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1. 发明授权

US4098329A Modular heat exchanger 失效
标题翻译：模块式换热器
公开(公告)号：US4098329A
公开(公告)日：1978-07-04
申请号：US709787
申请日：1976-07-29
申请人： Donald W. Culver
发明人： Donald W. Culver
IPC分类号： F28D7/16 , F28F9/02 , G21D1/00 , F28D7/10
CPC分类号： F28F9/02 , F28D7/1669 , F28D2021/0054
摘要： A heat exchanger for use in nuclear reactors includes a heat exchange tube bundle formed from similar modules each having a hexagonal shroud containing a large number of thermally conductive tubes which are connected with inlet and outlet headers at opposite ends of each module, the respective headers being adapted for interconnection with suitable inlet and outlet manifold means. In order to adapt the heat exchanger for operation in a high temperature and high pressure environment and to provide access to all tube ports at opposite ends of the tube bundle, a spherical tube sheet is arranged in sealed relation across the chamber with an elongated duct extending outwardly therefrom to provide manifold means for interconnection with the opposite end of the tube bundle.
摘要翻译：用于核反应堆的热交换器包括由类似的模块形成的热交换管束，每个模块具有包含大量导热管的六角形护罩，每个导热管与每个模块的相对端处的入口和出口集管相连，适于与合适的入口和出口歧管装置互连。为了使热交换器适应于在高温和高压环境中操作并且提供对管束相对端处的所有管端口的通路，球形管板以密封的关系布置在腔室上，并具有延伸的细长管道向外提供用于与管束的相对端相互连接的歧管装置。

2. 发明授权

US5873239A Nuclear rocket engine incorporating a heat exchange 失效
标题翻译：装有热交换的核火箭发动机
公开(公告)号：US5873239A
公开(公告)日：1999-02-23
申请号：US727868
申请日：1996-10-08
申请人： Donald W. Culver
发明人： Donald W. Culver
IPC分类号： G21D5/02
CPC分类号： G21D5/02 , G21Y2002/301 , G21Y2002/304 , G21Y2004/30
摘要： A heat exchanger includes a block having a first group of passages arranged in a generally circular pattern, a second group of passages spaced radially outward from the first group of passages and multiple groups of channels extending generally normal to and fluidly coupling the first and second groups of passages for radial flow therebetween. Selected pairs of passages, each including one passage from each passage group, are adapted for coupling to a first circulation line. The other ones of the passages are adapted for coupling to a second circulation line so that fluid heat from one of the circulation lines can be transferred to fluid from the other one of the lines in the heat exchanger. With this dense flow configuration, a compact heat exchanger can be constructed which, for example, is especially advantageous when used in conjunction with nuclear thermal rocket engines where space is at a premium. The dense fluid flow pattern also reduces material requirements and, thus, advantageously reduces weight. In addition, the passages and channels are distributed to form an essentially uniform distribution of voids. This enhances the uniformity of the heat exchanger density and, thus, improves its efficiency as a gamma shield when used with nuclear systems.
摘要翻译：热交换器包括具有以大致圆形图案布置的第一组通道的块，与第一组通道径向向外间隔的第二组通道，以及大体上垂直于第一组和第二组流体连接的多组通道的通道用于其间的径向流动。选择的一对通道，每个通道包括来自每个通道组的一个通道，适于联接到第一循环管线。其他通道适于联接到第二循环管线，使得来自循环管线之一的流体热量可以从热交换器中的另一条管线传递到流体。利用这种密集的流动结构，可以构造一个紧凑的热交换器，例如当与空间有限的核热能火箭发动机结合使用时，这是特别有利的。致密的流体流动模式也减少了材料的需求，因此有利地减轻了重量。此外，通道和通道被分配以形成基本均匀的空隙分布。这增强了热交换器密度的均匀性，因此当与核系统一起使用时，其提高了作为γ屏蔽的效率。

3. 发明授权

US5636512A Nuclear rocket feed system incorporating an auxiliary power cycle 失效
标题翻译：包含辅助动力循环的核火箭进料系统
公开(公告)号：US5636512A
公开(公告)日：1997-06-10
申请号：US324058
申请日：1994-10-14
申请人： Donald W. Culver
发明人： Donald W. Culver
IPC分类号： G21D5/02 , G21D5/00
CPC分类号： G21D5/02
摘要： A nuclear rocket engine comprising a primary feed system (4) for pumping rocket propellant from a propellant source (10) to a nuclear reactor (6) and an auxiliary feed system (60) coupled to the primary feed system. The auxiliary feed system includes a space radiator (84) for discharging excess reactor heat into space and a motorgenerator (74) for creating electricity from the excess reactor heat. A recuperator (20) operates to heat liquid propellant before it enters the reactor and to retain heat within the system. The auxiliary power system can be configured into a high thrust mode (see FIG. 1) for withdrawing heat from the engine when the reactor is operating at full power, a low thrust mode (see FIG. 2) for throttling propellant flow and radiating heat from the engine during reactor shutdown and a zero thrust mode (see FIG. 3) for cooling the nuclear reactor and generating electricity for the rocket's auxiliary power requirements for the remainder of the mission.
摘要翻译：一种核火箭发动机，其包括用于将火箭推进剂从推进剂源（10）泵送到核反应堆（6）的主进料系统（4）和耦合到主进料系统的辅助进料系统（60）。辅助进料系统包括用于将多余反应堆热量排放到空间中的空间散热器（84）和用于从多余的反应堆热量产生电力的电动发电机（74）。换热器（20）在其进入反应器之前加热液体推进剂并在系统内保持热量。辅助动力系统可以配置成高推力模式（见图1），用于当反应堆全功率运行时从发动机中排出热量，用于节流推进剂流量和辐射热的低推力模式（见图2）在反应堆关闭期间的发动机和用于冷却核反应堆的零推力模式（参见图3），并且为剩余任务中的火箭的辅助动力要求发电。

4. 发明授权

US5475722A Nuclear thermal rocket engine and nozzle therefor 失效
标题翻译：核热火箭发动机和喷嘴
公开(公告)号：US5475722A
公开(公告)日：1995-12-12
申请号：US324055
申请日：1994-10-14
申请人： Donald W. Culver
发明人： Donald W. Culver
IPC分类号： G21D5/02
CPC分类号： G21D5/02 , Y10S376/909
摘要： A nuclear thermal rocket engine is provided with an integrated and compact construction that facilitates vehicle size and weight reduction. The engine includes a nuclear reactor core having multiple fuel assemblies and moderator rods disposed therebetween. A reactor vessel surrounds a reflector assembly which surrounds the core and includes multiple passages formed therein for circulating coolant therethrough. The reactor vessel is surrounded by a nozzle assembly which includes a nozzle block having a plenum fluidly coupled to the outlets of the fuel assemblies and a nozzle throat region. Multiple struts extend from the reactor vessel and through the nozzle throat region to divide that region into multiple nozzle throats. Each strut includes multiple channels for circulating coolant (e.g., gaseous propellant) through the reflector assembly coolant passages and reactor core to extract heat energy from the reactor and recirculating that propellant to the fuel assemblies before being exhausted through the nozzle assembly. With this configuration, coolant can be provided to the reflector assembly without allocating valuable fuel assembly space to coolant channels. This construction also facilitates placing the reactor and nozzle in parallel with respect to the axial direction of the nozzle which further enhances the compact construction of the engine. In addition, the nozzle block, fuel assembly support and recuperator, which is provided to facilitate heat exchange from the reactor, form portions of the gamma shield, thereby reducing the weight impact of these elements on the rocket engine.
摘要翻译：核火箭发动机具有集成紧凑的结构，便于车辆尺寸和重量减轻。发动机包括具有多个燃料组件和设置在它们之间的调节杆的核反应堆堆芯。反应器容器围绕围绕芯的反射器组件，并且包括形成在其中的多个通道，用于使冷却剂循环通过。反应器容器被喷嘴组件包围，喷嘴组件包括具有流体耦合到燃料组件的出口的增压室和喷嘴喉部区域的喷嘴块。多个支柱从反应器容器延伸并且通过喷嘴喉部区域将该区域分成多个喷嘴喉部。每个支柱包括用于使冷却剂（例如，气体推进剂）循环通过反射器组件冷却剂通道和反应堆芯的多个通道，以从反应器提取热能，并且在通过喷嘴组件排出之前将该推进剂再循环到燃料组件。利用这种构造，可以向反射器组件提供冷却剂，而不向冷却剂通道分配有价值的燃料组件空间。这种结构还有助于将反应器和喷嘴相对于喷嘴的轴向平行放置，这进一步增强了发动机的紧凑结构。此外，提供用于促进从反应器的热交换的喷嘴块，燃料组件支撑件和换热器形成伽马护罩的部分，从而减少这些元件对火箭发动机的重量影响。

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