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1. 发明授权

US06968697B2 Integral compressor housing of gas turbine engines 失效
公开(公告)号：US06968697B2
公开(公告)日：2005-11-29
申请号：US10666611
申请日：2003-09-17
申请人： Ly D. Nguyen , Cristopher Frost , Ronald P. Maty , John M. Wait , Jason C. Smoke , Lori M. Wheeler , Richard D. Kocher
发明人： Ly D. Nguyen , Cristopher Frost , Ronald P. Maty , John M. Wait , Jason C. Smoke , Lori M. Wheeler , Richard D. Kocher
IPC分类号： F02C6/08 , F02C7/00 , F02C7/04 , F02C7/26
CPC分类号： F02C7/20 , F02C7/06 , F04D29/4206 , F05D2230/52 , Y02T50/672
摘要： A turbine engine compressor design utilizing multiple component integration, thereby reducing the number of required engine components. In conventional compressor designs, a multiple component system makes it difficult to predict the structural behaviors due to thermal and mechanical loading during transient conditions. The compressor design of the present invention has three main parts: a forward bearing housing, a bell-mouth (heat shield) and a coupled impeller shroud/diffuser. Such a design achieves the design objectives of the present invention, including reducing weight, reducing cost, minimizing tolerance build up and improving aerodynamic performance by utilizing multiple component integration for multiple modes of engine operation.

2. 发明授权

US07097411B2 Turbomachine compressor scroll with load-carrying inlet vanes 失效
标题翻译：涡轮机压缩机蜗轮带有承载入口叶片
公开(公告)号：US07097411B2
公开(公告)日：2006-08-29
申请号：US10829114
申请日：2004-04-20
申请人： Jason C. Smoke , Cristopher Frost , Richard D. Kocher , Jeff D. Guymon , Ly D. Nguyen
发明人： Jason C. Smoke , Cristopher Frost , Richard D. Kocher , Jeff D. Guymon , Ly D. Nguyen
IPC分类号： F01D1/02 , F04D29/44
CPC分类号： F04D29/444 , F01D9/026 , F04D29/624 , F05D2220/40 , F05D2250/52
摘要： A compressor scroll housing for use in conjunction with turbo-machinery, particularly applicable in aircraft. The scroll housing can include a plurality of scroll vanes arrayed around the scroll housing. Scroll vanes, integrally formed with the scroll housing, carry stress load on the scroll housing, including the load from fluid pressure within the scroll and carcass loading from the engine. The plurality of scroll vanes adapted for guiding flow of fluid from an inlet to an outlet while supporting the scroll housing. Chord length and cross sectional area of each scroll vane can be sized to maintain an equal stress in all scroll vanes. A method of making the scroll housing for use with an impeller connected to an engine is disclosed, as well as a method of operating turbo-machinery including supporting a load on the scroll housing with scroll vanes while maintaining an equal stress on each scroll vane.
摘要翻译：一种与涡轮机械结合使用的压缩机涡旋壳体，特别适用于飞机。涡旋壳体可以包括围绕涡旋壳体排列的多个涡旋叶片。与涡旋壳体一体形成的涡旋叶片在涡旋壳体上承受应力负荷，包括来自涡卷内的流体压力的负载和来自发动机的胎体负载。多个涡旋叶片适于在支撑涡旋壳体的同时引导流体从入口到出口的流动。每个涡旋叶片的弦长和横截面面积的尺寸可以确保在所有涡旋叶片中保持相等的应力。公开了一种制造与连接到发动机的叶轮一起使用的涡旋壳体的方法，以及一种操作涡轮机械的方法，包括在涡轮叶片上支撑负载，同时在每个涡旋叶片上保持相等的应力。

3. 发明授权

US07094024B2 Performance and durability improvement in compressor structure design 失效
标题翻译：压缩机结构设计的性能和耐久性改进
公开(公告)号：US07094024B2
公开(公告)日：2006-08-22
申请号：US10759928
申请日：2004-01-15
申请人： Ly D. Nguyen , Lori M. Wheeler , Greg Ockenfels , Darrell K. James , George E. Zurmehly
发明人： Ly D. Nguyen , Lori M. Wheeler , Greg Ockenfels , Darrell K. James , George E. Zurmehly
IPC分类号： F04D29/44
CPC分类号： F02C7/04 , F04D29/4206 , F04D29/444 , F04D29/681 , F05D2220/50 , Y10T29/49236
摘要： An integral assembly that may improve control over thermal and mechanical behaviors of assembly structures during various transient operation conditions is disclosed. The integral assembly comprises a continuous ring disposed coaxial with, and orthogonal to a central axis, the continuous ring comprising a plurality of surfaces, the plurality of surfaces having a continuous outer surface and a continuous inner surface; the plurality of surfaces being characterized by a continuous cross section having a first cross sectional dimension longitudinally disposed parallel to the central axis; the plurality of surfaces comprising a bell mouth surface in physical communication with a compressor shroud surface; the compressor shroud surface being in physical communication with a diffuser surface; and the diffuser surface being in physical communication with the bell mouth surface. The integral assembly comprising a compressor shroud is also provided. An auxiliary power unit including the integral assembly, and a method of making the integral assembly are also disclosed.
摘要翻译：公开了一种整体组件，其可以在各种瞬态操作条件期间改善对组装结构的热和机械特性的控制。整体组件包括与中心轴同轴并且与中心轴正交的连续环，连续环包括多个表面，多个表面具有连续的外表面和连续的内表面; 所述多个表面的特征在于具有平行于所述中心轴线纵向设置的第一横截面尺寸的连续横截面; 所述多个表面包括与压缩机护罩表面物理连通的喇叭口表面; 压缩机护罩表面与扩散器表面物理连通; 并且扩散器表面与喇叭口表面物理连通。还提供了包括压缩机护罩的整体组件。还公开了包括整体组件的辅助动力单元以及制造整体组件的方法。

4. 发明授权

US07007475B2 Conical helical of spiral combustor scroll device in gas turbine engine 有权
标题翻译：燃气涡轮发动机中螺旋燃烧器涡旋装置的锥形螺旋
公开(公告)号：US07007475B2
公开(公告)日：2006-03-07
申请号：US10386771
申请日：2003-03-11
申请人： Ly D. Nguyen , Hakan Aksoy , Stony Kujala , Cristopher Frost
发明人： Ly D. Nguyen , Hakan Aksoy , Stony Kujala , Cristopher Frost
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/52 , F23R3/425
摘要： A conical helical design for a turbine combustor scroll utilizes as much cavity of the combustor housing as possible by adding an axial shift and an irregular cross sectional shape in the scroll without adversely effecting aerodynamic performance. The axial shift region of the combustor scroll extends the cross-sectional area centroid of the scroll beyond the scroll's discharge area B-width. The resulting scroll design allows for the use of a high performance engine with a larger combustor while reducing the weight of the system by making the combustor housing as small as possible. Furthermore, the scroll design increases the air velocity for convection cooling by reducing the gap between the scroll and the housing. The turbine scroll of the present invention is useful in engines for which high performance is required, such as certain high performance aircraft.
摘要翻译：用于涡轮机燃烧器涡旋盘的锥形螺旋设计通过在涡旋中增加轴向移动和不规则横截面形状而尽可能多地利用燃烧器壳体的空腔，而不会不利地影响空气动力性能。燃烧器涡旋件的轴向移动区域将涡旋件的横截面积重心延伸超过涡旋件的排放区域B-宽度。所得到的涡卷设计允许使用具有较大燃烧器的高性能发动机，同时通过使燃烧器壳体尽可能小地减小系统的重量。此外，涡旋设计通过减小涡旋件和壳体之间的间隙来增加用于对流冷却的空气速度。本发明的涡轮涡旋盘可用于需要高性能的发动机，例如某些高性能飞机。

5. 发明授权

US5434226A Epoxy resin toughened with a polyether sulfone and polyarylsulfidesulfone 失效
标题翻译：环氧树脂用聚醚砜和聚芳基硫醚砜增韧
公开(公告)号：US5434226A
公开(公告)日：1995-07-18
申请号：US188663
申请日：1994-01-28
申请人： Ly D. Nguyen , Matthew A. Lowry , Deborah L. Stone , Julie A. Underwood
发明人： Ly D. Nguyen , Matthew A. Lowry , Deborah L. Stone , Julie A. Underwood
IPC分类号： C08G59/40 , C08L63/00 , C08L79/08 , C08L81/00 , C08L81/06 , C08L101/00 , H05K1/03 , C08F283/00
CPC分类号： C08L63/00 , C08J5/24 , C08L101/00 , C08L79/085 , C08L81/06 , C08J2379/08 , C08L2205/02 , H05K1/0333 , Y10S525/906 , Y10S525/935
摘要： Thermosetting resin systems exhibiting improved performance characteristics when utilized in composite product applications, said resin systems being modified with a polyarylsulfidesulfone dispersed therein and with a polyethersulfone dissolved therein.
摘要翻译：当在复合产品应用中使用时，表现出改进的性能特征的热固性树脂体系，所述树脂体系用分散在其中的聚芳基硫醚砜和其中溶解的聚醚砜进行改性。

6. 发明授权

US06912782B2 Forming and assembly method for multi-axial pivoting combustor liner in gas turbine engine 失效
标题翻译：燃气轮机发动机多轴转动燃烧器衬管的成形和组装方法
公开(公告)号：US06912782B2
公开(公告)日：2005-07-05
申请号：US10410794
申请日：2003-04-09
申请人： Ly D. Nguyen , Gregory O. Woodcock , Stony Kujala
发明人： Ly D. Nguyen , Gregory O. Woodcock , Stony Kujala
IPC分类号： F23R3/00 , F23R3/60 , B23P15/00
CPC分类号： F23R3/002 , F23R3/60 , F23R2900/00017 , Y10T29/49231 , Y10T29/49316 , Y10T29/4932
摘要： A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and relative to the turbine scroll. The pivoting liner has the ability to control and minimize air leakage from part to part, for example, from the liner to the turbine scroll, during various operating conditions. Additionally, the liner provides for easy assembly with no flow path steps. Finally, the pivoting liner tolerates thermal and mechanical stresses and minimizes thermal wear.
摘要翻译：在涡轮发动机的燃烧系统内的多轴旋转衬套允许系统以最小的热干扰工作，特别是在瞬态条件下的系统运行期间，通过允许衬套围绕其中心线枢转并且相对于涡轮机涡卷滑动。在各种操作条件下，枢转衬套具有控制和最小化从一部分到另一部分的空气泄漏的能力，例如从衬套到涡轮涡旋。另外，衬套提供了容易组装，没有流动路径的步骤。最后，旋转衬垫可承受热和机械应力，并最大限度地减少热磨损。

7. 发明授权

US07007480B2 Multi-axial pivoting combustor liner in gas turbine engine 有权
标题翻译：燃气涡轮发动机中的多轴旋转燃烧器衬套
公开(公告)号：US07007480B2
公开(公告)日：2006-03-07
申请号：US10410791
申请日：2003-04-09
申请人： Ly D. Nguyen , Gregory O. Woodcock , Stony Kujala
发明人： Ly D. Nguyen , Gregory O. Woodcock , Stony Kujala
IPC分类号： F02C1/00 , F02G3/00
CPC分类号： F23R3/283 , F23R3/60 , F23R2900/00014 , F23R2900/00017
摘要： A multi-axial pivoting liner within the combustion system of a turbine engine allows the system to work with minimum thermal interference, especially during system operation at transient conditions, by allowing the liner to pivot and slide about its centerline and relative to the turbine scroll. The pivoting liner has the ability to control and minimize air leakage from part to part, for example, from the liner to the turbine scroll and liner to the surrounding structures, during various operating conditions. Additionally, the liner provides for easy assembly with no flow path steps. Finally, the pivoting liner tolerates thermal and mechanical stresses and minimizes thermal wear.
摘要翻译：在涡轮发动机的燃烧系统内的多轴旋转衬套允许系统以最小的热干扰工作，特别是在瞬态条件下的系统运行期间，通过允许衬套围绕其中心线枢转并且相对于涡轮机涡卷滑动。在各种操作条件下，枢转衬套具有控制和最小化从一部分到另一部分的空气泄漏的能力，例如从衬套到涡轮机涡旋件和衬套到周围结构。另外，衬套提供了容易组装，没有流动路径的步骤。最后，旋转衬垫可承受热和机械应力，并最大限度地减少热磨损。

8. 发明授权

US06719524B2 Method of forming a thermally isolated gas turbine engine housing 有权
标题翻译：形成热隔离燃气涡轮发动机壳体的方法
公开(公告)号：US06719524B2
公开(公告)日：2004-04-13
申请号：US10084858
申请日：2002-02-25
申请人： Ly D. Nguyen , Louis Cruse , Ivar Gene Fowkes , Silvestre Salas , William North , Vadanth Kadambi
发明人： Ly D. Nguyen , Louis Cruse , Ivar Gene Fowkes , Silvestre Salas , William North , Vadanth Kadambi
IPC分类号： F01D2512
CPC分类号： F01D9/065 , F01D25/14
摘要： A method for forming a thermally isolating gas turbine housing from the significantly high temperatures associated with the combustion gases flowing through the housing. A floating liner is positioned within the turbine housing with an outer baffle arranged about the floating liner and an inner baffle arranged within the floating liner. The inner and outer baffles are welled or brazed to the floating liner assembly to form a unitary assembly creating a single, continuous cooling passageway within the housing for collecting heat from adjacent the surfaces of the floating liner and expelling the heat into the combustion exhaust stream.
摘要翻译：一种用于从与流过壳体的燃烧气体相关联的显着高温形成隔热燃气轮机壳体的方法。浮动衬套定位在涡轮机壳体内，其中外挡板布置在浮动衬套周围，并且内挡板布置在浮动衬套内。内挡板和外挡板被精加工或钎焊到浮动衬套组件以形成整体组件，其在壳体内形成单个连续的冷却通道，用于从相邻的浮动衬套的表面收集热量并将热量排出到燃烧废气流中。

9. 发明授权

US07442006B2 Integral diffuser and deswirler with continuous flow path deflected at assembly 有权
标题翻译：具有连续流动路径的整体扩散器和脱流器在组装时偏转
公开(公告)号：US07442006B2
公开(公告)日：2008-10-28
申请号：US11204640
申请日：2005-08-15
申请人： Ly D. Nguyen , Gary A. Shoff
发明人： Ly D. Nguyen , Gary A. Shoff
IPC分类号： F01D1/02
CPC分类号： F04D29/4206 , F04D29/444 , F04D29/624 , Y10T29/49323
摘要： An integrated assembly is provided for a centrifugal compressor, which integrates selected static portions of the centrifugal compressor into a monolithic structure to allow a small deflection of the inner flow path at assembly. The integrated assembly may include a machined compressor shroud casting having integral diffuser vanes, an aft sheet metal inner flow ring having a radially extending rim with slots in the inner flow ring for receiving diffuser vanes and slots in the rim for receiving deswirler vanes, an outer deswirler band surrounding the inner flow ring and having slots opposing those in the rim, and a plurality of deswirler vanes for fabrication between the inner flow ring and the deswirler band within the respective slots.
摘要翻译：提供了一种用于离心式压缩机的集成组件，该离心式压缩机将离心式压缩机的选定的静态部分整合成单片结构，以允许在组装时内部流动路径的小偏转。集成组件可以包括具有整体的扩散器叶片的机加工的压缩机护套浇铸件，后板金属内流动环，其具有径向延伸的边缘，在内流动环中具有槽，用于接收扩散器叶片和边缘中用于接收脱水叶片的槽，围绕内部流动环并且具有与边缘相对的狭槽的脱水带，以及用于在各个槽内的内部流动环和脱水带之间制造的多个脱流叶片。

10. 发明授权

US07093448B2 Multi-action on multi-surface seal with turbine scroll retention method in gas turbine engine 失效
标题翻译：多功能多功能涡轮发动机涡轮涡轮保持法多表面密封
公开(公告)号：US07093448B2
公开(公告)日：2006-08-22
申请号：US10682217
申请日：2003-10-08
申请人： Ly D. Nguyen , Gregory O. Woodcock , Stony Kujala
发明人： Ly D. Nguyen , Gregory O. Woodcock , Stony Kujala
IPC分类号： F02C3/00 , F23R3/42
CPC分类号： F23R3/54 , F23R3/50 , F23R3/52 , F23R3/60
摘要： A gas turbine engine comprises a turbine scroll inside a combustor housing, discouragers with 90-degree bending angles, a radial nozzle contacting a forward bayonet on the forward side of the turbine scroll at a bayonet engagement point and a B-width measured between the discouragers. Retaining ring maintains the size of the B-width. The turbine scroll may have eight surfaces sealing at four locations and a provision to maintain constant “B-width” for the thin sheet metal scroll within the combustion system. The design allows the scroll to operate at high temperature while maintaining lowest possible thermal and mechanical stresses. It can be easily assembled with excellent capability to control gas leakage and minimal component interface wearing or fretting. The gas turbine engine is adapted for aircraft, spacecraft, missiles, and other flight vehicles, especially high performance, high cycle flight vehicles.
摘要翻译：燃气涡轮发动机包括在燃烧器壳体内的涡轮机涡旋件，具有90度弯曲角度的气门，在卡口接合点处与涡轮机涡旋体的前侧接触前方卡口的径向喷嘴和在气门机构之间测量的B宽度。保持环保持B宽度的大小。涡轮机涡旋件可以在四个位置处具有八个表面密封，并且在燃烧系统内为薄板金属涡卷保持恒定的“B宽度”。该设计允许滚动体在高温下运行，同时保持尽可能低的热和机械应力。它可以很容易地组装，具有极好的控制气体泄漏的能力和最小的组件界面磨损或微动。燃气涡轮发动机适用于飞机，航天器，导弹和其他飞行器，特别是高性能，高周期的飞行器。

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