公开(公告)号：US11761451B1

公开(公告)日：2023-09-19

申请号：US18150329

申请日：2023-01-05

申请人： Blue Origin, LLC

发明人： Jordan Marshall

IPC分类号： F04D29/041 ,  F04D13/04 ,  F02K9/48

CPC分类号： F04D29/0416 ,  F04D13/04 ,  F02K9/48

摘要： A rocket engine propulsion system having improved engine performance is described herein. The rocket engine propulsion system includes an axial counterbalance to reduce or eliminate axial thrust exerted on components of a turbopump. The axial counterbalance can allow for a larger range of axial thrust forces while coupling this ability to a rotational speed (e.g., rotations per minute, or RPM) of a shaft. The axial counterbalance includes a protrusion on that extends circumferentially around a shaft that mates with a protrusion on a swing arm. The swing arm is rotatably attached to a bracket which is constrained by a static support.

公开(公告)号：US10072610B2

公开(公告)日：2018-09-11

申请号：US14440835

申请日：2013-11-04

申请人： SNECMA

发明人： Jean Michel Sannino ,  François Lassoudiere ,  David Hayoun

IPC分类号： F02K9/48 ,  F02K9/50 ,  F02K9/97 ,  F02K9/64

CPC分类号： F02K9/48 ,  F02K9/50 ,  F02K9/64 ,  F02K9/972

摘要： The invention relates to a feed device for feeding a thrust chamber (10) of a rocket engine (100) with first and second propellants. According to the invention, a first feed circuit (16) of the thrust chamber (10) comprises a turbopump (22) having at least one pump (22a) for pumping the first propellant from a first tank (12), and a turbine (22b) mechanically coupled to said pump (22a). The first feed circuit connects an outlet of the pump to an inlet of the turbine via a heat exchanger (24) configured to heat the first propellant with heat generated by the thrust chamber, in order to actuate the turbine. According to the invention, a second feed circuit (18) is configured to feed the thrust chamber with second propellant from a second tank (14) that is configured to be pressurized. The invention also provides a method of feeding a rocket engine thrust chamber with first and second propellants.

公开(公告)号：US09650995B2

公开(公告)日：2017-05-16

申请号：US14212397

申请日：2014-03-14

申请人： Orbital Sciences Corporation

发明人： Antonio L. Elias

IPC分类号： F02K9/42 ,  F02K9/48

CPC分类号： F02K9/42 ,  F02K9/48

摘要： Systems and methods are described herein for a hybrid liquid propellant rocket engine. In an embodiment, the engine includes a first pump powered by a first turbine, a second pump powered by a second turbine, and a gas generator. An output of the gas generator is connected to the first turbine and the second turbine. The engine further includes a third pump powered by a third turbine, a fourth pump powered by a fourth turbine, and a nozzle having an expander cycle in a wall and a combustion chamber. An output of the third pump is connected to the expander cycle and an output of the wall is connected to the third turbine and the fourth turbine. An output of the fourth pump, an output of the third turbine, and an output of the fourth turbine are connected to the combustion chamber.

公开(公告)号：US20160177963A1

公开(公告)日：2016-06-23

申请号：US14906712

申请日：2014-07-11

申请人： SNECMA

发明人： François DANGUY ,  Jean-Michel NGUYEN DUC ,  Laurent FABBRI ,  Cédric SENE

IPC分类号： F04D29/08 ,  F04D29/043 ,  F04D29/046 ,  F02K9/46 ,  F04D29/42 ,  F01D5/02 ,  F04D7/02 ,  F04D1/00 ,  F04D29/22

CPC分类号： F04D29/086 ,  F01D3/04 ,  F01D5/02 ,  F01D25/16 ,  F01D25/183 ,  F02K9/46 ,  F02K9/48 ,  F04D1/00 ,  F04D7/02 ,  F04D13/043 ,  F04D29/0413 ,  F04D29/043 ,  F04D29/046 ,  F04D29/108 ,  F04D29/22 ,  F04D29/426 ,  F05D2220/80 ,  F05D2240/53

摘要： The invention relates to the field of centrifugal pumps, and in particular it relates to a centrifugal pump (303, 403) comprising at least: an impeller (303a, 403a); a rotary shaft (302, 402) secured to said impeller (303a, 403a); a casing (320, 420) having an axial admission passage (325, 425); at least one first bearing (305, 405) supporting said rotary shaft (302, 402) in said casing (320, 420); and at least one dynamic seal (311, 411) around the rotary shaft (302, 402), the impeller (303a, 403a) being situated between the at least one dynamic seal (311, 411) and the axial admission passage (325, 425) of the pump (303, 403). The centrifugal pump (303, 403) also comprises, between the impeller (303a, 403a) and at least one dynamic seal (311, 411), an axial force compensation disk (330, 430) secured to the shaft (302, 402) and presenting a diameter greater than 70% of a diameter of the impeller (303a, 403a). A front face (330a, 430a) of the disk (330, 430) faces towards the impeller (303a, 403a) and is connected to a branch connection for fluid under pressure taken downstream from the pump (303, 403), and a rear face (330b, 430b) faces towards the dynamic seals (311, 411) and presents fins (330c, 430c) that are oriented radially, at least in part.

摘要翻译： 本发明涉及离心泵的领域，特别涉及一种至少包括叶轮（303a，403a）的离心泵（303,403）。 固定到所述叶轮（303a，403a）上的旋转轴（302,402）; 具有轴向入口通道（325,425）的壳体（320,420）; 在所述壳体（320,420）中支撑所述旋转轴（302,402）的至少一个第一轴承（305,405）; 以及围绕所述旋转轴（302,402）的至少一个动态密封件（311,411），所述叶轮（303a，403a）位于所述至少一个动态密封件（311,411）和所述轴向进入通道（325）之间， （303,403）。 离心泵（303,403）还包括在叶轮（303a，403a）和至少一个动态密封件（311,411）之间，固定到轴（302,402）的轴向力补偿盘（330,430） 并且具有大于叶轮（303a，403a）的直径的70％的直径。 盘（330,430）的前表面（330,430a）面向叶轮（303a，403a）并且连接到用于在泵（303,403）下游的压力下的流体的分支连接件，并且后部 面（330b，430b）面向动态密封件（311,411）并且呈现至少部分地径向定向的翅片（330c，430c）。

公开(公告)号：US09341315B2

公开(公告)日：2016-05-17

申请号：US14365204

申请日：2012-12-07

申请人： SNECMA

发明人： David Hayoun ,  Francois Danguy ,  Jean Michel Sannino ,  Pascal Marcel Jean Noir

IPC分类号： F17D1/16 ,  F17D3/01 ,  F02K9/50 ,  F17C5/00 ,  F16L53/00 ,  F02K9/48

CPC分类号： F17D3/01 ,  F02K9/48 ,  F02K9/50 ,  F16L53/30 ,  F17C5/00 ,  F17C2201/054 ,  F17C2205/0326 ,  F17C2221/011 ,  F17C2221/012 ,  F17C2221/017 ,  F17C2221/08 ,  F17C2223/0161 ,  F17C2223/033 ,  F17C2225/0123 ,  F17C2225/036 ,  F17C2227/0107 ,  F17C2227/0135 ,  F17C2227/0142 ,  F17C2227/0157 ,  F17C2227/0164 ,  F17C2227/0309 ,  F17C2227/0388 ,  F17C2270/0197 ,  Y02E60/321 ,  Y10T137/0396 ,  Y10T137/6579

摘要： A pressurizing device and method, for pressurizing a first tank, the device including at least a second tank configured to contain a cryogenic fluid, a first pressurizing circuit for putting the second tank into communication with the first tank, the first pressurizing circuit including at least a first heat exchanger for heating a flow of the cryogenic fluid extracted from the second tank through the first pressurizing circuit, and a second pressurizing circuit with a compressor, branched off from the first pressurizing circuit and leading to the second tank. A feed system for feeding a reaction engine with at least a first liquid propellant includes at least a first tank configured to contain the first liquid propellant, and a device for pressurizing the first tank.

摘要翻译： 一种用于对第一罐加压的加压装置和方法，所述装置至少包括构造成容纳低温流体的第二罐，用于使第二罐与第一罐连通的第一加压回路，第一加压回路至少包括 第一热交换器，用于加热通过第一加压回路从第二罐提取的低温流体的流动;以及第二加压回路，其具有从第一加压回路分支并通向第二罐的压缩机。 用于向至少第一液体推进剂供给反应引擎的进料系统包括至少第一罐，其构造成容纳第一液体推进剂，以及用于对第一罐加压的装置。

公开(公告)号：US09166510B1

公开(公告)日：2015-10-20

申请号：US14243248

申请日：2014-04-02

申请人： Hamilton Sundstrand Corporation

发明人： Richard A. Himmelmann

IPC分类号： F01D15/10 ,  F02C6/00 ,  H02K7/18 ,  H02P9/04 ,  H02P9/48 ,  B60R16/03 ,  F02K9/48 ,  F02B33/44

CPC分类号： H02P9/48 ,  B60R16/03 ,  F02K9/46 ,  F02K9/48 ,  F02K9/60 ,  F05D2220/764 ,  H02K7/1823

摘要： A rocket propelled vehicle includes a controllable voltage AC generator configured to be connected to a power generation turbine shaft and configured to convert rotational energy to electrical energy, wherein the controllable voltage AC generator is configured to output a desired voltage irrespective of a change in a rotational speed of the power generation turbine shaft, an AC electric motor pump configured to pump at least one of fuel or oxidizer to a combustion chamber of the rocket propelled vehicle, and an AC bus connecting the controllable voltage AC generator to each of the AC electric motor pump.

摘要翻译： 火箭推进车辆包括可控电压AC发电机，其被配置为连接到发电涡轮机轴并且被配置为将旋转能量转换成电能，其中可控电压AC发电机被配置为输出期望电压，而不管旋转的变化 发电涡轮轴的速度，构造成将燃料或氧化剂中的至少一种泵送到火箭推进车辆的燃烧室的AC电动机泵，以及将可控电压AC发电机连接到每个AC电动机的AC总线 泵。

公开(公告)号：US08613189B1

公开(公告)日：2013-12-24

申请号：US12627663

申请日：2009-11-30

申请人： Philip C Pelfrey ,  Alex Pinera

发明人： Philip C Pelfrey ,  Alex Pinera

IPC分类号： F02K9/00 ,  F02K9/46 ,  F02K9/50

CPC分类号： F02K9/48

摘要： A centrifugal impeller with a single inlet and dual outlets that include a low pressure outlet and a high pressure outlet. The impeller includes low pressure blades with high pressure blades located downstream. The impeller can be shrouded or unshrouded, and can include an inner shroud that forms a flow path for the low pressure fluid and a high pressure flow path for the high pressure fluid. The impeller can include a high pressure volute and a low pressure volute that forms a dual volute with dual diffusers for both fluids.

摘要翻译： 具有单个入口和双出口的离心式叶轮，包括低压出口和高压出口。 叶轮包括位于下游的具有高压叶片的低压叶片。 叶轮可以是遮蔽的或不带盖的，并且可以包括形成用于低压流体的流动路径的内部护罩和用于高压流体的高压流动路径。 叶轮可以包括高压蜗壳和低压蜗壳，其形成具有用于两种流体的双扩散器的双蜗壳。

公开(公告)号：US08572948B1

公开(公告)日：2013-11-05

申请号：US12905274

申请日：2010-10-15

申请人： Alex Pinera

发明人： Alex Pinera

IPC分类号： F02K9/50 ,  F02K9/64

CPC分类号： F02K9/50 ,  F02K9/48 ,  F02K9/64

摘要： A rocket propulsion system having a liquid fuel tank and a liquid oxidizer tank, where a liquid inert gas tank supplies liquid inert gas to a liquid inert gas pump driven by a turbine of the engine to pressurize the liquid inert gas, which is passed through a heat exchanger around the nozzle to vaporize the inert gas, that is then used to pressurize the liquid oxidizer tank so that a liquid oxidizer pump is not needed, or to pressurize both the liquid oxidizer tank and the liquid fuel tank so that a liquid oxidizer pump and a liquid fuel pump are not needed in the rocket engine.

摘要翻译： 一种具有液体燃料箱和液体氧化剂罐的火箭推进系统，其中液体惰性气体罐将液体惰性气体供应到由发动机的涡轮机驱动的液体惰性气体泵，以加压流过 在喷嘴周围的热交换器，以蒸发惰性气体，然后将其用于加压液体氧化剂罐，使得不需要液体氧化剂泵，或者对液体氧化剂罐和液体燃料箱两者加压，使得液体氧化剂泵 并且在火箭发动机中不需要液体燃料泵。

公开(公告)号：US08019494B1

公开(公告)日：2011-09-13

申请号：US12269717

申请日：2008-11-12

申请人： Frank S. Mango

发明人： Frank S. Mango

IPC分类号： B64G1/40

CPC分类号： F02K9/48 ,  B64G1/401 ,  B64G1/402 ,  F02K9/42 ,  F02K9/56 ,  F05D2270/13 ,  F05D2270/31

摘要： Propellant management systems and methods are provided for controlling the delivery of liquid propellants in a space launch vehicle utilizing multiple rockets. The propellant management systems and methods may be configured to enable substantial simultaneous depletion of liquid propellants in each of a plurality of active rockets during operation of various booster stages of the launch vehicle.

摘要翻译： 提供推进剂管理系统和方法，用于控制利用多个火箭的空间运载火箭中液体推进剂的输送。 推进剂管理系统和方法可以被配置为使得能够在运载火箭的各种增压级的运行期间在多个活动火箭中的每一个中实质上同时耗尽液体推进剂。

公开(公告)号：US20090235639A1

公开(公告)日：2009-09-24

申请号：US12200265

申请日：2008-08-28

申请人： Tatsuya KIMURA ,  Yoshihiro KAWAMATA ,  Kenichi NIU

发明人： Tatsuya KIMURA ,  Yoshihiro KAWAMATA ,  Kenichi NIU

IPC分类号： F02K9/08

CPC分类号： F02K1/38 ,  F02K9/48 ,  F02K9/58 ,  F02K9/82 ,  F02K9/972 ,  F05D2250/713

摘要： A rocket nozzle includes a dual-bell nozzle and a gas introducing section configured to introduce gas into space surrounded by the dual-bell nozzle. Combustion gas flows in the space. The dual-bell nozzle includes a first stage nozzle bell-shaped and surrounding an upstream portion of the space, and a second stage nozzle bell-shaped and surrounding a downstream portion of the space. The dual-bell nozzle has an inflection point between the first stage nozzle and the second stage nozzle. The gas introducing section includes a gas inlet provided to an inner wall surface of the first stage nozzle. The gas is introduced into the space from the gas inlet.

摘要翻译： 火箭喷嘴包括双钟形喷嘴和构造成将气体引入由双钟形喷嘴包围的空间中的气体导入部。 燃烧气体在空间中流动。 双钟形喷嘴包括钟形状的第一级喷嘴并且围绕该空间的上游部分，以及第二级喷嘴钟形并围绕该空间的下游部分。 双钟形喷嘴在第一级喷嘴和第二级喷嘴之间具有拐点。 气体导入部包括设置在第一级喷嘴的内壁面的气体入口。 气体从气体入口引入空间。