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61. 发明授权

US06907662B2 Method for manufacturing outlet nozzles for rocket engines 有权
标题翻译：制造火箭发动机出口喷嘴的方法
公开(公告)号：US06907662B2
公开(公告)日：2005-06-21
申请号：US10370536
申请日：2003-02-20
申请人： Jan Lundgren
发明人： Jan Lundgren
IPC分类号： B23K26/00 , B23K26/20 , B23K26/24 , B23K26/28 , F02K9/64 , F02K9/97 , B21D53/00 , F02K1/00
CPC分类号： F02K9/972 , B23K26/24 , B23K26/282 , B23K2101/045 , B23K2101/14 , B23K2101/18 , Y10T29/49346 , Y10T29/49995
摘要： Methods for manufacturing outlet nozzles for use in rocket motors are disclosed. The methods include providing an inner wall, positioning an outer wall around the inner wall, positioning spacers in the space between the inner and outer walls, and laser welding between the spacers and at least one of the inner and outer walls in order to form cooling ducts between the spacers and to provide T-shaped joints between the spacers and at least one of the inner and outer walls, the T-shaped joints including a rounded shape within the cooling ducts.
摘要翻译：公开了用于制造用于火箭发动机的出口喷嘴的方法。所述方法包括提供内壁，围绕内壁定位外壁，将间隔件定位在内壁和外壁之间的空间中，以及在间隔件与内壁和外壁中的至少一个之间的激光焊接以形成冷却并且在间隔件和内壁和外壁中的至少一个之间提供T形接头，T形接头在冷却管道内包括圆形形状。

62. 发明申请

US20050045306A1 Transpiration cooling system 有权
标题翻译：蒸腾冷却系统
公开(公告)号：US20050045306A1
公开(公告)日：2005-03-03
申请号：US10624908
申请日：2003-07-22
申请人： Miklos Petervary , Kevin Lohner
发明人： Miklos Petervary , Kevin Lohner
IPC分类号： B64C1/38 , B64C3/36 , B64G1/58 , F01D5/18 , F01D25/12 , F02K1/82 , F02K9/40 , F02K9/64 , F04D29/38 , F04D29/58 , F23R3/00 , F28F7/00
CPC分类号： F01D5/184 , B64C1/38 , B64G1/401 , B64G1/58 , F01D25/12 , F02K1/825 , F02K9/64 , F02K9/972 , F05D2250/323 , F23R3/002 , F23R3/007 , F23R2900/03041 , F28D2021/0078 , F28F13/003 , F42B15/34 , Y02T50/43
摘要： A system for cooling a structure or mechanism through transpiration processes. Generally a porous structural material may be used to form a hot wall surface of a high temperature or high heat flux environment component, typically used in combustion type devices. Coolant pressurized on the “cold” or cooler side of the wall is bled, “sweated”, or otherwise transpired to the “hot” wall surface in an effort to control the hot wall surface temperature by shielding the surface with a coolant layer at the surface and by removing heat via coolant flow past the surface. This may be done to manage the hot wall temperature for structural purposes, more effectively manage high heat fluxes, or to hide thermal signatures. The porous material can be selectively made such that the coolant material flows substantially in one direction only through the porous material to transfer thermal energy only away from the structure rather than towards the structure.
摘要翻译：一种通过蒸腾过程冷却结构或机制的系统。通常，多孔结构材料可用于形成通常用于燃烧型装置的高温或高热通量环境组分的热壁表面。在壁的“冷”或冷却器侧加压的冷却剂被排出，“出汗”或以其他方式蒸发到“热”壁表面，以通过在该表面上冷却表面屏蔽冷却剂层来控制热壁表面温度通过冷却液流过表面除去热量。这可以用于管理结构目的的热壁温度，更有效地管理高热通量或隐藏热特征。可以选择性地制造多孔材料，使得冷却剂材料仅通过多孔材料基本上在一个方向上流动，以将热能仅偏离结构而不是结构。

63. 发明授权

US06829884B2 Rocket engine combustion chamber having multiple conformal throat supports 失效
标题翻译：火箭发动机燃烧室具有多个保形喉支撑
公开(公告)号：US06829884B2
公开(公告)日：2004-12-14
申请号：US10299423
申请日：2002-11-19
申请人： Jeffry A. Fint , Douglas S. Ades , Michael B. Hankins , Maynard L. Stangeland
发明人： Jeffry A. Fint , Douglas S. Ades , Michael B. Hankins , Maynard L. Stangeland
IPC分类号： F02K1100
CPC分类号： B23P15/008 , F02K9/64 , F02K9/972 , F05D2230/60 , Y10T29/49346
摘要： In a first assembly step a coolant liner is formed having an outside surface. A plurality of coolant channels are formed on the outside surface. At least two inner conformal throat support sections and at least two outer conformal throat support sections are formed. The two inner conformal throat support sections are formed around the outside surface of the coolant liner to form a closed inner conformal throat outside surface. The inner conformal throat support sections are joined at inner throat seam lines. At least two outer conformal throat support sections are assembled around the closed inner conformal throat outside surface so as to cover the inner throat seam lines, to form a liner throat support assembly. An inlet manifold and an outlet manifold are assembled around the liner throat support assembly to form a hot isostatic press (HIP) assembly. A HIP'ed assembly is formed by HIP'ing the HIP assembly.
摘要翻译：在第一组装步骤中，形成具有外表面的冷却剂衬套。多个冷却剂通道形成在外表面上。形成至少两个内共形喉部支撑部分和至少两个外共形喉部支撑部分。两个内共形喉部支撑部分围绕冷却剂衬套的外表面形成，以形成封闭的内部共形喉部外表面。内部共形喉部支撑部分在内部喉部接缝线处连接。至少两个外共形喉部支撑部分围绕封闭的内部共形喉部外表面组装以覆盖内部喉部接缝线，以形成衬套喉部支撑组件。入口歧管和出口歧管围绕衬套喉部支撑组件组装以形成热等静压机（HIP）组件。 HIP组装由HIP组装形成。

64. 发明申请

US20040168428A1 NOZZLE WITH SPIRAL INTERNAL COOLING CHANNELS 失效
标题翻译：带螺旋内部冷却通道的喷嘴
公开(公告)号：US20040168428A1
公开(公告)日：2004-09-02
申请号：US10308645
申请日：2002-12-02
申请人： Aerojet-General Corporation
发明人： Ross A. Hewitt
IPC分类号： F02K009/64
CPC分类号： F02K9/972 , F05D2210/40 , F05D2250/25 , F05D2260/20
摘要： A convergent-divergent rocket nozzle is formed by joining two coaxially aligned conical sections at a throat plane, each diverging outward from the throat plane. Coolant channels formed in the wall of the nozzle are arranged in spirals around the nozzle axis. Preferably, the conical sections are formed from platelet laminates rolled into conical form with a single spiral seam, and at least one of the conical sections is a composite of two or more component conical sections separately formed and then joined in a nested arrangement with the seams not superimposed. A further preferred construction is one in which the convergent end of one conical section is split radially into strips that are then spread apart to serve as bonding surfaces to bond to the other conical section.
摘要翻译：通过在喉部平面处连接两个同轴对准的锥形部分形成会聚发散火箭喷嘴，每个锥形部分从咽喉平面向外发散。形成在喷嘴壁上的冷却剂通道围绕喷嘴轴线螺旋地布置。优选地，锥形部分由具有单个螺旋接缝卷成圆锥形的片状层压体形成，并且至少一个锥形部分是分开形成的两个或更多个部件锥形部分的复合体，然后以嵌套的方式与接缝不叠加另一个优选的结构是一个圆锥形部分的会聚端部径向分开成条带，然后将其分开，以作为粘合表面以与另一个锥形部分结合。

65. 发明申请

US20040093852A1 Rocket engine combustion chamber having multiple conformal throat supports 失效
公开(公告)号：US20040093852A1
公开(公告)日：2004-05-20
申请号：US10299423
申请日：2002-11-19
发明人： Jeffry A. Fint , Douglas S. Ades , Michael B. Hankins , Maynard L. Stangeland
IPC分类号： F02K009/40
CPC分类号： B23P15/008 , F02K9/64 , F02K9/972 , F05D2230/60 , Y10T29/49346
摘要： In a first assembly step a coolant liner is formed having an outside surface. A plurality of coolant channels are formed on the outside surface. At least two inner conformal throat support sections and at least two outer conformal throat support sections are formed. The two inner conformal throat support sections are formed around the outside surface of the coolant liner to form a closed inner conformal throat outside surface. The inner conformal throat support sections are joined at inner throat seam lines. At least two outer conformal throat support sections are assembled around the closed inner conformal throat outside surface so as to cover the inner throat seam lines, to form a liner throat support assembly. An inlet manifold and an outlet manifold are assembled around the liner throat support assembly to form a hot isostatic press (HIP) assembly. A HIP'ed assembly is formed by HIP'ing the HIP assembly.

66. 发明申请

US20040010900A1 Method for forming a tube-walled article 失效
标题翻译：用于形成管壁制品的方法
公开(公告)号：US20040010900A1
公开(公告)日：2004-01-22
申请号：US10197039
申请日：2002-07-17
发明人： Mark David Horn
IPC分类号： B23P017/00
CPC分类号： G21B1/13 , B21D53/08 , F02K9/64 , F02K9/972 , Y02E30/128 , Y10T29/49346 , Y10T29/49805 , Y10T29/49879 , Y10T29/49908 , Y10T29/49938
摘要： A method for forming an article having a wall that is at least partially fabricated from tubing. The methodology employs a pressurized fluid to deform the tubing such that an outer surface of the tubing substantially conforms to a predetermined first wall configuration, an inner surface of the tubing substantially conforms to a predetermined second wall configuration and each of segment or loop of the tubing is substantially contiguous with at least one other segment or loop between the first and second surfaces.
摘要翻译：一种用于形成具有至少部分地由管制成的壁的制品的方法。该方法采用加压流体使管道变形，使得管道的外表面基本上符合预定的第一壁构造，管道的内表面基本上符合预定的第二壁构造，并且管道的每个段或环基本上与第一和第二表面之间的至少一个其它段或环相邻。

67. 发明申请

US20030183606A1 Method for manufacturing outlet nozzles for rocket engines 有权
公开(公告)号：US20030183606A1
公开(公告)日：2003-10-02
申请号：US10370536
申请日：2003-02-20
申请人： Volvo Aero Corporation
发明人： Jan Lundgren
IPC分类号： B23K026/00
CPC分类号： F02K9/972 , B23K26/24 , B23K26/282 , B23K2101/045 , B23K2101/14 , B23K2101/18 , Y10T29/49346 , Y10T29/49995
摘要： Methods for manufacturing outlet nozzles for use in rocket motors are disclosed. The methods include providing an inner wall, positioning an outer wall around the inner wall, positioning spacers in the space between the inner and outer walls, and laser welding between the spacers and at least one of the inner and outer walls in order to form cooling ducts between the spacers and to provide T-shaped joints between the spacers and at least one of the inner and outer walls, the T-shaped joints including a rounded shape within the cooling ducts.

68. 发明授权

US6062018A Pulse detonation electrical power generation apparatus with water injection 失效
标题翻译：脉冲爆震发电装置注水
公开(公告)号：US6062018A
公开(公告)日：2000-05-16
申请号：US646022
申请日：1996-05-07
申请人： Thomas R. A. Bussing
发明人： Thomas R. A. Bussing
IPC分类号： B01J3/08 , C23C4/12 , F01D5/28 , F02C5/02 , F02K7/06 , F02K7/075 , F02K9/97
CPC分类号： B01J3/08 , C23C4/126 , F01D5/288 , F02C5/02 , F02K7/06 , F02K7/075 , F02K9/972 , F02K9/974 , F23R7/00
摘要： A pulse detonation power generation apparatus is provided. This apparatus is provided with a detonation chamber connected to fuel and air sources which detonate to produce energy which may be converted to electrical energy. The pulse detonation energy generator may have one or more detonation chambers, each having an inlet end and an outlet end; a fuel manifold for supplying fuel from a fuel source to said generator; an air manifold for supplying air to said generator; a pre-mixer operatively connected to said fuel manifold, air manifold, and the inlet end of said one or more detonation chambers; an impingement ring disposed along an internal wall of said pre-mixer; a disk valve positioned between the pre-mixer and the air manifold; a predetonator for initiating detonation in said detonation chambers; a rotary valve for pulse feeding an oxidizer or fuel to the predetonator; means for injecting liquid water or steam into combustion products produced in said detonation chambers; and means for converting the energy generated by a detonation in said detonation chambers into electrical energy.
摘要翻译：提供脉冲爆震发电装置。该装置设置有连接到燃料和空气源的爆炸室，其引爆以产生可转换成电能的能量。脉冲爆震能量发生器可以具有一个或多个引爆室，每个具有入口端和出口端; 燃料歧管，用于从燃料源向所述发电机提供燃料; 用于向所述发生器供应空气的空气歧管; 可操作地连接到所述燃料歧管，空气歧管和所述一个或多个引爆室的入口端的预混合器; 沿着所述预混合器的内壁设置的冲击环; 位于预混合器和空气歧管之间的盘阀; 用于在所述爆震室中起爆的预引爆器; 旋转阀，用于将氧化剂或燃料脉冲馈送到预灭火器; 用于将液态水或蒸汽注入在所述爆炸室中产生的燃烧产物中的装置; 以及用于将由所述爆震室中的爆震产生的能量转换为电能的装置。

69. 发明授权

US5855827A Pulse detonation synthesis 失效
标题翻译：脉冲爆震综合
公开(公告)号：US5855827A
公开(公告)日：1999-01-05
申请号：US613194
申请日：1996-03-08
申请人： Thomas R. A. Bussing , Joseph M. Ting
发明人： Thomas R. A. Bussing , Joseph M. Ting
IPC分类号： B01J3/08 , B05B7/00 , C23C4/12 , F01D5/28 , F02K7/06 , F02K7/075 , F02K9/97 , B29B9/00 , B05D1/36
CPC分类号： B01J3/08 , B05B7/0006 , C23C4/126 , F01D5/288 , F02K7/06 , F02K7/075 , F02K9/972 , F02K9/974
摘要： A Pulse Detonation Synthesis (PDS) process for the manufacture and deposition of ceramic powders and coatings is disclosed. PDS may use multiple detonation pulses that are initiated in a reaction chamber to synthesize ceramic materials from reactants introduced into the chamber. The reactants may be provided in the form of divided solids, gases, liquids, gels, and/or mixtures of the foregoing. The synthesized ceramic materials may take the form of micron and/or nano-scale powders or coatings. Non-coating powders may be collected for later use. The coatings produced by the present invention include, but are not limited to, gradient coatings, uniform coatings, thermal barrier coatings, and other commercially useful coatings.
摘要翻译：公开了用于制造和沉积陶瓷粉末和涂层的脉冲爆震合成（PDS）方法。 PDS可以使用在反应室中引发的多个引爆脉冲，以从引入室中的反应物合成陶瓷材料。反应物可以以分开的固体，气体，液体，凝胶和/或前述物质的混合物的形式提供。合成的陶瓷材料可以采取微米和/或纳米级粉末或涂层的形式。可以收集非涂层粉末供以后使用。由本发明生产的涂层包括但不限于梯度涂层，均匀涂层，热障涂层和其它商业上有用的涂层。

70. 发明授权

US5645127A Coolant supply arrangement for jet engine turbine walls 失效
标题翻译：喷气发动机涡轮机壁的冷却液供应装置
公开(公告)号：US5645127A
公开(公告)日：1997-07-08
申请号：US240585
申请日：1994-05-09
申请人： Heinrich Enderle , Achim Ottenstein
发明人： Heinrich Enderle , Achim Ottenstein
IPC分类号： F02C7/16 , F02K1/82 , F02K7/16 , F02K7/18 , F02K9/64 , F02K9/78 , F02K9/97 , F23R3/00 , F28F3/12 , F28F9/02 , F28F9/18 , F28D7/06
CPC分类号： F02K1/822 , F02K9/972 , F23R3/002 , F28F3/12 , F28F9/0243 , F28F9/18 , F28F2009/0297
摘要： An arrangement is disclosed for distributing and supplying and removing a coolant to and from a wall of a turbine engine, in particular a turbine dynamic jet engine, which is subjected to the flow of a hot fluid and has cooling channels which can be acted upon by the coolant and which are arranged substantially parallel to one another in the wall. The arrangement includes tube guides which are spatially separated from one another and connected to the wall, a casing of each tube guide having a longitudinal slot, each tube guide being attached on an inlet or outlet side to the respective cooling channels by way of the longitudinal slot and apertures in the wall, and a soldering or welded seam connecting the tube guides to the wall along the respective longitudinal slot.
摘要翻译：公开了用于将涡轮发动机，特别是涡轮机动力喷气发动机的壁分配和供给和从其中移出冷却剂的布置，涡轮机动力喷气发动机经受热流体的流动，并且具有能够被冷却剂并且其在壁中彼此基本平行地布置。该装置包括在空间上彼此分离并连接到壁的管引导件，每个管引导件的壳体具有纵向狭槽，每个管引导件通过纵向方向附接到相应的冷却通道的入口侧或出口侧壁上的槽和孔，以及沿着相应的纵向槽将管引导件连接到壁的焊接或焊缝。

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