公开(公告)号：US20030230071A1

公开(公告)日：2003-12-18

申请号：US10250012

申请日：2003-05-28

Applicant: VOLVO AERO CORPORATION

Inventor： Jan Haggander

IPC: F02K009/64

CPC classification number: F02K9/64 ,  F05D2230/90 ,  F05D2300/50212 ,  F05D2300/5024

Abstract: A wall structure (2) configured to be exposed to a thermal load. The wall structure having at least two layers including a first layer (5) and a second layer (6). The second layer (6) is located closer to a source of the thermal load than the first layer (5), and the layers (5, 6) are arranged so that heat is allowed to be conducted from the second layer (6) to the first layer (5). Each of the first and second layers (5, 6) are adapted to carry a significant portion of a structural load, and the second layer (6) exhibits a higher thermal conductivity and/or a lower thermal expansion than the first layer (5). The invention reduces the thermal strain in the wall structure (2).

Abstract translation: 构造成暴露于热负荷的壁结构（2）。 所述壁结构具有包括第一层（5）和第二层（6）的至少两层。 第二层（6）位于比第一层（5）更靠近热负荷的源处，并且布置层（5,6），使得允许热从第二层（6）传导到 第一层（5）。 第一层和第二层（5,6）中的每一个适于承载结构负载的重要部分，并且第二层（6）表现出比第一层（5）更高的热导率和/或较低的热膨胀， 。 本发明减少了壁结构（2）中的热应变。

公开(公告)号：US20030209589A1

公开(公告)日：2003-11-13

申请号：US10139659

申请日：2002-05-07

Applicant: General Electric Company

Inventor： Wayne Charles Hasz ,  Venkat S. Venkataramani ,  Ching-Pang Lee

IPC: B23K031/02

CPC classification number: B23P15/008 ,  B81B1/00 ,  C23C4/01 ,  C23C4/18 ,  C23C26/00 ,  C23C26/02 ,  C23C28/3215 ,  C23C28/3455 ,  F01D5/18 ,  F01D5/288 ,  F02K9/64 ,  F23R3/002 ,  F23R3/005 ,  Y02T50/67 ,  Y10T29/49321 ,  Y10T29/49341 ,  Y10T29/49812

Abstract: A method for forming a channel within a coated, metal-based substrate is described. In one technique, a channel-forming material is first deposited on the substrate, followed by the deposition of a bonding agent, such as a braze. One or more coatings can then be applied over the substrate. In one embodiment, the channel is formed when the channel-forming material is subsequently removed. In another embodiment, the channel is formed due to the lack of adhesion between particular channel-forming materials and the overlying bonding agent. Related articles are also described, e.g., gas turbine components which include protective coatings and a pattern of cooling channels.

Abstract translation: 描述了在涂覆的金属基底中形成通道的方法。 在一种技术中，首先在基底上沉积通道形成材料，然后沉积粘合剂，例如钎焊。 然后可以在衬底上施加一个或多个涂层。 在一个实施例中，当通道形成材料随后被去除时，形成通道。 在另一个实施方案中，由于在特定的通道形成材料和上覆粘合剂之间缺乏粘合而形成通道。 还描述了相关文章，例如包括保护涂层和冷却通道图案的燃气涡轮机部件。

公开(公告)号：US06637188B2

公开(公告)日：2003-10-28

申请号：US09985313

申请日：2001-11-02

Applicant: Peter Bichler ,  Hans Immich ,  Joachim Kretschmer ,  Günther Schmidt

Inventor： Peter Bichler ,  Hans Immich ,  Joachim Kretschmer ,  Günther Schmidt

IPC: F02K942

CPC classification number: F02K9/64

Abstract: A combustion chamber for a rocket engine expels a hot stream of gas and has a cooling device. The inner wall of the combustion chamber adjoins the cooling device and contains depressions formed in such a way that the stable outer layer of the stream of gas that forms in the proximity of the inner wall of the combustion chamber during operation of the combustion chamber is destabilized in the area of the depressions.

Abstract translation: 用于火箭发动机的燃烧室排出热气流，并具有冷却装置。 燃烧室的内壁与冷却装置相邻并且包含凹陷，其形成为使得在燃烧室操作期间在燃烧室的内壁附近形成的气体流的稳定外层不稳定 在洼地的地区。

公开(公告)号：US06606851B1

公开(公告)日：2003-08-19

申请号：US09946630

申请日：2001-09-06

Applicant: Joseph Roger Herdy, Jr. ,  Michel Roger Kamel ,  Jacob Brian Lopata

Inventor： Joseph Roger Herdy, Jr. ,  Michel Roger Kamel ,  Jacob Brian Lopata

IPC: F02K964

CPC classification number: F02K9/64 ,  B33Y80/00 ,  C23C4/137 ,  C23C4/185 ,  F02K9/972 ,  F05D2260/203 ,  Y10T29/49346

Abstract: A rocket engine having a combustion chamber with a chamber inner wall, a throat with a throat inner wall, and a nozzle with a nozzle inner wall is provided. The chamber inner wall is a vacuum plasma sprayed metal, the throat inner wall is a vacuum plasma sprayed metal, and the nozzle inner wall is a vacuum plasma sprayed metal. The porosity of the vacuum plasma sprayed metal varies in an axial direction of the engine.

Abstract translation: 提供具有燃烧室的火箭发动机，其具有室内壁，具有喉部内壁的喉部和具有喷嘴内壁的喷嘴。 腔室内壁是真空等离子喷涂金属，喉部内壁是真空等离子体喷涂金属，喷嘴内壁是真空等离子喷涂金属。 真空等离子喷涂金属的孔隙率在发动机的轴向方向上变化。

公开(公告)号：US06601380B2

公开(公告)日：2003-08-05

申请号：US09964294

申请日：2001-09-26

Applicant: William H. Knuth ,  Martin J. Chiaverini ,  Daniel J. Gramer

Inventor： William H. Knuth ,  Martin J. Chiaverini ,  Daniel J. Gramer

IPC: C06D500

CPC classification number: F23C3/006 ,  F02K9/52 ,  F02K9/62 ,  F02K9/64 ,  F23R3/58

Abstract: A hybrid rocket engine and a method for propelling a rocket utilizing a vortex flow field. The flow field includes an outer fluid vortex spiraling toward a closed end of the flow field generating apparatus and an inner fluid vortex substantially concentric with the outer vortex spiraling away from the closed end and toward an outlet opening in which the inner vortex spirals in the same direction as the outer vortex, but in the opposite axial direction. The invention also relates to a rocket propulsion system utilizing the flow field in which the propulsion system includes a combustion chamber with a fuel source and an oxidizer source that deliver the said fuel and said oxidizer to the said outer and inner vortexes in a manner to support a combustion process while flowing along the flow field.

公开(公告)号：US20020069636A1

公开(公告)日：2002-06-13

申请号：US09964294

申请日：2001-09-26

Inventor： William H. Knuth ,  Martin J. Chiaverini ,  Daniel J. Gramer

IPC: F02K009/72

CPC classification number: F23C3/006 ,  F02K9/52 ,  F02K9/62 ,  F02K9/64 ,  F23R3/58

Abstract: A hybrid rocket engine and a method for propelling a rocket utilizing a vortex flow field. The flow field includes an outer fluid vortex spiraling toward a closed end of the flow field generating apparatus and an inner fluid vortex substantially concentric with the outer vortex spiraling away from the closed end and toward an outlet opening in which the inner vortex spirals in the same direction as the outer vortex, but in the opposite axial direction. The invention also relates to a rocket propulsion system utilizing the flow field in which the propulsion system includes a combustion chamber with a fuel source and an oxidizer source that deliver the said fuel and said oxidizer to the said outer and inner vortexes in a manner to support a combustion process while flowing along the flow field.

Abstract translation: 混合火箭发动机和利用涡流场推进火箭的方法。 流场包括朝向流场发生装置的封闭端螺旋的外部流体涡流和与外部涡流基本上同心的内部流体涡流，该外部涡流远离封闭端螺旋形并且朝向出口开口，内部涡流在其中相同 方向作为外涡流，但在相反的轴向。 本发明还涉及一种利用流场的火箭推进系统，其中推进系统包括具有燃料源的燃烧室和氧化剂源，该燃料源和氧化剂源以支撑的方式将所述燃料和所述氧化剂输送到所述外涡流和内涡流 燃烧过程，同时沿着流场流动。

公开(公告)号：US06220016B1

公开(公告)日：2001-04-24

申请号：US09522817

申请日：2000-03-10

Applicant: Guido D. Defever ,  Robert S. Thompson, Jr.

Inventor： Guido D. Defever ,  Robert S. Thompson, Jr.

IPC: F02K1100

CPC classification number: F02K9/52 ,  F02K9/48 ,  F02K9/62 ,  F02K9/64 ,  F02K9/66 ,  F02K9/72 ,  F05D2240/40

Abstract: A rocket engine comprises first and second combustion chambers with respective combustion chamber liners bounding respective annular passages, wherein the first combustion chamber discharges into the second, and the respective annular passages are in fluid communication with one another. A portion of the effluent from the first combustion chamber flows from the first combustion chamber to the second combustion chamber through the respective annular passages via orifices in the respective combustion chamber liners, so as to provide for effusion cooling of a surface of the second combustion chamber. The first combustion chamber preferably operates fuel rich, reducing the temperature of the effusion cooling gases, which may be further cooled by a portion of unburned fuel. A flow restriction such as a turbine between the first and second combustion chambers provides a pressure differential therebetween that induces flow of effusion cooling gases.

Abstract translation: 火箭发动机包括第一和第二燃烧室，其中相应的燃烧室衬套限定相应的环形通道，其中第一燃烧室排放到第二燃烧室中，并且相应的环形通道彼此流体连通。 来自第一燃烧室的流出物的一部分通过相应的环形通道经由各个燃烧室衬套中的孔从第一燃烧室流到第二燃烧室，以便提供第二燃烧室的表面的积液冷却 。 第一燃烧室优选地运行富燃料，降低了可以被一部分未燃烧燃料进一步冷却的排出冷却气体的温度。 在第一和第二燃烧室之间的诸如涡轮机之类的流量限制件提供了它们之间的压力差，其引起渗出冷却气体的流动。

公开(公告)号：US06209199B1

公开(公告)日：2001-04-03

申请号：US09271394

申请日：1999-03-17

Applicant: Daniel Cornu ,  Christophe Verdy ,  Jean-Michel De Monicault ,  Christian Coddet

Inventor： Daniel Cornu ,  Christophe Verdy ,  Jean-Michel De Monicault ,  Christian Coddet

IPC: B23P1500

CPC classification number: B23P15/008 ,  B23P15/26 ,  C23C4/137 ,  F02K9/64 ,  Y10T29/49336 ,  Y10T29/49346

Abstract: A regenerative circuit structure is built up by implementing the following steps in particular: an intermediate layer is made on a support core representing the inner profile of the structure; a series of channels regularly distributed around the core is made with the channels opening to face the intermediate layer, each of the channels being provided with a soluble insert; the support core is preheated and the body of the structure is made by thermal spraying under a vacuum; channels are machined in the body from the outside, and said channels are filled by means of soluble inserts; a closure layer is formed to close the channels in the body, and an outer envelope is formed by thermal spraying under a vacuum, after preheating; and all of the soluble inserts and the intermediate layer are eliminated.

Abstract translation: 通过实施以下步骤来构建再生电路结构：在表示该结构的内部轮廓的支撑芯上形成中间层;围绕芯部规则分布的一系列通道被制成，通道开口面对 中间层，每个通道设置有可溶性插入物;支撑芯被预热，并且结构的主体通过真空下的热喷涂制成;通道从外部在主体中加工，并且所述通道由 手段的可溶性插入物;形成闭合层以封闭体内的通道，并且在预热之后通过真空热喷涂形成外壳; 并且所有可溶性插入物和中间层都被去除。

公开(公告)号：US6151887A

公开(公告)日：2000-11-28

申请号：US270481

申请日：1999-03-15

Applicant: Oskar Haidn ,  Hermann Hald ,  Michael Lezuo ,  Peter Winkelmann

Inventor： Oskar Haidn ,  Hermann Hald ,  Michael Lezuo ,  Peter Winkelmann

IPC: C04B35/80 ,  F02K9/64 ,  F02K9/97

CPC classification number: F02K9/64 ,  F02K9/972

Abstract: In order to provide a combustion chamber, in particular for a rocket engine, comprising a combustion area, an inner shell surrounding the combustion area, an outer shell surrounding the inner shell and coolant passages formed between the inner shell and the outer shell, the casing of which has an improved thermal stability and an increased mechanical bearing strength, it is suggested in accordance with the invention that the outer shell be formed from a fibrous ceramic material and the inner shell be formed from a fibrous ceramic material or from graphite.

Abstract translation: 为了提供特别是用于火箭发动机的燃烧室，包括燃烧区域，围绕燃烧区域的内壳，围绕内壳的外壳和形成在内壳和外壳之间的冷却剂通道，壳体 其具有改进的热稳定性和增加的机械承载强度，根据本发明提出，外壳由纤维状陶瓷材料形成，内壳由纤维状陶瓷材料或石墨形成。

公开(公告)号：US6052987A

公开(公告)日：2000-04-25

申请号：US970915

申请日：1997-11-14

Applicant: Gordon A. Dressler

Inventor： Gordon A. Dressler

IPC: F02G5/00 ,  F02K9/44 ,  F02K9/64 ,  F02K9/42

CPC classification number: F02K9/64 ,  F05D2260/205

Abstract: A space craft's rocket engines are cooled by a recirculating cooling system containing a non-propellant coolant fluid, such as water and/or ethylene glycol. With that recirculating cooling system to maintain the rocket engine combustion chamber at a lower temperature, spacecraft rocket engines may be constructed less expensively and can operate with greater safety by employing the more common metals in their construction. The cooling system also provides an easy means to warm and/or vaporize a propellant.

Abstract translation: 太空飞船的火箭发动机通过包含非推进剂冷却剂流体（例如水和/或乙二醇）的循环冷却系统来冷却。 利用该再循环冷却系统将火箭发动机燃烧室维持在较低的温度，宇宙飞船火箭发动机的建造成本较低，并且可以通过在其结构中采用更常见的金属在更大的安全性下运行。 冷却系统还提供了一种用于温热和/或蒸发推进剂的简单方法。