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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
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。
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公开(公告)号：US6107596A
公开(公告)日：2000-08-22
申请号：US391860
申请日：1999-09-08
申请人： Viktor Nikonorovich Semenov , Anatoly Ivanovich Grigoriev , Gennady Grigorievich Derkach , Boris Ivanovich Katorgin , Vladimir Konstantinovich Chvanov , Jury Vasilievich Movchan , Galina Vasilievna Shashelova , Vladimir Veniaminovich Sagalovich , Evgeny Ivanovich Baranov , Leonid Alexeevich Tumanov , Nikolai Kondratievich Dudkin , Ljudmila Alexandrovna Anosova , Raisa Vasilievna Chernikova , Alexandr Nikolaevich Vycherov , Oleg Ivanovich Studenikin , Nikolai Fedorovich Molev , Jury Alexandrovich Pestov , Jury Alexandrovich Bedov , Alexandr Alexandrovich Vasin , Vladimir Jurievich Bogushev , Vladimir Vladimirovich Fedorov , Nikolai Mikhailovich Grigorkin , Galina Andreevna Babaeva , Stanislav Dmitrievich Kamensky
发明人： Viktor Nikonorovich Semenov , Anatoly Ivanovich Grigoriev , Gennady Grigorievich Derkach , Boris Ivanovich Katorgin , Vladimir Konstantinovich Chvanov , Jury Vasilievich Movchan , Galina Vasilievna Shashelova , Vladimir Veniaminovich Sagalovich , Evgeny Ivanovich Baranov , Leonid Alexeevich Tumanov , Nikolai Kondratievich Dudkin , Ljudmila Alexandrovna Anosova , Raisa Vasilievna Chernikova , Alexandr Nikolaevich Vycherov , Oleg Ivanovich Studenikin , Nikolai Fedorovich Molev , Jury Alexandrovich Pestov , Jury Alexandrovich Bedov , Alexandr Alexandrovich Vasin , Vladimir Jurievich Bogushev , Vladimir Vladimirovich Fedorov , Nikolai Mikhailovich Grigorkin , Galina Andreevna Babaeva , Stanislav Dmitrievich Kamensky
CPC分类号： F02K9/68 , B23K1/0018 , B23K1/0056 , B23K15/0006 , B23K9/0026 , Y10T29/49346
摘要： A combustion chamber for a liquid-propellant rocket engine includes an injector head jointed to a combustion chamber casing having an exhaust head on a nozzle output. The casing is made of a steel jacket and a bronze-steel internal fire wall, which are joined with each other and contain shells connected in series. The exhaust head with shells of the casing, jointed to the exhaust head, are brazed using a solder on the basis of nickel, chromium and manganese. Parts of the injector head and other members of the combustion chamber casing are brazed using a copper-silver solder. Shells of the fire wall are connected by an electron-beam welding, directing an electron beam into axial gaps left while brazing between shells of the jacket. The shells of the jacket are then sequentially connected by an automatic gas-shielded arc welding through corresponding ring spacers.
摘要翻译： 用于液体推进剂火箭发动机的燃烧室包括连接到具有在喷嘴输出上的排气头的燃烧室壳体的喷射头。 外壳由钢护套和青铜钢内部防火墙制成，它们彼此连接并包含串联连接的外壳。 连接到排气头的壳体外壳的排气头使用镍，铬和锰的焊料进行钎焊。 喷射头部分和燃烧室壳体的其它部件使用铜 - 银焊料钎焊。 防火墙的外壳通过电子束焊接连接，将电子束导向轴向间隙，同时在外壳的外壳之间进行钎焊。 然后通过相应的环形间隔件通过自动气体保护电弧焊接顺序地连接外壳的外壳。
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公开(公告)号：US06321450B1
公开(公告)日：2001-11-27
申请号：US09410875
申请日：1999-10-01
申请人： Viktor Nikonorovich Semenov , Gennady Grigorievich Derkach , Boris Ivanovich Katorgin , Vladimir Konstantinovich Chvanov , Jury Vasilievich Movchan , Leonid Alexeevich Tumanov , Nikolai Kondratievich Dudkin , Valery Petrovich Mordashov , Anatoly Lukich Loginov , Oleg Andreevich Masljukov , Larisa Mikhailovna Panaskina , Alexandr Nikolaevich Vycherov , Nikolai Fedorovich Molev , Jury Alexandrovich Pestov , Alexandr Alexandrovich Vasin , Vladimir Jurievich Bogushev , Nikolai Mikhailovich Grigorkin
发明人： Viktor Nikonorovich Semenov , Gennady Grigorievich Derkach , Boris Ivanovich Katorgin , Vladimir Konstantinovich Chvanov , Jury Vasilievich Movchan , Leonid Alexeevich Tumanov , Nikolai Kondratievich Dudkin , Valery Petrovich Mordashov , Anatoly Lukich Loginov , Oleg Andreevich Masljukov , Larisa Mikhailovna Panaskina , Alexandr Nikolaevich Vycherov , Nikolai Fedorovich Molev , Jury Alexandrovich Pestov , Alexandr Alexandrovich Vasin , Vladimir Jurievich Bogushev , Nikolai Mikhailovich Grigorkin
IPC分类号： B21D5300
CPC分类号： F02K9/62 , B23K31/02 , Y10T29/49346 , Y10T29/49904
摘要： A gas generator is produced of separate units, including a mixing head, a casing and an outlet branch pipe, which are interjoined by welding. The mixing head is welded to the outlet branch pipe through a spacer and a structural spherical casing. The spacer and the outlet branch pipe are made of two inter-brazed envelopes, the inner envelopes of the spacer and the branch pipe are welded at their end faces by electron-beam welding, and the outer structural envelopes are welded by electron-arc welding using a split ring. The spacer is joined to the mixing head by automatic gas-shielded welding. The spherical casing of the gas generator is welded to the outlet branch pipe and the mixing head after the spacer is welded to the mixing head and the outlet branch pipe.
摘要翻译： 气体发生器由分开的单元制成，包括混合头，外壳和出口支管，它们通过焊接相连接。 混合头通过间隔件和结构球形外壳焊接到出口支管上。 间隔件和出口支管由两个相互钎焊的信封制成，间隔件和分支管的内包层通过电子束焊接在其端面焊接，外部结构信封通过电子电弧焊 使用开环。 间隔件通过自动气体保护焊接连接到混合头。 气体发生器的球形壳体焊接到出口支管，并且将间隔件焊接到混合头和出口支管上之后的混合头。
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公开(公告)号：US06222148B1
公开(公告)日：2001-04-24
申请号：US09398924
申请日：1999-09-16
申请人： Viktor Nikonorovich Semenov , Vladimir Ilich Bobkov , Mikhail Ivanovich Zykov , Valentin Georgievich Polushin , Boris Ivanovich Katorgin , Gennady Grigorievich Derkach , Vladimir Konstantinovich Chvanov , Jury Vasilievich Movchan , Jury Aleksandrovich Pestov , Pavel Ivanovich Ogibalin , Tatiana Mikhailovna Avsenjuk , Alexandr Nikolaevich Vycherov
发明人： Viktor Nikonorovich Semenov , Vladimir Ilich Bobkov , Mikhail Ivanovich Zykov , Valentin Georgievich Polushin , Boris Ivanovich Katorgin , Gennady Grigorievich Derkach , Vladimir Konstantinovich Chvanov , Jury Vasilievich Movchan , Jury Aleksandrovich Pestov , Pavel Ivanovich Ogibalin , Tatiana Mikhailovna Avsenjuk , Alexandr Nikolaevich Vycherov
IPC分类号： B23K909
摘要： The method for prodicing a multilayer thin-walled bellows of stainless steel consists of manufacturing round billets by welding the sheets, packing the round billets into a multilayer bank, corrugating the bank for forming the multilayer bellows and the bellows tightness testing. The round billets are manufactured of the preliminary cut sheets of given dimensions by their electric arc pulsed gas-shielded welding. The packed multilayer bank is welded from two sides over the end faces and subjected to heat treatment by its heating up to the temperature of 1000-1130° C. in the shielding medium and holding at this temperature during 20-45 minutes with subsequent cooling.
摘要翻译： 用于制造不锈钢多层薄壁波纹管的方法包括通过焊接片材制造圆形坯料，将圆形坯料包装成多层板，瓦楞纸板以形成多层波纹管和波纹管密封性测试。 通过电弧脉冲气体保护焊接，通过给定尺寸的预切割片制造圆钢坯。 堆叠多层体从端面两侧焊接，在屏蔽介质中通过加热至1000〜1130℃的温度进行热处理，并在此温度下保持20〜45分钟，随后冷却。
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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。
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6.发明授权Method for increasing the specific impulse in a liquid-propellant rocket engine and rocket powder unit for realising the same 有权用于提高液体推进剂火箭发动机和火箭发动机单元中实现相同冲击的方法公开(公告)号：US06415596B1
公开(公告)日：2002-07-09
申请号：US09744627
申请日：2001-03-15
申请人： Boris Ivanovich Katorgin , Felix Jurievich Chelkis , Igor Grigorievich Storozhenko , Sergei Prokopievich Chernykh , Oleg Efimovich Batalin , Evgeny Shmerovich Finkelshtein , Alexandr Grigorievich Liakumovich , Benyamin Sinaevich Strelchik , Vladimir Serapionovich Anufriev
发明人： Boris Ivanovich Katorgin , Felix Jurievich Chelkis , Igor Grigorievich Storozhenko , Sergei Prokopievich Chernykh , Oleg Efimovich Batalin , Evgeny Shmerovich Finkelshtein , Alexandr Grigorievich Liakumovich , Benyamin Sinaevich Strelchik , Vladimir Serapionovich Anufriev
IPC分类号： F02K972
摘要： The present invention pertains to the field of rocketry and more precisely to liquid-propellant rocket engines and to rocket power units. This invention essentially relates to a method for increasing the specific impulse in a liquid-propellant rocket engine by using oxygen as well as a hydrocarbon fuel consisting of dicyclobutyl (C8H14). The dicyclobutyl provides for a substantial increase in the specific impulse of the liquid-propellant rocket engine when compared with kerosene. This invention also relates to a power unit for a rocket that has tanks for liquid oxygen and for the hydrocarbon fuel. Since the fuel tank is filled with dicyclobutyl (C8H14), it is thus possible to increase the thrust, the specific impulse, as well as the in-flight operation duration of the engine, and to reduce the weight of the tanks without any substantial change in the circuits of the liquid-propellant rocket engine and of the rocket power unit.
摘要翻译： 本发明涉及火箭领域，更准确地涉及液体推进剂火箭发动机和火箭动力装置。 本发明基本上涉及通过使用氧以及由二环丁基（C 8 H 14）组成的烃燃料来增加液体推进剂火箭发动机中的比冲量的方法。 与煤油相比，二环丁基提供液体推进剂火箭发动机的比冲量的显着增加。 本发明还涉及一种具有用于液氧和烃类燃料的罐的火箭动力装置。 由于燃料箱中填充有二环丁基（C 8 H 14），因此可以增加发动机的推力，比冲量以及飞行中的运行时间，并且可以减轻油箱的重量，而没有任何实质性变化 在液体推进剂火箭发动机和火箭动力装置的回路中。
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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
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。
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公开(公告)号：US06244040B1
公开(公告)日：2001-06-12
申请号：US09391856
申请日：1999-09-08
申请人： Alexei Pogosovich Adzhian , Vladimir Jurievich Bogushev , Valentina Dmitrievna Kolesnikova , Alexandr Mikhailovich Samsonov , Jury Anatolievich Tjurin , Boris Ivanovich Katorgin
发明人： Alexei Pogosovich Adzhian , Vladimir Jurievich Bogushev , Valentina Dmitrievna Kolesnikova , Alexandr Mikhailovich Samsonov , Jury Anatolievich Tjurin , Boris Ivanovich Katorgin
IPC分类号： F02K942
摘要： A gas generator in particular for driving liquid-propellant rockets, having, a structural envelope, an outlet pipe, a cover connected to the structural envelope from the side opposite to the outlet pipe. A bush is made on the inner side of the cover. An injector face is mounted on the bush end to form a space between the injector face and the cover. Chambers are made in the injector face and the cover. A spacer, mounted inside the structural envelope, is fastened on the outlet pipe and the bush to form an annular space there between. Mixing modules are fastened in the cover and in the injector face chambers. A propellent feed inlet pipe is fastened to the outer surface of the cover inside which a propellant space is made. An oxidizer feed inlet pipe is fastened inside the structural envelope and communicates with the annular space. The annular space communicates with the space between the cover and the injector face via ports made in the bush. The propellant space communicates with propellant passages of the mixing modules through calibrated openings made in the cover. The space between the cover and the injector face communicates with annular oxidizer passages of the mixing modules via openings. Slots are made in the injector face between housing of the mixing modules and walls of the chambers.
摘要翻译： 特别是用于驱动液体推进剂火箭的气体发生器，具有结构外壳，出口管，从与出口管相对的一侧连接到结构外壳的盖。 在盖的内侧制作衬套。 注射器面安装在衬套端部上以在注射器面和盖之间形成空间。 腔室在注射器面和盖子中制成。 安装在结构外壳内部的间隔件紧固在出口管和衬套上，以在其间形成环形空间。 混合模块固定在盖子和注射器面腔中。 推进剂进料管固定在盖子的外表面上，在其外表面上形成有推进剂空间。 氧化剂进料管被固定在结构外壳内并与环形空间连通。 环形空间通过在衬套中形成的端口与盖和喷射器面之间的空间连通。 推进剂空间通过在盖中制成的校准开口与混合模块的推进剂通道连通。 盖和注射器面之间的空间通过开口与混合模块的环形氧化剂通道连通。 在混合模块的壳体和腔室壁之间的喷射器面中制造槽。
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