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11. 发明授权

US5385263A Compressed gas mobile storage module and lightweight composite cylinders 失效
标题翻译：压缩气体移动存储模块和轻质复合气瓶
公开(公告)号：US5385263A
公开(公告)日：1995-01-31
申请号：US236735
申请日：1994-05-02
申请人： Kenneth G. Kirk , Leonard Schoenman , Kris E. Baxter , John B. Mouritsen
发明人： Kenneth G. Kirk , Leonard Schoenman , Kris E. Baxter , John B. Mouritsen
IPC分类号： B60P3/00 , B65D8/08 , F17C1/16 , F17C13/08
CPC分类号： F17C1/16 , F17C13/085 , F17C2201/0109 , F17C2201/035 , F17C2201/054 , F17C2201/056 , F17C2203/035 , F17C2203/0629 , F17C2203/0636 , F17C2203/0665 , F17C2203/067 , F17C2205/0107 , F17C2205/013 , F17C2205/0161 , F17C2205/0332 , F17C2205/0338 , F17C2209/2154 , F17C2209/2163 , F17C2223/0123 , F17C2270/0168 , F17C2270/0171
摘要： Lightweight compressed gas cylinders are incorporated into a module which contains manifolding and which is designed for easy loading, unloading and transport on a flat-bed truck or other vehicle, particularly a roll-on roll-off transport truck, which is a specialized truck for mechanized handling of large containers. The module eliminates the need to retain the vehicle itself at the site of use. While a variety of cylinders of composite construction to achieve light weight can be used, certain novel composite cylinders whcih are particularly useful are also disclosed. These cylinders have a lightweight metallic liner or core cylinder wrapped with three layers of wound fiber. The inner and outer layers are axially-wound glass fiber and the intermediate layer is hoop-wound carbon fiber.
摘要翻译：轻型压缩气瓶装入一个包含歧管的模块中，该模块设计用于在平板车或其他车辆上轻松装载，卸载和运输，特别是滚装式滚降运输卡车，这是一种专门的卡车机械化处理大型集装箱。该模块消除了将车辆本身保持在使用现场的需要。虽然可以使用各种复合结构的气缸实现轻量化，但是也公开了特别有用的某些新型复合气缸。这些气缸具有轻薄的金属衬套或芯筒，其中包裹有三层缠绕纤维。内层和外层是玻璃纤维的轴向缠绕，中间层为环形碳纤维。

12. 发明授权

US4936091A Two stage rocket combustor 失效
标题翻译：两级火箭燃烧器
公开(公告)号：US4936091A
公开(公告)日：1990-06-26
申请号：US317166
申请日：1989-02-28
申请人： Leonard Schoenman
发明人： Leonard Schoenman
IPC分类号： F02K9/52 , F02K9/62 , F02K9/64
CPC分类号： F02K9/52 , F02K9/62 , F02K9/64
摘要： A method for operating a rocket engine by injecting fuel and oxidizer into an elongated combustion chamber in two flows, a core flow where the fuel and oxidizer are intimately mixed and immediately combusted and a peripheral curtain flow which surrounds the core flow and which is in contact with the combustion chamber wall to cool it and limit the heat transfer from the wall to the injector to prevent vapor locks in the injector. To prevent decomposed or partially combusted propellant products from chemically reacting with the chamber wall no mixing of fuel and oxidizer takes place in the curtain flow. The curtain flow is deflected radially inward into the core flow, before decomposed or partially combusted products can come into contact with the wall, into the core flow to fully combust the curtain flow out of contact with the wall. The rocket engine is defined by serially arranged first and second combustion chambers and an injector constructed to form the core and curtain flows. A ring plate projects radially inward at the downstream end of the first chamber and deflects the curtain flow into the coreflow.
摘要翻译：一种通过将燃料和氧化剂注入到两个流中的细长燃烧室中来操作火箭发动机的方法，其中燃料和氧化剂被紧密地混合并立即燃烧的核心流动以及围绕核心流动并与之接触的周边帘流其中燃烧室壁将其冷却并限制从壁到喷射器的热传递，以防止喷射器中的气体锁定。为了防止分解或部分燃烧的推进剂产物与室壁发生化学反应，在幕流中不会发生燃料和氧化剂的混合。在分解或部分燃烧的产品可能与壁接触的情况下，帘子流动被径向向内偏转到芯流中，从而将帘子流与墙壁完全燃烧以完全燃烧。火箭发动机由串联布置的第一和第二燃烧室和构造成形成芯和帘流的喷射器限定。环形板在第一室的下游端径向向内突出，并将窗帘流偏转到芯流中。

13. 发明授权

US4882904A Two stage rocket combustor 失效
标题翻译：两级火箭燃烧器
公开(公告)号：US4882904A
公开(公告)日：1989-11-28
申请号：US172622
申请日：1988-03-24
申请人： Leonard Schoenman
发明人： Leonard Schoenman
IPC分类号： F02K9/52 , F02K9/62 , F02K9/64
CPC分类号： F02K9/64 , F02K9/52 , F02K9/62
摘要： A method for operating a rocket engine by injecting fuel and oxidizer into an elongated combustion chamber in two flows, a core flow where the fuel and oxidizer are intimately mixed and immediately combusted and a peripheral curtain flow which surrounds the core flow and which is in contact with the combustion chamber wall to cool it and limit the heat transfer from the wall to the injector to prevent vapor locks in the injector. To prevent decomposed or partially combusted propellant products from chemically reacting with the chamber wall no mixing of fuel and oxidizer takes place in the curtain flow. The curtain flow is deflected radially inward into the core flow, before decomposed or partially combusted products can come into contact with the wall, into the core flow to fully combust the curtain flow out of contact with the wall. The rocket engine is defined by serially arranged first and second combustion chambers and an injector constructed to from the core and curtain flows. A ring plate projects radially inward at the downstream end of the first chamber and deflects the curtain flow into the coreflow.
摘要翻译：一种通过将燃料和氧化剂注入到两个流中的细长燃烧室中来操作火箭发动机的方法，其中燃料和氧化剂被紧密地混合并立即燃烧的核心流动以及围绕核心流动并与之接触的周边帘流其中燃烧室壁将其冷却并限制从壁到喷射器的热传递，以防止喷射器中的气体锁定。为了防止分解或部分燃烧的推进剂产物与室壁发生化学反应，在幕流中不会发生燃料和氧化剂的混合。在分解或部分燃烧的产品可能与壁接触的情况下，帘子流动被径向向内偏转到芯流中，从而将帘子流与墙壁完全燃烧以完全燃烧。火箭发动机由串联布置的第一和第二燃烧室和从核心和帘幕流构造的喷射器限定。环形板在第一室的下游端径向向内突出，并将窗帘流偏转到芯流中。

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