4. 发明申请

US20020078679A1 Pulsed Detonation Engine With Divergent Inflow Transition Section 失效
标题翻译：脉冲引爆发动机不同流入过渡段
公开(公告)号：US20020078679A1
公开(公告)日：2002-06-27
申请号：US10008799
申请日：2001-11-13
申请人： McDonnell Douglas Corporation
发明人： Thomas A. Kaemming , Paul G. Willhite , Richard S. Dyer , Michael A. Guntorius
IPC分类号： F02K007/02
CPC分类号： F02K7/02 , F02K7/06 , F02K7/12 , F02K7/20 , F05D2250/324
摘要： A pulsed detonation engine having an initiator tube fueled with an enhanced fuel mixture is configured in fluid communication with a detonation chamber via a divergent inflow transition section. The divergent inflow transition section has a diverging contoured shape having a rate of divergence continuously dependent upon the diameter of the tube, the critical diameter of the enhanced fuel mixture within the tube and the cross-sectional area of the detonation chamber. The inflow transition section, which may have a stair-step configuration, includes a plurality of fuel and/or air ports to permit the fuel and air to be injected through the transition section and into the detonation chamber. The pulsed detonation engine may optionally include a volume of ejector/bypass air surrounding the detonation chamber, which captures the detonation engine exhaust and mixes the exhaust with the ejector air, and a back pressure device for feeding dynamic pressure ejector air to the interior of the detonation chamber near its outlet end.
摘要翻译：具有用增强的燃料混合物燃料的起动器管的脉冲式爆震发动机构造成通过发散流入过渡段与爆轰室流体连通。发散流入过渡段具有发散的轮廓形状，其发散速率连续取决于管的直径，管内的增强的燃料混合物的临界直径和爆炸室的横截面积。可以具有阶梯构造的流入过渡部分包括多个燃料和/或空气端口，以允许燃料和空气通过过渡段注入并进入引爆室。脉冲爆震发动机可以可选地包括围绕引爆室的一定体积的喷射器/旁路空气，其捕获引爆发动机排气并将排气与喷射器空气混合，以及用于将动态压力喷射器空气供给到内部的背压装置爆炸室靠近其出口端。

5. 发明授权

US2745248A Convertible pulse jet and ram jet engine 失效
标题翻译：可转换脉冲射流和冲压喷气发动机
公开(公告)号：US2745248A
公开(公告)日：1956-05-15
申请号：US18973650
申请日：1950-10-12
申请人： MCDONNELL AIRCRAFT CORP
发明人： WINTER JOHN S , KALLAL GEORGE W , MAZZONI JAMES J
IPC分类号： F02K7/20
CPC分类号： F02K7/20 , Y10T137/7839

6. 发明授权

US09353704B2 Air inlet arrangement and method of making the same 有权
标题翻译：进气口布置及其制作方法
公开(公告)号：US09353704B2
公开(公告)日：2016-05-31
申请号：US13541482
申请日：2012-07-03
申请人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
发明人： Timothy R. Conners , Preston A. Henne , Donald C. Howe
IPC分类号： F02C7/04 , F02C7/045 , B64D33/02 , F02K7/10 , F02K7/16 , F02K7/20 , F02K1/04 , F02K1/46 , F02C7/00 , F02K7/00 , F02K3/02
CPC分类号： F02K1/46 , B64D33/02 , B64D2033/026 , B64D2033/0273 , B64D2033/0286 , F02C7/00 , F02C7/04 , F02C7/045 , F02K1/04 , F02K1/34 , F02K3/02 , F02K7/00 , F02K7/10 , F02K7/16 , F02K7/20 , F05D2210/12 , F05D2220/323 , F05D2220/80 , F05D2230/60 , F05D2250/70 , F05D2260/96 , Y10T29/49346 , Y10T137/0536
摘要： An inlet arrangement is disclosed herein for use with a supersonic jet engine configured to consume air at a predetermined mass flow rate when the supersonic jet engine is operating at a predetermined power setting and moving at a predetermined Mach speed. The air inlet arrangement includes, but is not limited to, a cowl having a cowl lip and a center body coaxially aligned with the cowl. A protruding portion of the center body extends upstream of the cowl lip for a length greater than a conventional spike length. The protruding portion is configured to divert air flowing over the protruding portion out of a pathway of an inlet to the supersonic jet engine such that a remaining airflow approaching and entering the inlet matches the predetermined mass flow rate.
摘要翻译：本文公开了一种与超音速喷气发动机一起使用的入口装置，其构造成当超音速喷气发动机以预定的功率设定运行并以预定的马赫速度运动时以预定的质量流量消耗空气。空气入口装置包括但不限于具有整流罩和与整流罩同轴对准的中心体的整流罩。中心体的突出部分在前罩的上游延伸的长度大于传统的尖钉长度。突出部分构造成将在突出部分上流动的空气从入口的路径转移到超音速喷气发动机，使得接近并进入入口的剩余气流与预定质量流量匹配。

7. 发明申请

US20110036067A1 AIRFLOW MODULATION FOR DUAL MODE COMBINED CYCLE PROPULSION SYSTEMS 有权
标题翻译：双模式组合循环推进系统的气流调制
公开(公告)号：US20110036067A1
公开(公告)日：2011-02-17
申请号：US12539451
申请日：2009-08-11
申请人： George D. Rupp , Trajaen J. Troia
发明人： George D. Rupp , Trajaen J. Troia
IPC分类号： F02K3/02
CPC分类号： F01D17/12 , F01D5/02 , F01D9/04 , F02C7/042 , F02K3/02 , F02K7/075 , F02K7/16 , F02K7/20 , F05D2220/10 , F05D2300/502 , Y02T50/672
摘要： The present invention relates to a mechanical system and method that modulates airflow in an aircraft inlet diffuser that is used in conjunction with an aircraft engine that integrates both a center turbine engine and a high Mach engine such as a constant volume combustor (CVC) arrangement or ramjet arrangement with intakes formed co-centrically about the turbine. The modulation system uses two articulating components, a movable air flow duct and an articulating cone. The air flow duct, in a first position, is in exclusive air flow communication with the circular intake face of the turbine in a first position to receive air from the intake diffuser. In this configuration the expandable cone is in a retracted position and does not redirect airflow and allows the aircraft to operates in low speed mode as only the turbo jet receives airflow. In a transition speed mode, the air flow duct is retracted to allow air flow to both the turbo jet and the CVC. At its widest expanse, the articulating cone completely covers the turbo jet circular intake face directing air solely to the high Mach aircraft engine to allow the aircraft to operate in high speed mode.
摘要翻译：本发明涉及一种机械系统和方法，其调节与整合中等涡轮发动机和诸如恒定体积燃烧室（CVC）排列的高马赫发动机的飞机发动机结合使用的飞行器入口扩散器中的气流，或冲压喷气式排气装置，与涡轮机共同形成进气口。调制系统使用两个铰接部件，一个可移动的空气流动管道和一个铰接锥体。处于第一位置的空气流动管道处于与来自涡轮机的圆形进气面的第一位置专用气流连通，以从进气扩散器接收空气。在该配置中，可膨胀锥体处于缩回位置，并且不会使气流重定向，并允许飞行器以低速模式操作，因为只有涡轮喷气机接收气流。在过渡速度模式中，空气流动管道缩回以允许空气流动到涡轮喷气机和CVC。铰链锥体完全覆盖涡轮喷气圆形进气面，将空气仅引导到高马赫飞机发动机，以使飞机能够以高速运行。

8. 发明申请

US20030029162A1 PROPULSION MODULE 有权
标题翻译：推进模块
公开(公告)号：US20030029162A1
公开(公告)日：2003-02-13
申请号：US09759933
申请日：2001-01-12
发明人： Von David Baker
IPC分类号： F02K007/02
CPC分类号： B64D27/20 , B64D33/02 , B64G1/002 , B64G1/401 , F02C7/042 , F02K7/04 , F02K7/06 , F02K7/20 , F02K9/74 , F02K9/78 , Y10T137/0536
摘要： A propulsion module including a wave rotor detonation engine having a rotor with a plurality of fluid flow channels. The fluid flow channels extend between an inlet rotor plate, which has a pair of fixed inlet ports, and an outlet rotor plate, which has a pair of fixed outlet ports. The propulsion module includes a pair of inlet ducts have a stowed mode and a deployed mode. The pair of inlet ducts include a fluid flow passageway adapted to convey air to the pair of inlet ports. A fueling system is positioned prior to the inlet ports to deliver fuel into the air introduced through the pair of inlet ducts and into the pair of inlet ports. A pair of ignition chambers are disposed adjacent to the inlet rotor plate.
摘要翻译：一种推进模块，其包括具有多个流体流动通道的转子的波浪转子爆震发动机。流体流动通道在具有一对固定入口的入口转子板和具有一对固定出口的出口转子板之间延伸。推进模块包括一对具有收起模式和展开模式的入口管道。一对入口管道包括适于将空气输送到一对入口端口的流体流动通道。加油系统位于入口之前，以将燃料输送到通过一对入口管引入的空气中，并进入一对入口。一对点火室与入口转子板相邻设置。

9. 发明申请

US20020059793A1 Pulsed Detonation Engine With Backpressure 有权
标题翻译：带背压的脉冲引爆发动机
公开(公告)号：US20020059793A1
公开(公告)日：2002-05-23
申请号：US10008103
申请日：2001-11-13
发明人： Thomas A. Kaemming , Paul G. Willhite , Richard S. Dyer , Michael A. Guntorius
IPC分类号： F02K007/02
CPC分类号： F02K7/02 , F02K7/06 , F02K7/12 , F02K7/20 , F05D2250/324
摘要： A pulsed detonation engine having an initiator tube fueled with an enhanced fuel mixture is configured in fluid communication with a detonation chamber via a divergent inflow transition section. The divergent inflow transition section has a diverging contoured shape having a rate of divergence continuously dependent upon the diameter of the tube, the critical diameter of the enhanced fuel mixture within the tube and the cross-sectional area of the detonation chamber. The inflow transition section, which may have a stair-step configuration, includes a plurality of fuel and/or air ports to permit the fuel and air to be injected through the transition section and into the detonation chamber. The pulsed detonation engine may optionally include a volume of ejector/bypass air surrounding the detonation chamber, which captures the detonation engine exhaust and mixes the exhaust with the ejector air, and a back pressure device for feeding dynamic pressure ejector air to the interior of the detonation chamber near its outlet end.
摘要翻译：具有用增强的燃料混合物燃料的起动器管的脉冲式爆震发动机构造成通过发散流入过渡段与爆轰室流体连通。发散流入过渡段具有发散的轮廓形状，其发散速率连续取决于管的直径，管内的增强的燃料混合物的临界直径和爆炸室的横截面积。可以具有阶梯构造的流入过渡部分包括多个燃料和/或空气端口，以允许燃料和空气通过过渡段注入并进入引爆室。脉冲爆震发动机可以可选地包括围绕引爆室的一定体积的喷射器/旁路空气，其捕获引爆发动机排气并将排气与喷射器空气混合，以及用于将动态压力喷射器空气供给到内部的背压装置爆炸室靠近其出口端。

10. 发明授权

US3604211A Combined pulse jet and variable ram jet engine 失效
标题翻译：组合脉冲喷射和可变RAM喷射发动机
公开(公告)号：US3604211A
公开(公告)日：1971-09-14
申请号：US3604211D
申请日：1969-09-12
申请人： JOHN N GHOUGASIAN
发明人： GHOUGASIAN JOHN N
IPC分类号： F02K7/20 , F02K7/06 , F02K7/10
CPC分类号： F02K7/20
摘要： A reaction thrust engine operating in a pulse jet mode to attain cruising speeds, is converted to ram jet operation by variations in the internal flow controlling geometry and location of the combustion zone. This is accomplished by an axially shiftable center body and a tubular check valve assembly.

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