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1. 发明授权

US08127443B2 Method of fabricating a rocket engine nozzle using pressure brazing 有权
标题翻译：使用压力钎焊制造火箭发动机喷嘴的方法
公开(公告)号：US08127443B2
公开(公告)日：2012-03-06
申请号：US12271920
申请日：2008-11-16
申请人： Jeffry A. Fint , Michael B. Hankins , Myron L. Jew , Donald G. Ulmer , Brian L. Wherley , William D. Romine , Frederick M. Kuck , Douglas S. Ades
发明人： Jeffry A. Fint , Michael B. Hankins , Myron L. Jew , Donald G. Ulmer , Brian L. Wherley , William D. Romine , Frederick M. Kuck , Douglas S. Ades
IPC分类号： B21K25/00 , F02K9/00
CPC分类号： F02K9/972 , F02K9/97 , F05D2230/237 , Y10S29/004 , Y10T29/49323 , Y10T29/49346 , Y10T29/49432
摘要： A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.
摘要翻译：使用压力钎焊制造火箭发动机喷嘴组件的方法通常包括首先将火箭发动机喷嘴衬套组装到用于火箭发动机喷嘴组件的火箭发动机喷嘴护套中。然后可以密封火箭发动机喷嘴组件。在对火箭发动机喷嘴组件进行压力钎焊之前，可以确定压力钎焊参数。压力钎焊可以用确定的压力钎焊参数进行，以完成火箭发动机喷嘴的制造。火箭发动机喷嘴组件可以包括火箭发动机喷嘴护套和具有多个通道的火箭发动机喷嘴衬套，每个通道之间的空间限定了一个平台，而火箭发动机喷嘴衬套具有至少一对端部，结束。火箭发动机喷嘴衬套通过端部粘合到火箭发动机喷嘴护套上，端部被接合到喷嘴护套，并且焊盘被压焊到喷嘴护套上。

2. 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。

3. 发明申请

US20090100678A1 ROCKET ENGINE NOZZLE AND METHOD OF FABRICATING A ROCKET ENGINE NOZZLE USING PRESSURE BRAZING 有权
标题翻译：摇头发动机喷嘴及使用压力制动器制造发动机喷嘴的方法
公开(公告)号：US20090100678A1
公开(公告)日：2009-04-23
申请号：US12271920
申请日：2008-11-16
申请人： Jeffry A. Fint , Michael B. Hankins , Myron L. Jew , Donald G. Ulmer , Brian L. Wherley , William D. Romine , Frederick M. Kuck , Douglas S. Ades
发明人： Jeffry A. Fint , Michael B. Hankins , Myron L. Jew , Donald G. Ulmer , Brian L. Wherley , William D. Romine , Frederick M. Kuck , Douglas S. Ades
IPC分类号： B23P15/00 , F02K1/00
CPC分类号： F02K9/972 , F02K9/97 , F05D2230/237 , Y10S29/004 , Y10T29/49323 , Y10T29/49346 , Y10T29/49432
摘要： A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.
摘要翻译：使用压力钎焊制造火箭发动机喷嘴组件的方法通常包括首先将火箭发动机喷嘴衬套组装到用于火箭发动机喷嘴组件的火箭发动机喷嘴护套中。然后可以密封火箭发动机喷嘴组件。在对火箭发动机喷嘴组件进行压力钎焊之前，可以确定压力钎焊参数。压力钎焊可以用确定的压力钎焊参数进行，以完成火箭发动机喷嘴的制造。火箭发动机喷嘴组件可以包括火箭发动机喷嘴护套和具有多个通道的火箭发动机喷嘴衬套，每个通道之间的空间限定了一个平台，而火箭发动机喷嘴衬套具有至少一对端部，结束。火箭发动机喷嘴衬套通过端部粘合到火箭发动机喷嘴护套上，端部被接合到喷嘴护套，并且焊盘被压焊到喷嘴护套上。

4. 发明授权

US07306710B2 Apparatus and method for electroplating a metallic film on a rocket engine combustion chamber component 有权
标题翻译：在火箭发动机燃烧室部件上电镀金属膜的装置和方法
公开(公告)号：US07306710B2
公开(公告)日：2007-12-11
申请号：US10290723
申请日：2002-11-08
申请人： Chad M. Schepel , Jeffry A. Fint , Steve J. Evans , Cecil E. Flowers
发明人： Chad M. Schepel , Jeffry A. Fint , Steve J. Evans , Cecil E. Flowers
IPC分类号： C25D5/00 , C25D5/02
CPC分类号： C25D7/00 , C25D5/04
摘要： A tank is utilized for containing a plating solution. A rotatable support assembly rotatably supports a combustion chamber component relative to the tank for providing partial immersion of the combustion chamber component within the plating solution. An anode is positioned within the tank proximate a surface of the combustion chamber component to be electroplated. A current source is connected to the anode and in electrical contact with the combustion chamber component. When the combustion chamber component is rotated, the submerged portions are deposited with metal from the plating solution.
摘要翻译：罐用于容纳电镀溶液。可旋转的支撑组件可旋转地支撑相对于罐的燃烧室部件，用于将燃烧室部件局部浸没在镀液中。阳极被定位在靠近待电镀的燃烧室部件表面的槽内。电流源连接到阳极并与燃烧室部件电接触。当燃烧室部件旋转时，浸没的部分从镀液中以金属沉积。

5. 发明授权

US07596940B2 Rocket engine nozzle and method of fabricating a rocket engine nozzle using pressure brazing 失效
标题翻译：火箭发动机喷嘴和使用压力钎焊制造火箭发动机喷嘴的方法
公开(公告)号：US07596940B2
公开(公告)日：2009-10-06
申请号：US11086084
申请日：2005-03-22
申请人： Jeffry A. Fint , Michael B. Hankins , Myron L. Jew , Donald G. Ulmer , Brian L. Wherley , William D. Romine , Frederick M. Kuck , Douglas S. Ades
发明人： Jeffry A. Fint , Michael B. Hankins , Myron L. Jew , Donald G. Ulmer , Brian L. Wherley , William D. Romine , Frederick M. Kuck , Douglas S. Ades
IPC分类号： F02K9/00
CPC分类号： F02K9/972 , F02K9/97 , F05D2230/237 , Y10S29/004 , Y10T29/49323 , Y10T29/49346 , Y10T29/49432
摘要： A method of fabrication of a rocket engine nozzle assembly using pressure brazing generally includes initially assembling a rocket engine nozzle liner into a rocket engine nozzle jacket for a rocket engine nozzle assembly. The rocket engine nozzle assembly may then be sealed. Prior to pressure brazing the rocket engine nozzle assembly, pressure brazing parameters may be determined. The pressure brazing may be performed with the determined pressure brazing parameters to complete the fabrication of the rocket engine nozzle. The rocket engine nozzle assembly may include a rocket engine nozzle jacket and a rocket engine nozzle liner having a plurality of channels, with the space between each channel defining a land, and the rocket engine nozzle liner having at least a pair of endlands disposed at each end thereof. The rocket engine nozzle liner is bonded to the rocket engine nozzle jacket by the endlands being bonded to the nozzle jacket and the lands being pressure brazed to the nozzle jacket.
摘要翻译：使用压力钎焊制造火箭发动机喷嘴组件的方法通常包括首先将火箭发动机喷嘴衬套组装到用于火箭发动机喷嘴组件的火箭发动机喷嘴护套中。然后可以密封火箭发动机喷嘴组件。在对火箭发动机喷嘴组件进行压力钎焊之前，可以确定压力钎焊参数。压力钎焊可以用确定的压力钎焊参数进行，以完成火箭发动机喷嘴的制造。火箭发动机喷嘴组件可以包括火箭发动机喷嘴护套和具有多个通道的火箭发动机喷嘴衬套，每个通道之间的空间限定了一个平台，而火箭发动机喷嘴衬套具有至少一对端部，结束。火箭发动机喷嘴衬套通过端部粘合到火箭发动机喷嘴护套上，端部被接合到喷嘴护套，并且焊盘被压焊到喷嘴护套上。

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