公开(公告)号：US07895823B2

公开(公告)日：2011-03-01

申请号：US12147396

申请日：2008-06-26

申请人： Frank A. Sciorelli

发明人： Frank A. Sciorelli

IPC分类号： F02K99/00

CPC分类号： F28D7/1623 ,  F02K9/64 ,  F02K9/972 ,  F02K9/974 ,  F28D21/0003 ,  F28F2265/16

摘要： A cylindrical rocket engine exhaust duct has a liner that fits inside an outer jacket. The outer periphery of the liner has circumferentially spaced ribs defining a sinuous path for a fluid to be heated. The liner has a least one, preferably several, transverse fins with internal serpentine passages for carrying the fluid to be heated through the fins. The fluid to be heated is directed around the periphery of the liner (between the liner and the jacket), and consecutively through the separate fins, along sinuous and serpentine paths for heating of the fluid by heat transfer from the exhaust gas of the rocket engine.

摘要翻译： 圆柱形火箭发动机排气管具有适合外护套内衬的衬里。 衬套的外周边具有限定用于被加热流体的弯曲路径的周向隔开的肋。 衬里具有至少一个，优选几个横向翅片，其具有内部蛇形通道，用于承载要通过翅片加热的流体。 待加热的流体围绕衬套的周边（在衬套和护套之间）引导，并且沿着弯曲和蛇形路径连续地穿过单独的翅片，用于通过从火箭发动机的废气的热传递来加热流体 。

公开(公告)号：US20110005193A1

公开(公告)日：2011-01-13

申请号：US12803836

申请日：2010-07-06

申请人： Thomas Clayton Pavia ,  James Robert Grote

发明人： Thomas Clayton Pavia ,  James Robert Grote

IPC分类号： F02K9/64

CPC分类号： F02K9/64 ,  F02K9/972 ,  F05D2250/232 ,  F05D2260/202 ,  F05D2260/205

摘要： The invention of this disclosure is methods and apparatuses improving the ease of fabrication and delivered specific impulse performance of simplified rocket engine thrust chambers. Included are a method and apparatus for a pool-boiling cooling system rocket thrust chamber. This cooling system utilizes a convective coolant flowing in a continuous or semi-continuous coolant loop. In addition the convective coolant itself is cooled in a pool-boiling heat exchanger by the evaporation of a propellant that functions as a boiling coolant. The invention also includes a method and apparatus for a shortened, simplified, conical expansion nozzle for a rocket thrust chamber that can operate with reduced specific impulse losses due to nozzle configuration and the use of film coolant in the thrust chamber.

摘要翻译： 本公开的发明是改进简化的火箭发动机推力室的制造容易性和输送特定脉冲性能的方法和装置。 包括一个池沸腾冷却系统火箭推进室的方法和装置。 该冷却系统利用在连续或半连续冷却剂回路中流动的对流冷却剂。 此外，对流冷却剂本身通过作为沸腾冷却剂起作用的推进剂的蒸发在池沸腾热交换器中冷却。 本发明还包括一种用于火箭推进室的缩短的，简化的锥形膨胀喷嘴的方法和装置，其可以由于喷嘴构造而减少的比冲量损失和在推力室中使用薄膜冷却剂来操作。

公开(公告)号：US20100180575A1

公开(公告)日：2010-07-22

申请号：US12748382

申请日：2010-03-27

申请人： Arne Boman

发明人： Arne Boman

IPC分类号： F02K9/64 ,  F02K9/97

CPC分类号： F02K9/972 ,  F02K9/64 ,  F05D2230/60 ,  F05D2230/642 ,  F05D2300/5024 ,  Y10T29/49346

摘要： An engine wall structure includes an inner wall to which hot gas is admitted during engine operation, an outer wall, which is colder than the inner wall during engine operation, and at least two webs that connect the inner wall with the outer wall and delimit a cooling duct between the walls. The webs are mainly formed by a first material and the inner wall is mainly formed by a second material of other composition and other heat conductivity than the first material.

摘要翻译： 发动机壁结构包括在发动机运行期间进入热气体的内壁，在发动机运行期间比内壁冷的外壁，以及连接内壁和外壁的至少两个腹板，并限定一个 墙之间的冷却管道。 网主要由第一材料形成，并且内壁主要由其它组成的第二材料和比第一材料的其他热导率形成。

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。

公开(公告)号：US20090218086A1

公开(公告)日：2009-09-03

申请号：US12147396

申请日：2008-06-26

申请人： Frank A. Sciorelli

发明人： Frank A. Sciorelli

IPC分类号： F28F1/10

CPC分类号： F28D7/1623 ,  F02K9/64 ,  F02K9/972 ,  F02K9/974 ,  F28D21/0003 ,  F28F2265/16

摘要： A cylindrical rocket engine exhaust duct has a liner that fits inside an outer jacket. The outer periphery of the liner has circumferentially spaced ribs defining a sinuous path for a fluid to be heated. The liner has a least one, preferably several, transverse fins with internal serpentine passages for carrying the fluid to be heated through the fins. The fluid to be heated is directed around the periphery of the liner (between the liner and the jacket), and consecutively through the separate fins, along sinuous and serpentine paths for heating of the fluid by heat transfer from the exhaust gas of the rocket engine.

摘要翻译： 圆柱形火箭发动机排气管具有适合外护套内衬的衬里。 衬套的外周边具有限定用于被加热流体的弯曲路径的周向隔开的肋。 衬里具有至少一个，优选几个横向翅片，其具有内部蛇形通道，用于承载要通过翅片加热的流体。 待加热的流体围绕衬套的周边（在衬套和护套之间）引导，并且沿着弯曲和蛇形路径连续地穿过单独的翅片，用于通过从火箭发动机的废气的热传递来加热流体 。

公开(公告)号：US07581385B2

公开(公告)日：2009-09-01

申请号：US11265862

申请日：2005-11-03

申请人： Jorge I. Farah ,  Michael J. Murphy ,  John R. Buey

发明人： Jorge I. Farah ,  Michael J. Murphy ,  John R. Buey

IPC分类号： F02C7/12 ,  F02K1/82

CPC分类号： F02K9/972 ,  F02K1/822 ,  F02K9/64 ,  F05D2250/184 ,  F05D2250/71 ,  F05D2250/713 ,  F05D2260/201 ,  F05D2260/202 ,  Y10T428/234 ,  Y10T428/24149

摘要： A cooling liner having a liner hot sheet formed as a relatively thick iso-grid structure having iso-grid ribs, which extend from a surface between the ribs. A multitude of metering sheets are mounted directly to the liner hot sheet surface. Each metering sheet is mounted to the iso-grid to define a multitude of discrete chambers. A seal is located in a pattern along a subset of the iso-grid ribs to further segregate the surface covered by each metering sheet into a further number of discrete subchambers. Each metering sheet includes a multitude of metering sheet apertures and the surface between the iso-grid ribs of the liner hot sheet include a multitude of hot sheet apertures. By varying the ratio between the number of metering sheet apertures and the number of hot sheet apertures, the pressure in each chamber is defined to efficiently maintain the minimum desired pressure ratio across the hot sheet without undue wastage of cooling airflow.

摘要翻译： 一种具有衬里热板的冷却衬套，其形成为具有等间隔栅格的相对较厚的等栅格结构，其从肋之间的表面延伸。 大量的计量纸直接安装在衬板热板表面上。 每个计量片安装到等电网以限定多个分立的室。 密封沿着等栅格肋的子集位于图案中，以进一步将每个计量片覆盖的表面分离成另外数量的离散子室。 每个计量片材包括多个计量片材孔，并且衬里热片材的异格栅肋之间的表面包括多个热片孔。 通过改变计量纸张孔数与热板孔数之间的比率，每个室中的压力被定义为有效地保持热板上的最小期望压力比，而不会造成冷却气流的不适当浪费。

公开(公告)号：US07343732B2

公开(公告)日：2008-03-18

申请号：US10794390

申请日：2004-03-02

申请人： Ross A. Hewitt

发明人： Ross A. Hewitt

IPC分类号： F02K9/64

CPC分类号： F02K9/64 ,  B64G1/401 ,  F02K9/972

摘要： A combustion chamber/supersonic nozzle assembly is cooled by an array of coolant channels in the wall of the assembly with coolant being fed to the assembly at the throat plane between the subsonic (convergent) and supersonic (divergent) sections. A minor portion of the coolant entering at the throat plane is directed to coolant channels in the supersonic section wall, while the remainder is directed to a complex arrangement of channels in the subsonic section wall. The latter arrangement includes an outer layer of wide axially oriented channels for delivery of coolant to, and removal from, an inner layer of smaller, circumferentially oriented channels that are adjacent to the hot gas and carry the bulk of the coolant load. The path of coolant travel through each inner channel is relatively short, lessening the pressure drop through those channels relative to coolant channel arrangements of the prior art.

摘要翻译： 燃烧室/超音速喷嘴组件通过组件壁中的冷却剂通道阵列冷却，其中冷却剂在亚音速（收敛）和超音速（发散）部分之间的喉部平面处被馈送到组件。 进入喉管平面的冷却剂的一小部分被引导到超声部分壁中的冷却剂通道，而其余部分被引导到亚音速部分壁中的通道的复杂布置。 后一种布置包括宽的轴向定向通道的外层，用于将冷却剂输送到邻近热气体并承载大部分冷却剂负载的较小周向取向的通道的内层和从其移除。 冷却剂通过每个内部通道的路径相对较短，减小了相对于现有技术的冷却剂通道布置的通过这些通道的压降。

公开(公告)号：US20070163228A1

公开(公告)日：2007-07-19

申请号：US11334965

申请日：2006-01-19

申请人： William Brown ,  Peter Schilhavy

发明人： William Brown ,  Peter Schilhavy

IPC分类号： F02K9/42

CPC分类号： F02K9/64 ,  F02K9/42 ,  F02K9/82 ,  F02K9/972 ,  F05D2260/202

摘要： A rocket engine with an augmentation gas system that improves performance of the hypergolic combustion process. The augmentation gas system includes an acoustic cavity manifold mounted between an outer perimeter of an injector face and the combustion chamber. The augmentation gas system injects an augmentation gas active element such as hydrogen or an inactive element such as helium to provide significantly enhanced boundary layer coolant effect to reduce heat loading on the combustion chamber wall and enhance the specific impulse of the rocket engine.

摘要翻译： 具有增强气体系统的火箭发动机，其改善了过程燃烧过程的性能。 增强气体系统包括安装在喷射器面的外周和燃烧室之间的声腔歧管。 增压气体系统注入增压气体活性元素如氢气或诸如氦气的惰性元素，以提供显着增强的边界层冷却剂效果，以减少燃烧室壁上的热负荷并增强火箭发动机的比冲量。

公开(公告)号：US06945032B2

公开(公告)日：2005-09-20

申请号：US10872667

申请日：2004-06-21

申请人： Jan Lundgren

发明人： Jan Lundgren

IPC分类号： B23K26/00 ,  B23K26/20 ,  B23K26/24 ,  B23K26/28 ,  F02K9/64 ,  F02K9/97 ,  F02K9/72

CPC分类号： F02K9/972 ,  B23K26/24 ,  B23K26/282 ,  B23K2101/045 ,  B23K2101/14 ,  B23K2101/18 ,  Y10T29/49346 ,  Y10T29/49995

摘要： A wall structure capable of withstanding high thermal load, including a wall structure with an inner wall, an outer wall positioned about the inner wall, and distancing elements located between the inner and outer walls. The distancing elements are joined to at least one of the inner and outer walls by means of laser welding and thereby establishing a plurality of cooling ducts between the inner and outer walls and a weld joint formed by the laser welding and having a cross-section taken through the wall structure that is substantially T-shaped and which displays a rounded shape towards an inside one of the plurality of cooling ducts.

摘要翻译： 能够承受高热负荷的壁结构，包括具有内壁的壁结构，围绕内壁定位的外壁和位于内壁和外壁之间的间隔元件。 隔离元件通过激光焊接连接到内壁和外壁中的至少一个，从而在内壁和外壁之间建立多个冷却管道，以及通过激光焊接形成的具有横截面的焊接接头 通过大致T形的壁结构，并且朝向多个冷却管道的内侧显示圆形。

公开(公告)号：US06907662B2

公开(公告)日：2005-06-21

申请号：US10370536

申请日：2003-02-20

申请人： Jan Lundgren

发明人： Jan Lundgren

IPC分类号： B23K26/00 ,  B23K26/20 ,  B23K26/24 ,  B23K26/28 ,  F02K9/64 ,  F02K9/97 ,  B21D53/00 ,  F02K1/00

CPC分类号： F02K9/972 ,  B23K26/24 ,  B23K26/282 ,  B23K2101/045 ,  B23K2101/14 ,  B23K2101/18 ,  Y10T29/49346 ,  Y10T29/49995

摘要： Methods for manufacturing outlet nozzles for use in rocket motors are disclosed. The methods include providing an inner wall, positioning an outer wall around the inner wall, positioning spacers in the space between the inner and outer walls, and laser welding between the spacers and at least one of the inner and outer walls in order to form cooling ducts between the spacers and to provide T-shaped joints between the spacers and at least one of the inner and outer walls, the T-shaped joints including a rounded shape within the cooling ducts.

摘要翻译： 公开了用于制造用于火箭发动机的出口喷嘴的方法。 所述方法包括提供内壁，围绕内壁定位外壁，将间隔件定位在内壁和外壁之间的空间中，以及在间隔件与内壁和外壁中的至少一个之间的激光焊接以形成冷却 并且在间隔件和内壁和外壁中的至少一个之间提供T形接头，T形接头在冷却管道内包括圆形形状。