专利快速检索-快速检索全球专利，免费商用专利数据库-IPRDB

1. 发明授权

US06205770B1 Rocket engine 有权
标题翻译：火箭发动机
公开(公告)号：US06205770B1
公开(公告)日：2001-03-27
申请号：US09522871
申请日：2000-03-10
申请人： Gregg G. Williams , Robert S. Thompson, Jr. , Richard D. Stephens , Dean S. Musgrave , John F. Jones , Guido D. Defever
发明人： Gregg G. Williams , Robert S. Thompson, Jr. , Richard D. Stephens , Dean S. Musgrave , John F. Jones , Guido D. Defever
IPC分类号： F02K948
CPC分类号： F02K9/52 , F02K9/48 , F02K9/62 , F02K9/64 , F02K9/66 , F02K9/72 , F05D2240/40
摘要： A rocket engine comprises first and second rotary injectors for injecting respective fuel and oxidizer propellant components into a first combustion chamber, and the effluent therefrom drives a turbine that rotates the rotary injectors. The mixture within the first combustion chamber is preferably fuel-rich so as to reduce the associated combustion temperature, and the fuel-rich effluent mixes in a second combustion chamber with additional oxidizer injected by a third rotary injector so as to generate a high temperature effluent suitable for propulsion. The rotary injectors are adapted so as to isolate the low pressure propellant supply from the relatively high pressures in the respective combustion chambers.
摘要翻译：火箭发动机包括用于将相应的燃料和氧化剂推进剂组分喷射到第一燃烧室中的第一和第二旋转喷射器，并且其流出物驱动旋转旋转喷射器的涡轮机。第一燃烧室内的混合物优选为富燃料，以便降低相关的燃烧温度，并且富含燃料的流出物在第二燃烧室中与另外的由第三旋转喷射器注入的氧化剂混合，从而产生高温流出物适合推进。旋转喷射器适于将低压推进剂供应与相应燃烧室中的较高压力隔离。

2. 发明授权

US06220016B1 Rocket engine cooling system 失效
标题翻译：火箭发动机冷却系统
公开(公告)号：US06220016B1
公开(公告)日：2001-04-24
申请号：US09522817
申请日：2000-03-10
申请人： Guido D. Defever , Robert S. Thompson, Jr.
发明人： Guido D. Defever , Robert S. Thompson, Jr.
IPC分类号： F02K1100
CPC分类号： F02K9/52 , F02K9/48 , F02K9/62 , F02K9/64 , F02K9/66 , F02K9/72 , F05D2240/40
摘要： A rocket engine comprises first and second combustion chambers with respective combustion chamber liners bounding respective annular passages, wherein the first combustion chamber discharges into the second, and the respective annular passages are in fluid communication with one another. A portion of the effluent from the first combustion chamber flows from the first combustion chamber to the second combustion chamber through the respective annular passages via orifices in the respective combustion chamber liners, so as to provide for effusion cooling of a surface of the second combustion chamber. The first combustion chamber preferably operates fuel rich, reducing the temperature of the effusion cooling gases, which may be further cooled by a portion of unburned fuel. A flow restriction such as a turbine between the first and second combustion chambers provides a pressure differential therebetween that induces flow of effusion cooling gases.
摘要翻译：火箭发动机包括第一和第二燃烧室，其中相应的燃烧室衬套限定相应的环形通道，其中第一燃烧室排放到第二燃烧室中，并且相应的环形通道彼此流体连通。来自第一燃烧室的流出物的一部分通过相应的环形通道经由各个燃烧室衬套中的孔从第一燃烧室流到第二燃烧室，以便提供第二燃烧室的表面的积液冷却。第一燃烧室优选地运行富燃料，降低了可以被一部分未燃烧燃料进一步冷却的排出冷却气体的温度。在第一和第二燃烧室之间的诸如涡轮机之类的流量限制件提供了它们之间的压力差，其引起渗出冷却气体的流动。

你已经成功收藏专利！

检索式保存成功!

IPRDB

热门服务

关于我们

友情链接

联系方式