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    Method for producing multilayer thin-walled bellows
    3.
    发明授权
    Method for producing multilayer thin-walled bellows 有权
    生产多层薄壁波纹管的方法

    公开(公告)号：US06202281B1

    公开(公告)日：2001-03-20

    申请号：US09391192

    申请日：1999-09-07

    申请人： Viktor Nikonorovich Semenov ,  Alexandr Konstantinovich Tretiakov ,  Gennady Grigorievich Derkach ,  Vladimir Konstantinovich Chvanov ,  Jury Vasilievich Movchan ,  Mikhail Ivanovich Zykov ,  Valentin Georgievich Polushin

    发明人： Viktor Nikonorovich Semenov ,  Alexandr Konstantinovich Tretiakov ,  Gennady Grigorievich Derkach ,  Vladimir Konstantinovich Chvanov ,  Jury Vasilievich Movchan ,  Mikhail Ivanovich Zykov ,  Valentin Georgievich Polushin

    IPC分类号： B23P1904

    CPC分类号： B21D15/06 ,  B21C37/09 ,  B21C37/154 ,  B21C37/20 ,  Y10T29/49877

    摘要： A method includes the round billet skelping, several runs of each round billet drawing up to a given size, packing the drawn billets into a multilayer bank, corrugating the bank with the bellows formation as a result and its heat treatment. Each round billet is skelped of the age-hardenable nickel alloy containing components of the following group: niobium, aluminum, titanium, tungsten and molybdenum. Each round billet is drawn, heated up to the temperature of 1000-1130° C., held in the shielding medium at the above temperature, and cooled down, after that the above operations of drawing, heating, holding and cooling are repeated until the given size of each round billet is reached. The drawn round billets are packed into the multilayer bank and the bank is corrugated for forming the multilayer bellows. The heat treatment of the bellows is made by its heating up to the temperature of 1000-1130° C., holding in the shielding medium at this temperature until the strengthening phase is completely dissolved in the alloy and subsequent cooling down to the temperature of the phase transition termination in the alloy. A rarefied air medium or argon are used as the shielding medium.

    摘要翻译： 一种方法包括圆坯坯，每个圆坯坯的拉伸达到给定尺寸的几个运行，将拉制的坯料包装成多层板，结果使波纹管形成波纹，并进行热处理。 每个圆形坯料都是含有下列组分的成分的老化硬化镍合金：铌，铝，钛，钨和钼。 每个圆钢坯被拉伸，加热至1000-1130℃的温度，在上述温度下保持在屏蔽介质中，并冷却，之后重复上述拉伸，加热，保持和冷却操作直到 给定每个圆形钢坯的尺寸。 拉制的圆形坯料被包装在多层板中，并且波纹形成堤岸以形成多层波纹管。 波纹管的热处理通过加热至1000-1130℃，在该温度下保持在屏蔽介质中，直到强化相完全溶解在合金中，随后冷却至 合金中的相变终止。 使用稀薄的空气介质或氩气作为屏蔽介质。

    Liquid-propellant rocket engine with turbine gas afterburning
    5.
    发明授权
    Liquid-propellant rocket engine with turbine gas afterburning 有权
    液体推进剂火箭发动机与涡轮气体燃烧

    公开(公告)号：US06226980B1

    公开(公告)日：2001-05-08

    申请号：US09393435

    申请日：1999-09-10

    申请人： Boris Ivanovich Katorgin ,  Vladimir Konstantinovich Chvanov ,  Gennady Grigorievich Derkach ,  Jury Vasilievich Movchan ,  Felix Jurievich Chelkis ,  Vadim Iliich Semenov ,  Leonid Alexeevich Tolstikov

    发明人： Boris Ivanovich Katorgin ,  Vladimir Konstantinovich Chvanov ,  Gennady Grigorievich Derkach ,  Jury Vasilievich Movchan ,  Felix Jurievich Chelkis ,  Vadim Iliich Semenov ,  Leonid Alexeevich Tolstikov

    IPC分类号： F02K948

    CPC分类号： F02K9/48 ,  F02K9/95

    摘要： The engine comprises a chamber, fuel and oxidizer booster pumps, a turbopump unit, a gas generator, an electrically driven thrust regulator, and a fuel throttle. A programmable starting and ignition system is introduced, which includes a fuel tank, connected to the thrust regulator, and a first ampoule with starting fuel, an output of which through a starting/cut-off valve is connected to fuel injectors of the gas generator. The aforesaid tank is also connected through a second ampoule to the starting fuel and by a jet to autonomous ignition injectors located in the space of the combustion chamber of the engine. An inclined Archimedian screw pump with a gas turbine as an actuator and an oxidizing gas as a working medium is used as an oxidizer booster pump. The gas is discharged after its use in a turbine into an outlet manifold of the booster pump. A heat exchanger, in which the gas used for rocket tank pressurization is heated, is mounted on a pipeline feeding the gas to the aforesaid gas turbine of the booster pump actuator.

    摘要翻译： 发动机包括室，燃料和氧化剂增压泵，涡轮泵单元，气体发生器，电动推力调节器和燃料油门。 引入了可编程起动和点火系统，其包括连接到推力调节器的燃料箱和具有起动燃料的第一安瓶，其通过起动/截止阀的输出连接到气体发生器的燃料喷射器 。 上述罐还通过第二安瓿连接到起动燃料，并且通过喷射器连接到位于发动机的燃烧室的空间中的自动点火喷射器。 使用具有作为致动器的燃气轮机和作为工作介质的氧化气体的倾斜的阿基米经螺杆泵作为氧化剂增压泵。 气体在涡轮机使用后被排放到增压泵的出口歧管中。 将用于火箭罐加压的气体加热的热交换器安装在将气体供给到增压泵致动器的上述燃气轮机的管道上。

    Liquid-propellant rocket engine
    6.
    发明授权
    Liquid-propellant rocket engine 有权
    液体推进剂火箭发动机

    公开(公告)号：US06170258B2

    公开(公告)日：2001-01-09

    申请号：US09391154

    申请日：1999-09-08

    申请人： Boris Ivanovich Katorgin ,  Vladimir Konstantinovich Chvanov ,  Felix Jurievich Chelkis ,  Vadim Lliich Semenov ,  Valentin Georgievich Polushin ,  Nina Ivanovna Murlykina

    发明人： Boris Ivanovich Katorgin ,  Vladimir Konstantinovich Chvanov ,  Felix Jurievich Chelkis ,  Vadim Lliich Semenov ,  Valentin Georgievich Polushin ,  Nina Ivanovna Murlykina

    IPC分类号： F02K900

    CPC分类号： F02K9/60 ,  F02K9/42 ,  F05D2240/90

    摘要： The liquid-propellant rocket engine comprises two combustion chambers, a gas generator, a turbopump assembly, pipelines as well as a frame having footpads and supports located in different planes that are perpendicular to the engine axis, said frame being made up of at least two welded rod sections. Said sections are fastened to each other by a plane rod joint. The engine pipelines are connected to the combustion chambers and comprise bellows balances or flexible hoses which have their movable ends connected directly to the combustion chambers or to pipes joined thereto. The frame is made demountable due to the use of threaded connections that joint together the frame sections and the plane rod joint. The frame is made as a compensation frame by placing the footpad plane over the support plane. A curved pipe joint comprises a curved pipe, a hinge and a frame. At its end on the outlet side, the pipe is provided with a balance for compensating angular displacements, for instance, a bellows balance with a cardan mechanism. The curved pipe is connected to the frame by a hinge, and its outlet end is gas-tightly connected to the bellows of the balance.

    摘要翻译： 液体推进剂火箭发动机包括两个燃烧室，气体发生器，涡轮泵组件，管道以及位于垂直于发动机轴线的不同平面中的脚垫和支架的框架，所述框架由至少两个 焊接杆部分。 所述部分通过平面杆接头彼此紧固。 发动机管道连接到燃烧室，并且包括波纹管平衡或软管，其可动端部直接连接到燃烧室或连接到其上的管道。 由于使用将框架部分和平面杆接头连接在一起的螺纹连接，框架可拆卸。 通过将支脚平面放置在支撑平面上，框架作为补偿框架。 弯曲管接头包括弯管，铰链和框架。 在出口侧的端部，管道设置有用于补偿角位移的平衡，例如与万向节机构的波纹管平衡。 弯管通过铰链连接到框架，其出口端气密地连接到天平的波纹管。

    Liquid-propellant rocket engine chamber and its casing
    7.
    发明授权
    Liquid-propellant rocket engine chamber and its casing 有权
    液体推进剂火箭发动机室及其外壳

    公开(公告)号：US06244041B1

    公开(公告)日：2001-06-12

    申请号：US09394259

    申请日：1999-09-10

    申请人： Alexandr Alexandrovich Vasin ,  Stanislav Dmitrievich Kamensky ,  Boris Ivanovich Katorgin ,  Alexei Ivanovich Kolesnikov ,  Viktor Petrovich Nosov ,  Anatoly Ivanovich Stavrulov ,  Vladimir Vladimirovich Fedorov ,  Vladimir Konstantinovich Chvanov

    发明人： Alexandr Alexandrovich Vasin ,  Stanislav Dmitrievich Kamensky ,  Boris Ivanovich Katorgin ,  Alexei Ivanovich Kolesnikov ,  Viktor Petrovich Nosov ,  Anatoly Ivanovich Stavrulov ,  Vladimir Vladimirovich Fedorov ,  Vladimir Konstantinovich Chvanov

    IPC分类号： F02K995

    CPC分类号： F02K9/62 ,  F02K9/52

    摘要： The invention relates to rocket engine manufacturing, and may also be used in aircraft engine manufacturing. A chamber comprises a casing, ignition means and a mixing head. The mixing head consists of an internal injector face, a middle bottom, an external bottom. Bipropellant injectors are fixed in the internal injector face and the middle bottom. A portion of the bipropellant injectors are mounted projecting from the internal injector face, while another portion are recessed in the internal injector face. The ignition means are made from jet injectors mounted in a structural casing behind the internal injector face. Axes of diverging ports of jet injectors are positioned at an acute angle to an outlet from the structural casing and deflected in a circle in a lateral plane from the longitudinal axis of the structural casing in an identical direction. The chamber casing comprises a combustion chamber and a nozzle, made from an external structural envelope and an internal fire wall. A regenerative cooling passage is positioned between the external structural envelope and the internal fire wall. A ring-like slot of a gas-screen belt is made in the internal fire wall before the nozzle throat. The regenerative cooling passage of the chamber is made with a branched inlet. One of its branches communicates with the space of the chamber regenerative cooling passage between the nozzle throat and its scarf, a second branch—with the space of the chamber regenerative cooling passage before the nozzle throat, and a third—with the space of the chamber regenerative cooling passage before the ring-like slot of the gas-screen belt.

    摘要翻译： 本发明涉及火箭发动机制造，也可用于飞机发动机制造。 腔室包括壳体，点火装置和混合头。 混合头由内部注射器面，中间底部，外部底部组成。 双通道注射器固定在内部注射器面和中间底部。 双组元推进剂注射器的一部分从内部注射器表面安装突出，而另一部分凹入内部注射器表面。 点火装置由安装在内部喷射器面后面的结构壳体中的喷射喷射器制成。 喷射喷射器的发散端口的轴线与结构壳体的出口成锐角地定位，并且沿着相同方向从结构壳体的纵向轴线在横向平面中以一个圆形的方式偏转。 室外壳包括由外部结构外壳和内部防火墙制成的燃烧室和喷嘴。 再生冷却通道位于外部结构外壳和内部防火墙之间。 气体屏蔽带的环状槽在喷嘴喉部之前的内部防火墙中制成。 室的再生冷却通道由分支入口制成。 其一个分支与喷嘴喉部和其围巾之间的腔室再生冷却通道的空间相通，第二分支与腔室再生冷却通道的空间在喷嘴喉部之间，第三分支与腔室的空间 气体屏蔽带环形槽前的再生冷却通道。