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公开(公告)号：US4107919A
公开(公告)日：1978-08-22
申请号：US559847
申请日：1975-03-19
Applicant: Daniel E. Sokolowski
Inventor： Daniel E. Sokolowski
Abstract: A heat exchanger, as exemplified by a rocket combustion chamber, is constructed by stacking thin metal rings having microsized openings therein at selective locations to form cooling passages defined by an inner wall, an outer wall and fins. Suitable manifolds are provided at each end of the rocket chamber. In addition to the cooling channel openings, coolant feed openings may be formed in each of rings. The coolant feed openings may be nested or positioned within generally U-shaped cooling channel openings. Compression on the stacked rings may be maintained by welds or the like or by bolts extending through the stacked rings.
Abstract translation: 如火箭燃烧室所例示的热交换器通过在选择性位置上堆叠具有微细开口的薄金属环构成，以形成由内壁，外壁和翅片限定的冷却通道。 在火箭室的每个端部设置合适的歧管。 除了冷却通道开口之外，可以在每个环中形成冷却剂供给开口。 冷却剂供给开口可以嵌套或定位在大致U形的冷却通道开口内。 堆叠环的压缩可以通过焊缝等或通过延伸穿过堆叠环的螺栓来保持。
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公开(公告)号：US3798902A
公开(公告)日：1974-03-26
申请号：US36945873
申请日：1973-06-13
Applicant: MESSERSCHMITT BOELKOW BLOHM
Inventor： BUTTER K
Abstract: Longitudinally extending coolant channels are formed by means of a cutting tool in a monolithic tubular wall section used as the convergent-divergent thrust nozzle for a rocket engine combustion chamber. The width of the channels at particular locations along their length is established in inverse relationship to the amount of heat to be removed from the combustion chamber at that location. In forming the coolant channels their side wall planes are established and radial planes of the tubular wall section are formed in parallel relationship with the side wall planes. The cutting tool is aligned in the radial planes and then is displaced laterally into the side wall planes for cutting the channels. The number of passes required for the cutting operation depends on the width of the tool and the width of the channel which varies over the length of the combustion chamber.
Abstract translation: 纵向延伸的冷却剂通道借助于用作火箭发动机燃烧室的会聚 - 发散推力喷嘴的整体管状壁部分中的切削工具形成。 沿着其长度的特定位置处的通道的宽度与在该位置处从燃烧室移除的热量成反比关系。 在形成冷却剂通道时，其侧壁平面被建立，并且管状壁部分的径向平面与侧壁平面形成平行关系。 切割工具在径向平面中对准，然后横向移位到侧壁平面中以切割通道。 切割操作所需的通过次数取决于工具的宽度和在燃烧室的长度上变化的通道的宽度。
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63.发明授权
公开(公告)号：US3738916A
公开(公告)日：1973-06-12
申请号：US3738916D
申请日：1971-03-12
Applicant: MESSERSCHMITT BOELKOW BLOHM
CPC classification number: C25D1/00 , F02K9/64 , F02K9/972 , Y10S29/012 , Y10T29/49346
Abstract: A PROCESS FOR THE PRODUCTION OF ROCKET COMBUSTION CHAMBERS AND THRUST NOZZLE ASSEMBLIEES HAVING LENGTHWISE COOLING CHANNELS. THE PROCESS CONSISTS OF THE FOLLOWING STEPS: (1) CUTTING THE NEGAATIVE FORM OF THE COOLING CHANNELS INTO THE SURFACE OF A SUITABLE CORE, (2) GALVANICALLY DEPOSITING A FIRST LAYER ON THE CORE SURFACE TO PROVIDE THE INNER WALL OF THE ROCKET COMBUSTION CHAMBER AND THRUST NOZZLE ASSEMBLY SAID INNER WALL ALSO DEFINING SAID COOLING CHANNELS,
(3) FILLING THE COOLING CHANNELS EXTERNALLY WITH AN ELECTRICALLY CONDUCTIVE FILL MATERIAL, AND (4) GALVANICALLY DEPOSITING A SECOND LAYER ON SAID FIRST LAYER AND THE FILL MATERIAL TO PROVIDE A SMOOTH EXTERNAL WALL FOR THE ROCKET COMBUSTION CHAMBER AND THRUST NOZALE ASSEMBLIES.Abstract translation: 一种具有基本均匀厚度的内层的火箭燃烧室或推力喷嘴组件，其具有多个壁桥或肋，以及在其外表面上的冷却通道或凹槽，以及固定到 内层。
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公开(公告)号：US3719046A
公开(公告)日：1973-03-06
申请号：US3719046D
申请日：1970-07-02
Applicant: ROCKET RESEARCH CORP
Inventor： SUTHERLAND G , EMMONS D
CPC classification number: F02K9/64 , F02K9/68 , F05D2260/208
Abstract: An oxidizer, such as nitrogen tetroxide or fluorine, is introduced into a reaction chamber in the path of the decomposition products of hydrazine and reacts therewith to form high temperature, high thrust propulsive gases. A heat pipe surrounds the reaction chamber and includes a wick saturated with a volatile liquid, such as liquid lithium, which liquid is vaporized thereby removing heat from the chamber wall. The vaporized fluid is directed through a heat exchanger and is therein condensed back into a liquid state.
Abstract translation: 将氧化剂如四氧化二氮或氟引入到肼的分解产物的路径中的反应室中，并与其反应形成高温高推力推进气体。 热管围绕反应室并且包括用挥发性液体如液体锂饱和的芯，该液体被蒸发，从而从室壁中除去热量。 蒸发的流体被引导通过热交换器，并在其中冷凝回液态。
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公开(公告)号：US3714695A
公开(公告)日：1973-02-06
申请号：US3714695D
申请日：1970-09-17
Applicant: US AIR FORCE
Inventor： BEESON P
CPC classification number: B21D53/06 , F02K9/64 , Y10T29/49346 , Y10T29/49357
Abstract: A method for forming thrust chambers in which a plurality of tubes are welded together in tube-to-tube alignment. These tubes form a ''''blanket'''' of tubes which can then be formed to any desired thrust chamber configuration.
Abstract translation: 一种用于形成推力室的方法，其中多个管以管对管对准的方式焊接在一起。 这些管形成管的“毯子”，然后可以将其形成为任何所需的推力室构型。
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Patent Agency Ranking
公开(公告)号：US3695515A
公开(公告)日：1972-10-03
申请号：US3695515D
申请日：1970-04-21
Applicant: KARL STOCKEL
Inventor： STOCKEL KARL
CPC classification number: F02K9/64
Abstract: A fluid cooled combustion chamber for a rocket engine is composed of walls forming a longitudinally extending convergentdivergent thrust nozzle having a neck portion at its narrowest section. A radially inner row and a radially outer row of cooling ducts encircle the interior surface of the thrust nozzle at its neck portion with the ducts extending longitudinally into the convergent and divergent portions. The outlet end of the inner row of cooling ducts may be arranged to direct coolant fluid into the thrust nozzle with means providing a twist to the fluid as it enters the nozzle.
Abstract translation: 用于火箭发动机的流体冷却燃烧室由形成纵向延伸的会聚发散推力喷嘴的壁组成，其在其最窄部分具有颈部。 径向内排和径向外排的冷却管道在其颈部处包围推力喷嘴的内表面，其中管道纵向延伸到会聚和发散部分。 内排冷却管道的出口端可以布置成将冷却剂流体引导到推力喷嘴中，该流体在进入喷嘴时向流体提供扭转。
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公开(公告)号：US3659001A
公开(公告)日：1972-04-25
申请号：US3659001D
申请日：1970-02-26
Applicant: PHILLIPS PETROLEUM CO
Inventor： MILLS KING L
Abstract: An electrolyte cell having a heat exchanging shell disposed therein and dividing the cell into an upper and a lower electrolyte chamber. Cathodic tube means, segregated in one region of the shell, extend through said shell and are in communication with said electrolyte chambers. Anode means are disposed in said cathode tubes in a manner to preserve said communication. Down-comer tube means, segregated in another region of said shell, also extend through the shell into communication with said electrolyte chambers.
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68.发明授权
公开(公告)号：US3613207A
公开(公告)日：1971-10-19
申请号：US3613207D
申请日：1969-06-05
Applicant: MESSERSCHMITT BOELKOW BLOHM
Inventor： MALBURG WERNER ADOLF
CPC classification number: B21D53/04 , F02K9/64 , Y10T29/49346 , Y10T29/49357 , Y10T29/4981
Abstract: A METHOD FOR COVERING AND CLOSING COOLING CHANNELS WHICH ARE DEFINED IN A COMBUSTION CHAMBER WALL INCLUDES INSERTING WIRE RODS OVER THE RADIALLY OUTER OPENED ENDS OF THE CHANNELS BETWEEN LONGITUDINALLY EXTENDING WEBB WHICH DEFINE THE CHANNELS AND ESTABLISHING A PERMANENT CONNECTION OF THE WIRE RODS TO THE WEBS SUCH AS BY WELDING OR SOLDERING. A COMBUSTION ENGINE PARTICULARLY ROCKET ENGINE IS FORMED PREFERABLY WITH A CYLINDRICAL MAIN COMBUSTION CHAMBER PORTION HAVING A NARROW THROAT SECTION TERMINATING IN A NOZZLE DISCHARGE FOR THE THRUST GASES AND WITH LONGITUDINALLY EXTENDING GROOVES FOR COOLING FLUID WHICH EXTEND ALONG THE COMPLETE LENGTH OF THE COMBUSTION CHAMBER AND INCLUDING THE NOZZLE SETION. SPACERS OR TEMPLATES ARE INSERTED INTO THE BOTTOM OF THE GROOVES FROM EACH END OF THE COMBUSTION CHAMBER AND THEY ABUT FOR EXAMPLE, IN THE NARROW THROAT SECTION. THEREAFTER WIRE RODS ARE PRESSED INTO THE GROOVES BETWEEN THE WEBS OF THE WALL UP TO THE LIMIT OF THE TEMPLATES AND THEY ARE SECURED TO THE WALLS SUCH AS BY ELECTRONIC WELDING, BY BRAZING USING SOLDERING ROD OR BY SHIELD GAS WELDING. INSTEAD OF USING TEMPLATES THE RODS MAY BE FORMED WITH TRANSVERSE SUPPORTS OF PROJECTING SHOULDERS OR THE WEBS MAY BE FORMED WITH A STEP OR SHOULDER TO POSITION THE ROD UP TO THE DESIRED GROOVE PENETRATION.
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公开(公告)号：US3483698A
公开(公告)日：1969-12-16
申请号：US3483698D
申请日：1966-11-22
Applicant: UNITED AIRCRAFT CORP
Inventor： LEWIS GEORGE D , FORD HARVEY J
CPC classification number: F02K9/64 , F02K9/56 , F05D2260/96 , F23R2900/00014
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公开(公告)号：US3460759A
公开(公告)日：1969-08-12
申请号：US3460759D
申请日：1967-03-07
Applicant: NASA
Inventor： GREGORY JOHN W , NORED DONALD L
CPC classification number: F02K9/64 , Y10S60/909 , Y10T428/249969 , Y10T428/24997
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