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213 条记录 (耗时 0.016 秒)

    Ablative baffle for a liquid rocket engine thrust chamber
    13.
    发明申请
    Ablative baffle for a liquid rocket engine thrust chamber 失效
    用于液体火箭发动机推力室的烧蚀挡板

    公开(公告)号：US20050097883A1

    公开(公告)日：2005-05-12

    申请号：US10734279

    申请日：2003-12-15

    申请人： Chulsung Ryu ,  Wooseok Seol ,  Sangyeop Han

    发明人： Chulsung Ryu ,  Wooseok Seol ,  Sangyeop Han

    IPC分类号： F02K1/06 ,  F02K9/34 ,  F02K9/42 ,  F02K9/62 ,  F02K9/95

    CPC分类号： F02K9/42 ,  F02K9/34 ,  F02K9/62

    摘要： The present invention is related to an ablative baffle for a liquid rocket engine thrust chamber that comprises: a hub member having a hollow structure, of which both top and bottom parts are open; a plurality of blade rib members, each of which is connected removably at one end to the outer surface of the hub member; and a blade-connecting member having a hollow structure, of which both top and bottom parts are open, to the inner part of which each of blade rib members is connected at the other end. The present invention does not use a conventional internal cooling method, but an ablation cooling method using the composite heat resistant material structure with metal core, so that a liquid rocket engine system may be simplified, and the reliability of liquid rocket engine increases, and the manufacturing cost is cut down.

    摘要翻译： 本发明涉及一种用于液体火箭发动机推力室的烧蚀挡板，其包括：具有中空结构的毂构件，其顶部和底部都是开放的; 多个叶片肋构件，每个叶片肋构件的一端可拆卸地连接到轮毂构件的外表面; 以及具有中空结构的叶片连接构件，其顶部和底部部分均敞开，在其内部，每个叶片肋构件在另一端连接。 本发明不使用传统的内部冷却方法，而是使用具有金属芯的复合耐热材料结构的消融冷却方法，从而可以简化液体火箭发动机系统，并且液体火箭发动机的可靠性增加， 制造成本下降。

    Rocket engine with combustion chamber step structure insert, and its fabrication
    14.
    发明授权
    Rocket engine with combustion chamber step structure insert, and its fabrication 失效
    火箭发动机具有燃烧室阶梯结构插件及其制造

    公开(公告)号：US6138451A

    公开(公告)日：2000-10-31

    申请号：US76033

    申请日：1998-05-11

    申请人： Kurt Kreiner ,  David Bronson

    发明人： Kurt Kreiner ,  David Bronson

    IPC分类号： F02K9/52 ,  F02K9/62

    CPC分类号： F02K9/52 ,  F02K9/62 ,  F05D2230/90 ,  F05D2300/13 ,  F05D2300/133 ,  Y10T29/49346

    摘要： A rocket engine has a combustion chamber formed of an annular wall made of an annular wall material, and an annular insert made of an annular insert material that is of substantially the same thermal expansion coefficient as the annular wall material. The annular insert has an insert outer surface sized to fit within and contact the wall inner surface along less than the wall length. The annular wall and the annular insert are welded together. There is further an attachment between the combustion chamber and an injector. The attachment includes an annular metallic deposit bonded to the combustion chamber, an annular adaptor ring, a weld joint between the adaptor ring and the metallic deposit, and a joint between the adaptor ring and the injector.

    摘要翻译： 火箭发动机具有由环形壁材料制成的环形壁形成的燃烧室和由与环形壁材料基本相同的热膨胀系数的环形插入材料制成的环形插入件。 环形插入件具有插入件外表面，其尺寸适于沿着小于壁长度装配在壁内表面内并且接触壁内表面。 环形壁和环形插入件焊接在一起。 在燃烧室和喷射器之间还有附件。 附件包括结合到燃烧室的环形金属沉积物，环形适配环，适配环和金属沉积物之间的焊接接头以及接合环和注射器之间的接头。

    Discus-shaped aerodyne vehicle for extremely high velocities
    15.
    发明授权
    Discus-shaped aerodyne vehicle for extremely high velocities 失效
    铁饼型空气动力车非常高速度

    公开(公告)号：US5836543A

    公开(公告)日：1998-11-17

    申请号：US666581

    申请日：1996-08-01

    申请人： Klaus Kunkel ,  Peter Plichta

    发明人： Klaus Kunkel ,  Peter Plichta

    IPC分类号： B64C39/06 ,  F02K9/44 ,  F02K9/62 ,  F02K9/68 ,  B64C15/12 ,  B64C30/00

    CPC分类号： F02K9/68

    摘要： A discus-shaped aircraft is provided with a peripheral jet arrangement for generating lift and, in the bottom of the aircraft, at least one rocket engine supplied with silicon hydride and compressed air and operated under conditions in which the silicon hydride is reacted with nitrogen of the compressed air to form silicon nitride while the nitrogen of the silicon hydride compounds reacts with oxygen to form H.sub.2 O.

    摘要翻译： PCT No.PCT / DE95 / 01430 Sec。 371日期：1996年8月1日 102（e）日期1996年8月1日PCT 1995年10月16日PCT PCT。 WO96 / 14504 PCT出版物 日期1996年5月17日一种铁饼形飞机设置有用于产生升降机的外围喷射装置，并且在飞机的底部中至少一个提供有氢化硅和压缩空气的火箭发动机，并在其中硅氢化物 与压缩空气的氮气反应以形成氮化硅，同时氮化硅化合物的氮与氧反应形成H 2 O.

    Generator of hot gases using hybrid propellant
    16.
    发明授权
    Generator of hot gases using hybrid propellant 失效
    使用混合推进剂的热气发生器

    公开(公告)号：US3584461A

    公开(公告)日：1971-06-15

    申请号：US3584461D

    申请日：1969-11-24

    申请人： EUROP PROPULSION

    发明人： DEBIZE FRANCIS ,  DUSSAUT JEAN-JACQUES HENRI ,  MORIN RENE THEOPHILE ALBERT

    IPC分类号： F02K9/62 ,  F02K9/04 ,  F23R1/16

    CPC分类号： F02K9/62 ,  F02K9/72

    摘要： A generator of hot gases employing hybrid propellant, more especially for a rocket-motor, and which includes an enclosure which terminates at one of its ends in a nozzle and in which there is accommodated a propellant in the solid phase and into which at least two injection devices have port, which devices each emit at least one jet of a propellant in the fluid phase able to enter into reaction with the propellant in the solid phase so as to produce a gaseous mass which escapes through the nozzle, wherein the enclosure is divided by a perforated partition or screen, arranged transversely to the general direction of flow of the gaseous mass, into an upstream space remote from the nozzle, in which space the entirety of the solid phase is accommodated in the form of a multitude of fragments, and into an unoccupied downstream space, one of the injection devices, or the primary injection device, having port in the upstream space while the other or secondary injection device has port in the downstream space.