公开(公告)号：US06582160B2

公开(公告)日：2003-06-24

申请号：US09876448

申请日：2001-06-07

申请人： Eddie W. Campbell ,  Thomas J. Mueller

发明人： Eddie W. Campbell ,  Thomas J. Mueller

IPC分类号： B65G5346

CPC分类号： B65G53/10 ,  B65D90/623

摘要： The hopper tee provides increased material flow rates and includes a first hollow pipe section having an upper end and an opposite lower end, the upper end including an inlet opening for connecting to a discharge opening of a hopper for receiving material contained in the hopper therethrough, and an interior cylindrical side wall forming an internal passage connecting the inlet opening to the lower end for flow of the material thereto. The hopper tee includes a second hollow pipe section having a first open end, an opposite second open end, an intermediate portion therebetween, and an interior cylindrical side wall forming an internal passage connecting the first and second open ends providing a flow path for a flow of air therethrough, the lower end of the first hollow pipe section being connected to the intermediate portion of the second hollow pipe section forming a material inlet port connecting the internal passage of the first hollow pipe section to the internal passage of the second hollow pipe section for flow of the material into the flow path. The hopper tee further includes an element or flow director disposed in the internal passage of the second hollow pipe section having a surface protruding from the cylindrical side wall thereof into the flow path and oriented at an acute angle with respect to a cylinder axis of the side wall, for directing a portion of the flow of air adjacent to the material inlet port away from the port at an increased velocity for inducing the flow of the material through the port into the flow path.

公开(公告)号：US07503511B2

公开(公告)日：2009-03-17

申请号：US11198053

申请日：2005-08-04

申请人： Thomas J. Mueller

发明人： Thomas J. Mueller

IPC分类号： B05B7/10 ,  B05B7/04

CPC分类号： F02K9/52 ,  F23L7/007 ,  F23L2900/07004 ,  Y02E20/344

摘要： A bi-propellant rocket engine may include a primary propellant flowing in a central passageway, a secondary propellant flowing in a secondary passageway generally coaxial with central passageway and a pintle tip having a central chamber sidewall coaxial with the primary passageway and surrounding a central chamber, the central chamber sidewall having a first plurality of apertures there through so that some of the primary propellant exits the central chamber transverse to the flow of the secondary propellant in the secondary passageway. The pintle tip may have a secondary chamber sidewall, substantially thicker than the primary chamber sidewall, surrounding a secondary chamber downstream of and in fluid communication with the primary chamber, the secondary chamber sidewall having a second plurality of apertures there through so that some of the primary propellant exits the secondary chamber transverse to the flow of the secondary propellant in the secondary passageway. The pintle tip may have an end wall generally traverse to the flow of the primary propellant in the central passageway and adjacent the secondary chamber sidewall so that the flow of primary propellant through the secondary chamber sidewall cools a downstream face of the end wall during combustion of the mixed propellants adjacent the downstream face of the end wall. The pintle tip may be used for mixing a first liquid with a second liquid.

公开(公告)号：US06591603B2

公开(公告)日：2003-07-15

申请号：US09802002

申请日：2001-03-08

申请人： Gordon A. Dressler ,  Thomas J. Mueller ,  Scott J. Rotenberger

发明人： Gordon A. Dressler ,  Thomas J. Mueller ,  Scott J. Rotenberger

IPC分类号： B64C1502

CPC分类号： F02K9/52 ,  F02K9/972

摘要： The present invention provides a rocket engine (10) that is self-compensating on nozzle thrust coefficient for varying ambient backpressures. The rocket engine (10) includes a combustion chamber (12) having an injector end (14) and a nozzle end (16). A propellant injector (20) is in fluid communication between a propellant line and an inside periphery of the combustion chamber injector end (14). A nozzle throat (18) is formed at the nozzle end (14) of the combustion chamber (12). A nozzle exit cone (22) extends outwardly from the nozzle throat (18). A plug support (30) is coupled between a nozzle plug (28) and the propellant injector (20). The nozzle plug (28) aerodynamically self-compensates for changes in ambient backpressure at the nozzle exit cone (22) such that the nozzle thrust coefficient is maximized for any ambient backpressure.

摘要翻译： 本发明提供了一种火箭发动机（10），其对于改变环境背压的喷嘴推力系数进行自补偿。 火箭发动机（10）包括具有喷射器端（14）和喷嘴端（16）的燃烧室（12）。 推进剂喷射器（20）在推进剂管线和燃烧室喷射器端部（14）的内周边之间流体连通。 在燃烧室（12）的喷嘴端（14）处形成喷嘴喉（18）。 喷嘴出口锥体（22）从喷嘴喉部（18）向外延伸。 插头支撑件（30）联接在喷嘴塞（28）和推进剂喷射器（20）之间。 喷嘴塞（28）在空气动力学上自我补偿喷嘴出口锥体（22）处的环境背压的变化，使得喷嘴推力系数对于任何环境背压最大化。

公开(公告)号：US5720451A

公开(公告)日：1998-02-24

申请号：US574505

申请日：1995-12-19

申请人： Melvin L. Chazen ,  Thomas J. Mueller ,  William D. Kruse

发明人： Melvin L. Chazen ,  Thomas J. Mueller ,  William D. Kruse

IPC分类号： F02K9/62 ,  B32B15/00

CPC分类号： F02K9/62 ,  F05D2300/15 ,  Y10T428/12458

摘要： A high temperature thrust chamber for spacecraft (20) is provided herein. The high temperature thrust chamber comprises a hollow body member (12) having an outer surface and an internal surface (16) defining the high temperature chamber (10). The body member (12) is made substantially of rhenium. An alloy (18) consisting of iridium and at least alloying metal selected of the group consisting of rhodium, platinum and palladium is deposited on at least a portion of the internal surface (16) of the body member (12). The iridium and the alloying metal are electrodeposited onto the body member (12). A HIP cycle is performed upon the body member (12) to cause the coating of iridium and the alloying metal to form the alloy (18) which protects the body member (12) from oxidation.

摘要翻译： 本文提供了一种用于航天器（20）的高温推力室。 高温推进室包括具有外表面的中空本体构件（12）和限定高温室（10）的内表面（16）。 主体构件（12）基本上由铼制成。 由铱和至少选自铑，铂和钯的合金金属的合金（18）沉积在主体部件（12）的内表面（16）的至少一部分上。 铱和合金金属电沉积到主体部件（12）上。 对本体构件（12）进行HIP循环，以使铱和合金金属的涂层形成保护体部件（12）免受氧化的合金（18）。

公开(公告)号：US20090007543A1

公开(公告)日：2009-01-08

申请号：US11198053

申请日：2005-08-04

申请人： Thomas J. Mueller

发明人： Thomas J. Mueller

IPC分类号： F02K9/52 ,  B05B7/04 ,  B05B1/24

CPC分类号： F02K9/52 ,  F23L7/007 ,  F23L2900/07004 ,  Y02E20/344

摘要： A bi-propellant rocket engine may include a primary propellant flowing in a central passageway, a secondary propellant flowing in a secondary passageway generally coaxial with central passageway and a pintle tip having a central chamber sidewall coaxial with the primary passageway and surrounding a central chamber, the central chamber sidewall having a first plurality of apertures there through so that some of the primary propellant exits the central chamber transverse to the flow of the secondary propellant in the secondary passageway. The pintle tip may have a secondary chamber sidewall, substantially thicker than the primary chamber sidewall, surrounding a secondary chamber downstream of and in fluid communication with the primary chamber, the secondary chamber sidewall having a second plurality of apertures there through so that some of the primary propellant exits the secondary chamber transverse to the flow of the secondary propellant in the secondary passageway. The pintle tip may have an end wall generally traverse to the flow of the primary propellant in the central passageway and adjacent the secondary chamber sidewall so that the flow of primary propellant through the secondary chamber sidewall cools a downstream face of the end wall during combustion of the mixed propellants adjacent the downstream face of the end wall. The pintle tip may be used for mixing a first liquid with a second liquid.

摘要翻译： 双推进剂火箭发动机可以包括在中心通道中流动的主推进剂，在与中心通道大致同轴的次级通道中流动的次级推进剂和具有与主通道同轴并围绕中心室的中心室侧壁的枢轴端头， 中央室侧壁具有第一多个孔，通过这些孔，使得一些主推进剂在第二通道中横向于二次推进剂的流动而离开中心室。 枢轴端部可以具有基本上比主室侧壁更厚的次级室侧壁，围绕主室的下游并与主室流体连通，次级室侧壁具有穿过第二多个孔的部分， 主推进剂在第二通道中离开辅助室横向于二次推进剂的流动。 枢轴端头可以具有通常在中心通道中并且邻近次级室侧壁的主推进剂流动的端壁，使得通过次级室侧壁的初级推进剂的流动在端壁的燃烧期间冷却端壁的下游面 混合的推进剂邻近端壁的下游面。 针尖可用于将第一液体与第二液体混合。

公开(公告)号：US06655127B2

公开(公告)日：2003-12-02

申请号：US10328909

申请日：2002-12-24

申请人： William D. Kruse ,  Thomas J. Mueller ,  John J. Weede

发明人： William D. Kruse ,  Thomas J. Mueller ,  John J. Weede

IPC分类号： F02K948

CPC分类号： F02K9/48

摘要： A method is provided for using high concentrations of hydrogen peroxide to drive a turbine (20′) in a turbopump fed rocket engine (12′). The method includes the steps of: (a) receiving fuel into a fuel rich pre-burner (50); (b) receiving high concentrations of hydrogen peroxide into the pre-burner (50); (c) converting the fuel and hydrogen peroxide into a fuel rich gas; and (d) passing the fuel rich gas through a turbine (20′), thereby using high concentrations of hydrogen peroxide to drive the turbine. Thus, by utilizing a fuel rich pre-burner (50) that operates at a very low mixture ratio, the drive gas for a turbine (20′) can be maintained at moderate temperature levels.

摘要翻译： 提供了一种使用高浓度的过氧化氢来驱动涡轮泵送入火箭发动机（12'）中的涡轮机（20'）的方法。 该方法包括以下步骤：（a）将燃料接收到富燃料预燃烧器（50）中; （b）将高浓度的过氧化氢接收到预燃烧器（50）中; （c）将燃料和过氧化氢转化为富燃气体; 和（d）使富燃气体通过涡轮机（20'），由此使用高浓度的过氧化氢来驱动涡轮机。 因此，通过利用以非常低的混合比操作的富燃料预燃烧器（50），用于涡轮（20'）的驱动气体可以保持在中等温度水平。

公开(公告)号：US06505463B2

公开(公告)日：2003-01-14

申请号：US09761957

申请日：2001-01-17

申请人： William D. Kruse ,  Thomas J. Mueller ,  John J. Weede

发明人： William D. Kruse ,  Thomas J. Mueller ,  John J. Weede

IPC分类号： F02K948

CPC分类号： F02K9/48

摘要： A method is provided for using high concentrations of hydrogen peroxide to drive a turbine (20′) in a turbopump fed rocket engine (12′). The method includes the steps of: (a) receiving fuel into a fuel rich pre-burner (50); (b) receiving high concentrations of hydrogen peroxide into the pre-burner (50); (c) converting the fuel and hydrogen peroxide into a fuel rich gas; and (d) passing the fuel rich gas through a turbine (20′), thereby using high concentrations of hydrogen peroxide to drive the turbine. Thus, by utilizing a fuel rich pre-burner (50) that operates at a very low mixture ratio, the drive gas for a turbine (20′) can be maintained at moderate temperature levels.

摘要翻译： 提供了一种使用高浓度的过氧化氢来驱动涡轮泵送入火箭发动机（12'）中的涡轮机（20'）的方法。 该方法包括以下步骤：（a）将燃料接收到富燃料预燃烧器（50）中; （b）将高浓度的过氧化氢接收到预燃烧器（50）中; （c）将燃料和过氧化氢转化为富燃气体; 和（d）使富燃气体通过涡轮机（20'），由此使用高浓度的过氧化氢来驱动涡轮机。 因此，通过利用以非常低的混合比操作的富燃料预燃烧器（50），用于涡轮（20'）的驱动气体可以保持在中等温度水平。

公开(公告)号：US5855456A

公开(公告)日：1999-01-05

申请号：US732600

申请日：1996-10-16

申请人： Thomas J. Mueller

发明人： Thomas J. Mueller

IPC分类号： B65G53/52 ,  B65G51/02

CPC分类号： B65G53/525

摘要： A bulk material conveying system for use with a bulk material holding tank having at least one outlet. The conveying system includes a main supply line for carrying pressurized gas and a material conveying line having an inlet and an outlet. The material conveying line is in communication with the holding tank outlet for transporting the bulk material from the holding tank to the conveying line outlet. The inlet of the material conveying line is in communication with the main supply line for receiving the pressurized gas whereby the gas moves the bulk material in the conveying line towards the conveying line outlet. The system further includes an aerator line having an inlet and an outlet and at least one connector for feeding the pressurized gas into the bulk material holding tank to agitate the bulk material and push it towards the holding tank outlet and a pressure sensor for sensing when the pressure in the material conveying line exceeds a predetermined level. A shut-off valve is connected to the main supply line for establishing communication between the main supply line and the aerator line and operable in response to the pressure sensor sensing the exceeding of pressure for shutting off flow of the pressurized gas from the main supply line to the aerator line thereby increasing gas flow to the material conveying line for eliminating buildup of bulk material in the material conveying line.

摘要翻译： 一种用于与具有至少一个出口的散装材料容纳箱一起使用的散装物料输送系统。 输送系统包括用于承载加压气体的主供应管线和具有入口和出口的材料输送管线。 物料输送管线与储存罐出口连通，用于将散装材料从储存罐输送到输送管线出口。 物料输送线的入口与用于接收加压气体的主供应管路连通，由此气体将输送线路中的散装材料移动到输送线出口。 该系统还包括具有入口和出口的充气器管线和至少一个连接器，用于将加压气体进入散装材料容纳槽以搅拌散装材料并将其推向储存箱出口;以及压力传感器，用于感测何时 材料输送线中的压力超过预定水平。 关闭阀连接到主供应管线，用于建立主供应管线和曝气器管线之间的连通，并且响应于压力传感器可操作以感测到超过压力以关闭来自主供应管线的加压气体的流动 从而增加到材料输送线的气流，以消除材料输送线中散装材料的堆积。

公开(公告)号：US5641963A

公开(公告)日：1997-06-24

申请号：US536151

申请日：1995-09-29

申请人： Thomas J. Mueller

发明人： Thomas J. Mueller

IPC分类号： G08B13/193 ,  G01J5/10

CPC分类号： G08B13/193

摘要： An improved IR detector system is described which uses a plurality of IR detection modules coupled to a central computer to determine the location of an intrusion to the system. Each IR detection module has a plurality of optically isolated lens and detector pairs arranged in an arcuate array coupled to a local microprocessor chip which is unique to that module such that each lens and detector pair produces a response to a sensed intrusion along a particular radial of the array's arc to allow the local microprocessor to produce a coded signal to the central computer which corresponds to the direction of the sensed intrusion. Using a triangulation algorithm, the central computer combines the coded signals from whichever of the plurality of IR detection modules are active to compute the location of the intrusion.

摘要翻译： 描述了一种改进的IR检测器系统，其使用耦合到中央计算机的多个IR检测模块来确定入侵到系统的位置。 每个IR检测模块具有多个光学隔离的透镜和检测器对，其布置成耦合到本地微处理器芯片的弓形阵列，该阵列对该模块是唯一的，使得每个透镜和检测器对产生对沿着特定径向的感测入侵的响应 该阵列的弧线允许本地微处理器产生对应于感测入侵方向的中央计算机的编码信号。 使用三角测量算法，中央计算机将来自多个IR检测模块中的哪一个的编码信号组合起来，以计算入侵的位置。