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1. 发明授权

US07735311B2 Pulsed detonation engines manufactured from materials having low thermal stability 有权
标题翻译：由具有低热稳定性的材料制成的脉冲引爆发动机
公开(公告)号：US07735311B2
公开(公告)日：2010-06-15
申请号：US10730020
申请日：2003-12-09
申请人： Shmuel Eidelman , Dimitrios Lianos
发明人： Shmuel Eidelman , Dimitrios Lianos
IPC分类号： F02K5/02
CPC分类号： B64G1/40 , F02K9/60 , F02K9/68 , Y10S60/909
摘要： Pulsed detonation engines (PDEs), or various components thereof, such as the detonation chamber and/or nozzle, can be economically constructed from materials having low thermal stability, such as plastics, composites, and light metals. During operation, the intermittent injection and detonation of reactants produces a motive force (e.g., thrust) over relatively short intervals useful in orbit control and the like. The relatively short intervals of operation prevent temperatures of the PDE components from reaching temperatures that would result in their dimensional failure.
摘要翻译：脉冲引爆发动机（PDE）或其各种部件，例如爆轰室和/或喷嘴，可以由具有低热稳定性的材料如塑料，复合材料和轻金属经济地构造。在操作期间，反应物的间歇注入和引爆在相当短的间隔中产生在轨道控制等中有用的动力（例如推力）。相对较短的操作间隔可防止PDE组件的温度达到导致其尺寸失效的温度。

2. 发明授权

US06195984B1 Rocket engine thrust chamber assembly 失效
公开(公告)号：US06195984B1
公开(公告)日：2001-03-06
申请号：US09228034
申请日：1998-12-10
申请人： Charles S. Cornelius , Richard H. Counts , W. Neill Myers , Jeffrey D. Lackey , Warren Peters , Michael D. Shadoan , David L. Sparks , Timothy W. Lawrence
发明人： Charles S. Cornelius , Richard H. Counts , W. Neill Myers , Jeffrey D. Lackey , Warren Peters , Michael D. Shadoan , David L. Sparks , Timothy W. Lawrence
IPC分类号： F02K900
CPC分类号： F02K9/974 , B29C53/585 , B29L2031/3097 , F02K9/62 , F02K9/97 , Y10S60/909
摘要： A thrust chamber assembly for liquid fueled rocket engines and the method of making it wherein a two-piece mandrel having the configuration of an assembly having a combustion chamber portion connected to a nozzle portion through a throat portion is wrapped with a silica tape saturated with a phenolic resin, the tape extending along the mandrel and covering the combustion chamber portion of the mandrel to the throat portion. The width of the tape is positioned at an angle of 30 to 50° to the axis of the mandrel such that one edge of the tape contacts the mandrel while the other edge is spaced from the mandrel. The phenolic in the tape is cured and the end of the wrap is machined to provide a frustoconical surface extending at an angle of 15 to 30° with respect to the axis of the mandrel for starting a second wrap on the mandrel to cover the throat portion. The remainder of the mandrel is wrapped with a third silica tape having its width positioned at a angle of 5 to 20° from the axis of the mandrel. The resin in the third tape is cured and the assembly is machined to provide a smooth outer surface. The entire assembly is then wrapped with a tow of graphite fibers wetted with an epoxy resin and, after the epoxy resin is cured, the graphite is machined to final dimensions.

3. 发明授权

US5771680A Stiffened composite structures and method of making thereof 失效
标题翻译：加固复合结构及其制造方法
公开(公告)号：US5771680A
公开(公告)日：1998-06-30
申请号：US576249
申请日：1995-12-21
申请人： Ahmad P. Zahedi , Stephen C. Mitchell
发明人： Ahmad P. Zahedi , Stephen C. Mitchell
IPC分类号： B32B15/14 , F01D25/24 , F02C2/20
CPC分类号： F01D25/24 , B32B15/14 , Y02T50/672 , Y10S60/909 , Y10T156/1002 , Y10T428/1362 , Y10T428/1369
摘要： A stiffened composite is provided exhibiting multi-directional reinforcement with continuous long fibers. The composite has a substrate and serpentine stiffeners adhered thereto. The stiffeners merge toward, join with and diverge from adjacent stiffeners to provide a stiffener matrix on the substrate. The serpentine stiffener permit the matrix to exhibit multi-directional reinforcement with the continuous long fibers within the serpentine ribs. The composite structures are useful as aircraft bypass ducts, and as other composite products.
摘要翻译：提供了具有连续长纤维的多方向加强件的加强复合材料。复合材料具有粘附到其上的基底和蛇形加强件。加强件与相邻的加强件相融合并与其分离，以在基板上提供加强筋基体。蛇形加强筋允许基体在蜿蜒肋内连续的长纤维展现出多方向的增强。复合结构可用作飞机旁路管道以及其他复合材料。

4. 发明授权

US5749229A Thermal spreading combustor liner 失效
标题翻译：热扩散燃烧器衬套
公开(公告)号：US5749229A
公开(公告)日：1998-05-12
申请号：US542982
申请日：1995-10-13
申请人： Nesim Abuaf , Steven George Goebel
发明人： Nesim Abuaf , Steven George Goebel
IPC分类号： F02K1/82 , F23R3/00 , F02C1/00
CPC分类号： F23R3/002 , F02K1/82 , F05D2260/201 , F23R2900/03044 , Y02T50/67 , Y02T50/675 , Y10S60/909 , Y10T428/12611
摘要： A combustor liner includes an inner layer for facing combustion gases, and an opposite outer layer for facing a cooling fluid. The outer layer has a greater coefficient of thermal conductivity than the inner layer for reducing temperature gradients in the liner. In a preferred embodiment, the outer layer significantly reduces temperature gradients in the liner which are caused by the varying cooling ability of impingement cooling air jets for more uniformly cooling the combustor liner and reducing the maximum temperature thereof.
摘要翻译：燃烧器衬套包括用于面对燃烧气体的内层和用于面对冷却流体的相对的外层。外层具有比内层更大的导热系数，用于降低内衬中的温度梯度。在一个优选实施例中，外层显着降低了衬套中的温度梯度，这是由冲击冷却空气射流变化的冷却能力引起的，用于更均匀地冷却燃烧器衬套并降低其最大温度。

5. 发明授权

US5725692A Nickel base superalloy articles with improved resistance to crack propagation 失效
标题翻译：镍基超合金制品具有改善的抗裂纹扩展能力
公开(公告)号：US5725692A
公开(公告)日：1998-03-10
申请号：US537341
申请日：1995-10-02
申请人： Daniel P. DeLuca , Charles M. Biondo , Howard B. Jones , Chris C. Rhemer
发明人： Daniel P. DeLuca , Charles M. Biondo , Howard B. Jones , Chris C. Rhemer
IPC分类号： C22C19/03 , C22C19/05 , C22F1/10
CPC分类号： C22F1/10 , C22C19/055 , C22C19/056 , C22C19/057 , C22C19/058 , Y10S60/909
摘要： The present invention relates to a heat treated, gamma prime precipitation strengthened nickel base alloy having an improved resistance to hydrogen embrittlement, particularly crack propagation. The alloy has a microstructure which is essentially free of script carbides, gamma--gamma prime eutectic islands and porosity. The microstructure further includes a plurality of regularly occurring large barrier gamma prime precipitates and a continuous field of fine cuboidal gamma prime precipitates surrounding the large barrier gamma prime precipitates.
摘要翻译：本发明涉及具有改善的耐氢脆性，特别是裂纹扩展的经热处理的γ'析出强化镍基合金。该合金具有基本上没有脚本碳化物，γ-γ初始共晶岛和孔隙率的微结构。微结构进一步包括多个规则存在的大阻挡γ原子沉淀物和围绕大阻挡γ'析出物的细长方体γ'沉淀物的连续场。

6. 发明授权

US5439750A Titanium metal matrix composite inserts for stiffening turbine engine components 失效
标题翻译：用于加固涡轮发动机部件的钛金属基体复合材料刀片
公开(公告)号：US5439750A
公开(公告)日：1995-08-08
申请号：US76670
申请日：1993-06-15
申请人： Richard Ravenhall , Charles R. Wojciechowski , Stephen C. Mitchell , Gary D. Mercer , Thomas J. Kelly , Melvin A. Schobert , Harvey M. Maclin
发明人： Richard Ravenhall , Charles R. Wojciechowski , Stephen C. Mitchell , Gary D. Mercer , Thomas J. Kelly , Melvin A. Schobert , Harvey M. Maclin
IPC分类号： C22C1/10 , F01D5/28 , B32B15/02
CPC分类号： F01D5/282 , C22C1/1036 , Y02T50/672 , Y10S60/909 , Y10T428/12486
摘要： A cast article having a reinforced structural composite core is disclosed. The cast article includes a structural element which is embedded in the otherwise cast metal article. The structural element is comprised of a metal matrix composite structural core. It includes a plurality of reinforcing fibers within a metal matrix. The fibers are generally a non-metallic material such as a ceramic which degrade at a temperature below the melting temperature of the cast metal comprising the article. The metal matrix composite structural core is encased with a sheath. The sheath, attached to and completely surrounding the core, is made of the same metal as the cast metal article. In a preferred embodiment, the article is a titanium alloy strut for a gas turbine engine.
摘要翻译：公开了一种具有增强结构复合芯的铸造制品。铸造制品包括嵌入另外的铸造金属制品中的结构元件。结构元件由金属基复合结构芯构成。它在金属基体内包括多个增强纤维。纤维通常是非金属材料，例如陶瓷，其在低于包含制品的铸造金属的熔融温度的温度下降解。金属基复合结构芯被护套包裹。附着在并完全围绕芯的护套由与铸造金属制品相同的金属制成。在优选实施例中，制品是用于燃气涡轮发动机的钛合金支柱。

7. 发明授权

US4787202A Combustion chamber for rocket motor and its assembling method 失效
标题翻译：火箭发动机燃烧室及其组装方法
公开(公告)号：US4787202A
公开(公告)日：1988-11-29
申请号：US5647
申请日：1987-01-21
申请人： Dino Crapiz
发明人： Dino Crapiz
IPC分类号： F02K9/62 , B29C65/54 , B29K105/06 , B29L22/00 , F02K9/34 , F16B11/00 , F02K9/08
CPC分类号： F16B11/006 , F02K9/343 , Y10S60/909
摘要： Combustion chamber for rocket motor of the type comprising two domes, interconnected by a cylindrical shell, each of said domes and the intermediate shell being produced from a filamentary composite material, in which each dome comprises a slightly conical skirt of which the external face is joined over at least part of its length to the inner face of the shell, via a split cylindro-conical connection ring and at least opposite the conical skirt of the dome, one conical face having the same conicity as the conical skirt, the assembling of the three elements to be connected, i.e. dome, shell and ring, being achieved by adhesive bonding.
摘要翻译：用于火箭发动机的燃烧室包括由圆柱形壳体相互连接的两个圆顶，每个所述穹顶和中间壳体均由丝状复合材料制成，其中每个穹顶包括稍微锥形的裙部，其外表面被连接通过分开的圆锥形连接环并且至少与圆顶的圆锥形裙部相对的方式，至少部分长度至少部分地延伸到壳体的内表面，一个锥形面具有与锥形裙部相同的锥度，要连接的三个元件，即圆顶，外壳和环，通过粘合剂粘合来实现。

8. 发明授权

US4552070A Insulating layer for solid fuel rocket engines 失效
标题翻译：固体燃料火箭发动机绝缘层
公开(公告)号：US4552070A
公开(公告)日：1985-11-12
申请号：US411514
申请日：1982-08-25
申请人： Heinz G. Langer
发明人： Heinz G. Langer
IPC分类号： F02K9/34 , F42B15/00
CPC分类号： F02K9/346 , Y10S60/909
摘要： A solid fuel rocket engine comprises a casing which defines a combustion chamber with a solid propellant charge in the combustion chamber and an insulating layer of a water containing alkali silicate and fibers disposed between the casing and the charge. The layer is a type which will froth at a predetermined temperature which occurs during burn off of the propellant charge so that it increases in its thickness dimension in the area of the hot gases which develop and provides an adequate insulation. A method of producing the layer comprises heating the alkali silicate layer to a temperature in which it becomes plastic and sheathing the propellant charge with the plastic layer. Thereafter the sheath charge is inserted into the combustion chamber casing leaving an annular gap between this layer and combustion chamber casing. Thereafter heat is applied to the vicinity of the chamber to cause the layer to froth and expand to close the annular gap. It is advantageous to include a lining of a plastic alkali layer in addition to the layer which sheaths the propellant charge between it and the casing. In addition, it is sometimes advantageous to add a plastic foam material in the gap between the sheath, the cover charge and the casing.
摘要翻译：固体燃料火箭发动机包括壳体，其限定在燃烧室中具有固体推进剂装料的燃烧室，以及设置在壳体和电荷之间的含有碱性硅酸盐和纤维的水的绝缘层。该层是在燃烧期间发生的预定温度下发泡的类型，使得其在发生并提供足够绝缘的热气体的区域中其厚度尺寸增加。制造该层的方法包括将碱金属硅酸盐层加热至其变成塑料的温度，并用塑料层包覆推进剂电荷。此后，护套电荷被插入到燃烧室壳体中，在该层与燃烧室壳体之间留下环形间隙。此后，将热量施加到室附近，使得该层起泡沫并膨胀以封闭环形间隙。除了在其与壳体之间的推进剂电荷的鞘之外，还包括塑料碱层的衬里是有利的。此外，有时在塑料泡沫材料的护套，覆盖物和壳体之间的间隙中加入塑料泡沫材料是有利的。

9. 发明授权

US4414181A Gas generator outlet having controlled temperature transition 失效
标题翻译：气体发生器出口具有受控的温度转换
公开(公告)号：US4414181A
公开(公告)日：1983-11-08
申请号：US317712
申请日：1981-11-02
申请人： Edward J. Ford, Jr.
发明人： Edward J. Ford, Jr.
IPC分类号： B01J19/02
CPC分类号： B01J19/02 , B01J2219/0236 , Y10S60/909
摘要： A gas generator outlet manufactured of different metals, each possessing ferent thermal capability, welded together with a tapered internal insulation system. The generator outlet is designed to contain a high-pressure gas having a flame temperature of 3000.degree. F. The external surface of the gas generator outlet remains at or below 600.degree. F. while the outlet interfaces with a metal manifold having a temperature of approximately 3000.degree. F.
摘要翻译：一种由不同金属制成的气体发生器出口，每个具有不同的热能，与锥形内部绝缘系统焊接在一起。发电机出口被设计成容纳火焰温度为3000°F的高压气体。气体发生器出口的外表面保持在或低于600°F，而出口与金属歧管的温度约为 3000°F

10. 发明授权

US4150540A Rocket nozzle system 失效
标题翻译：火箭喷嘴系统
公开(公告)号：US4150540A
公开(公告)日：1979-04-24
申请号：US787676
申请日：1977-04-14
申请人： Harold A. Krayenbuhl , Gene Dolgonas , Charles J. Rogers
发明人： Harold A. Krayenbuhl , Gene Dolgonas , Charles J. Rogers
IPC分类号： F02K9/30 , F02K9/97 , F02K9/04
CPC分类号： F02K9/30 , F02K9/97 , F02K9/974 , Y10S60/909
摘要： An improved rocket nozzle system having a closure insulator located adjacent the combustion chamber of a rocket engine. The closure insulator has formed as an integral part thereof a plurality of nozzles. Each of the nozzles has incorporated therein a throat insert of pyrolized graphite cloth laminate and a consumable washer. The entire closure insulator assembly including nozzles is transfer molded as one piece into a steel housing. The housing is mounted on the combustion chamber thereby providing an effective nozzle system which is reliably operable under high temperature operation.
摘要翻译：一种改进的火箭喷嘴系统，其具有邻近火箭发动机的燃烧室的闭合绝缘体。闭合绝缘体作为其整体部分形成多个喷嘴。每个喷嘴都加入了热解石墨布层压板和消耗式洗衣机的喉部插入件。包括喷嘴的整个闭合绝缘体组件被一体地转移模制到钢壳体中。壳体安装在燃烧室上，从而提供一种在高温操作下可靠操作的有效喷嘴系统。

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