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1. 发明授权

US06652222B1 Fan case design with metal foam between Kevlar 有权
标题翻译：凯夫拉尔风扇外壳采用金属泡沫设计
公开(公告)号：US06652222B1
公开(公告)日：2003-11-25
申请号：US10200460
申请日：2002-09-03
申请人： Czeslaw Wojtyczka , Samy Amin
发明人： Czeslaw Wojtyczka , Samy Amin
IPC分类号： F01D2100
CPC分类号： F01D21/045 , B32B3/12 , B32B5/18 , F05D2220/326 , F05D2220/327 , F05D2300/433 , F05D2300/601 , F05D2300/612 , F05D2300/614
摘要： A fan blade fragment containment assembly for a gas turbine engine having a fan case surrounding the fan and having a circumferential axially extending blade fragment impact zone. An inner relatively slack or low tension deformable layer of Kevlar™ or Zylon™ fabric is mounted to the fan case outer surface and envelopes the impact zone. A compressible (ex. metal foam or honeycomb) layer is mounted on an outer surface of the deformable layer. A friction reduction layer of Teflon™ is mounted on an outer surface of the compressible layer and an outer relatively taut higher tension containment layer of Kevlar™ or Zylon™ fabric is mounted on an outer surface of the friction reduction layer. The friction reduction layer enhances the distribution of impact forces about the circumference of the compressible layer by reducing local shear stresses between the compressible layer and the containment layer.
摘要翻译：一种用于燃气涡轮发动机的风扇叶片碎片容纳组件，其具有围绕所述风扇且具有周向轴向延伸的叶片碎片冲击区的风扇壳体。 Kevlar TM或Zylon TM织物的内部相对松弛或低张力可变形层被安装到风扇壳体外表面并且包围冲击区域。可压缩（例如金属泡沫或蜂窝）层安装在可变形层的外表面上。 Teflon TM的摩擦减小层安装在可压缩层的外表面上，Kevlar TM或Zylon TM织物的外部较紧张的较高张力的容纳层安装在摩擦减小层的外表面上。摩擦减小层通过减小可压缩层和容纳层之间的局部剪切应力来增强围绕可压缩层的圆周的冲击力的分布。

2. 发明授权

US06375410B2 Frangible cover for turbofan engine blade removal and access 有权
标题翻译：涡轮发动机叶片拆卸和通道的易碎盖
公开(公告)号：US06375410B2
公开(公告)日：2002-04-23
申请号：US09758352
申请日：2001-01-12
申请人： Brian Ellis Clouse , Robert Armstrong Morse
发明人： Brian Ellis Clouse , Robert Armstrong Morse
IPC分类号： F01D2100
CPC分类号： F01D21/045 , F01D25/24 , F04D29/644 , F04D29/646 , F05B2260/3011 , F05D2220/326 , F05D2220/327 , F05D2230/70 , F05D2230/80 , Y02T50/671
摘要： A frangible cover is provided for a recess in a containment case for turbofan engine blade removal and access. The recess provided in the containment case allows outward radial movement of the engine fan blade when the engine fan blade is to be removed from the containment case. The present invention proposes a frangible component to cover the recess. A plurality of initiation points, notched in the frangible cover at intersections of surfaces encourages brittle fracture of the frangible component.
摘要翻译：在容纳壳体中设置用于涡轮风扇发动机叶片拆卸和通路的凹槽的易碎盖。当将发动机风扇叶片从容纳壳体移除时，设置在容纳壳体中的凹部允许发动机风扇叶片的向外径向移动。本发明提出了一种用于覆盖凹部的易碎部件。在表面交叉处的易碎盖中切口的多个起始点鼓励易碎部件的脆性断裂。

3. 发明授权

US06575694B1 Gas turbine engine blade containment assembly 有权
标题翻译：燃气轮机发动机叶片安全壳组件
公开(公告)号：US06575694B1
公开(公告)日：2003-06-10
申请号：US09924104
申请日：2001-08-08
申请人： Ewan F Thompson , Ian G Martindale , David S Knott , Kenneth F Udall , David Geary , Julian M Reed , Sivasubramaniam K Sathianathan
发明人： Ewan F Thompson , Ian G Martindale , David S Knott , Kenneth F Udall , David Geary , Julian M Reed , Sivasubramaniam K Sathianathan
IPC分类号： F01D2100
CPC分类号： F01D21/045 , F05D2250/15 , F05D2250/25 , F05D2250/61 , Y02T50/671
摘要： A turbofan gas turbine engine (10) comprises a fan rotor (32) carrying a plurality of radially extending fan blades (34). A fan blade containment assembly (38) surrounds the fan blades (34) and the fan blade containment assembly (34) comprises a generally annular, or frustoconical, cross-section casing (52). At least one corrugated sheet metal ring surrounds the casing (52) wherein the corrugations extend with axial and/or circumferential components.
摘要翻译：涡轮风扇燃气涡轮发动机（10）包括承载多个径向延伸的风扇叶片（34）的风扇转子（32）。风扇叶片容纳组件（38）围绕风扇叶片（34）并且风扇叶片容纳组件（34）包括大致环形或截头圆锥形的横截面壳体（52）。至少一个波纹板金属环围绕壳体（52），其中波纹随轴向和/或周向部分延伸。

4. 发明授权

US06533541B1 High energy particle arrestor for air turbine starters 有权
标题翻译：用于空气涡轮起动器的高能量微粒捕集器
公开(公告)号：US06533541B1
公开(公告)日：2003-03-18
申请号：US10004906
申请日：2001-12-04
申请人： Gary A. Farnsworth , Glenn H. Lane , Douglas C. Smith
发明人： Gary A. Farnsworth , Glenn H. Lane , Douglas C. Smith
IPC分类号： F01D2100
CPC分类号： F02C7/05 , F01D21/045 , F02C7/277 , F05D2250/232 , F05D2260/607 , Y02T50/675
摘要： One or more particle arrestor rings are mounted in a curved radial flow portion of a gas turbine annular flow passage. The arrestor rings block line of sight paths between the turbine wheel and the annular flow passage outlet. Thus, the arrestor rings substantially inhibit relatively high energy particles from exiting the gas turbine housing, thus substantially inhibiting collateral damage to surrounding equipment and structure.
摘要翻译：一个或多个避雷器环安装在燃气轮机环形流动通道的弯曲的径向流动部分中。避雷器环阻挡在涡轮机叶轮和环形流动通道出口之间的视线路径。因此，避雷器环基本上抑制相对高能量的颗粒离开燃气轮机壳体，从而基本上抑制对周围设备和结构的附带损坏。

5. 发明授权

US06499940B2 Compressor casing for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的压缩机壳体
公开(公告)号：US06499940B2
公开(公告)日：2002-12-31
申请号：US09812001
申请日：2001-03-19
申请人： Paul R. Adams
发明人： Paul R. Adams
IPC分类号： F01D2100
CPC分类号： F01D11/08 , F04D29/164 , F04D29/526 , F04D29/685 , Y10S415/914
摘要： The cylindrical compressor casing of a gas turbine engine has a plurality of radially inwardly and axially rearwardly opening anti-surge grooves disposed on a radially inner surface thereof whereby foreign objects ingested into the engine and entering the grooves are free to move axially rearwardly of the engine.
摘要翻译：燃气涡轮发动机的圆筒形压缩机壳体具有设置在其径向内表面上的多个径向向内和轴向向后打开的防喘振槽，由此吸入发动机并进入槽的异物自由地沿着发动机的轴向向后移动。

6. 发明授权

US06290455B1 Contoured hardwall containment 有权
标题翻译：轮廓硬壁遏制
公开(公告)号：US06290455B1
公开(公告)日：2001-09-18
申请号：US09454706
申请日：1999-12-03
申请人： Robert J. Hemmelgarn , Sugato Bhattacharjee , Laura A. Iyer , Robert P. Czachor , Michael L. Barron
发明人： Robert J. Hemmelgarn , Sugato Bhattacharjee , Laura A. Iyer , Robert P. Czachor , Michael L. Barron
IPC分类号： F01D2100
CPC分类号： F01D21/045 , F05B2260/3011 , Y02T50/671
摘要： An improved containment structure for use with turbomachinery, such as turbofan engines. A casing is provided with at least one impact resistant section of a thickness sufficient to resist being pierced upon impact by a blade. The impact resistant section has a smoothly contoured thickness along its axial length and is free from features likely to cause a local failure in the event of impact by a blade released from a rotating disk.
摘要翻译：用于涡轮机械的改进的容纳结构，例如涡轮风扇发动机。壳体设置有至少一个抗冲击部分，其厚度足以抵抗在被叶片撞击时被刺穿。抗冲击部分沿着其轴向长度具有平滑的成形厚度，并且没有在由旋转盘释放的刀片碰撞的情况下可能导致局部故障的特征。

7. 发明授权

US06497550B2 Gas turbine engine blade containment assembly 有权
标题翻译：燃气轮机发动机叶片安全壳组件
公开(公告)号：US06497550B2
公开(公告)日：2002-12-24
申请号：US09804298
申请日：2001-03-13
申请人： Stephen J Booth
发明人： Stephen J Booth
IPC分类号： F01D2100
CPC分类号： F01D21/045 , Y02T50/671
摘要： A gas turbine engine fan blade containment assembly (38) comprising a generally cylindrical, or frustoconical, metal casing (40) has an upstream portion (56), a blade containment portion (54) and a transition portion (58). The upstream portion (56) has a flange (52) connecting the metal containment casing (40) to an axially adjacent casing. The upstream portion (56) of the casing (40) has a greater diameter (D1) than the diameter (D2) of the blade containment portion (54) and the blade containment portion (54) has a greater thickness (T2) than the thickness (T1) of the upstream portion (54). The transition portion (58) connects the blade containment portion (54) and the upstream portion (56) to transmit loads from the blade containment portion (54) to the upstream flange (42). The transition portion (58) has a smoothly curved increase in diameter between the blade containment portion (54) and the upstream portion (56) whereby the transition portion (58) is allowed to flex to reduce impact loads transmitted to the upstream flange (42).
摘要翻译：包括大致圆柱形或截头圆锥形的金属壳体（40）的燃气涡轮发动机风扇叶片容纳组件（38）具有上游部分（56），叶片容纳部分（54）和过渡部分（58）。上游部分（56）具有将金属容纳壳体（40）连接到轴向相邻壳体的凸缘（52）。壳体（40）的上游部分（56）具有比叶片容纳部分（54）的直径（D2）更大的直径（D1），并且叶片容纳部分（54）的厚度（T2）比上游部分（54）的厚度（T1）。过渡部分（58）连接叶片容纳部分（54）和上游部分（56），以将载荷从叶片容纳部分（54）传递到上游凸缘（42）。过渡部分（58）在叶片容纳部分（54）和上游部分（56）之间具有平滑弯曲的直径增加，从而允许过渡部分（58）弯曲以减少传递到上游凸缘（42）的冲击载荷）。

8. 发明授权

US06305899B1 Gas turbine engine 有权
标题翻译：燃气轮机
公开(公告)号：US06305899B1
公开(公告)日：2001-10-23
申请号：US09392301
申请日：1999-09-08
申请人： Duncan Saunders
发明人： Duncan Saunders
IPC分类号： F01D2100
CPC分类号： F01D25/243 , F01D21/045 , Y02T50/671
摘要： A gas turbine engine core casing comprises axially adjacent portions (20,21) that are flanged to receive bolts (28) that attach the portions (20,21) to each other. One of the casing portions (20) is provided with flange (23) that is of L-shape cross-section to provide local enhancement of the rigidity of the casing portion (20). Such rigidity enhancement provides improved debris containment in the event of the failure of rotor components within the casing.
摘要翻译：燃气涡轮发动机芯壳体包括轴向相邻的部分（20,21），其被凸缘以接收将部分（20,21）彼此附接的螺栓（28）。壳体部分（20）中的一个设置有L形横截面的凸缘（23），以提供壳体部分（20）的刚性的局部增强。这种刚性增强在壳体内的转子部件故障的情况下提供改进的碎屑收容。

9. 发明授权

US06264424B1 Relating to compressors and turbines 有权
标题翻译：关于压缩机和涡轮机
公开(公告)号：US06264424B1
公开(公告)日：2001-07-24
申请号：US09168953
申请日：1998-10-09
申请人： John Fuller
发明人： John Fuller
IPC分类号： F01D2100
CPC分类号： F04D25/04 , F01D21/045 , F04D29/023 , F04D29/4206 , F05B2260/3011 , F05D2220/40 , F05D2300/133
摘要： A centripetal compressor includes a compressor housing, a compressor wheel mounted within the housing and having compressor blades. The compressor housing comprises a cover plate and a diffuser flange that is fixed to both the cover plate and to a bearing housing. The diffuser member has an outer peripheral portion attached to the cover plate and a radially inner portion attached to the bearing housing. A frangible groove or weakened section is defined in the diffuser at a position intermediate the outer peripheral and the radially inner portions so as to enable predictable fracture of the diffuser flange during failure of the compressor wheel. The same principle is applied to the turbine of a turbocharger.
摘要翻译：向心式压缩机包括压缩机壳体，安装在壳体内并具有压缩机叶片的压缩机叶轮。压缩机壳体包括盖板和固定到盖板和轴承壳体的扩散器凸缘。扩散器构件具有附接到盖板的外周部分和附接到轴承壳体的径向内部。在扩散器中在外周和径向内部中间的位置处限定易碎的凹槽或弱化部分，以便在压缩机叶轮故障期间能够预测到扩散器凸缘的断裂。相同的原理应用于涡轮增压器的涡轮机。

10. 发明授权

US06179551B2 Gas turbine containment casing 有权
标题翻译：燃气轮机安全壳
公开(公告)号：US06179551B2
公开(公告)日：2001-01-30
申请号：US09324942
申请日：1999-06-03
申请人： Sivasubramaniam K Sathianathan , Michael R Lawson , Sunil V Charadva
发明人： Sivasubramaniam K Sathianathan , Michael R Lawson , Sunil V Charadva
IPC分类号： F01D2100
CPC分类号： F01D21/045 , Y02T50/671
摘要： A containment casing for a gas turbine engine comprising a substantially rigid casing shell arranged in operation coaxially with an axis of rotation of the gas turbine engine. The casing extending circumferentially around an array of fan rotor blades which are arranged to rotate about the engine axis. In the region of the casing where it is predicted blade impact in the event of a fan blade failure, there is at least one reinforcing rib extending substantially radially from the casing and circumscribing the outer periphery of the casing shell. The ribs providing improved strengthening of the casing. Preferably a first rib is positioned about the casing between the operational position of the trailing edge and the mid chord point of the fan blade. A second rib is axially positioned between the operational position of the mid chord point and the leading edge of the fan blade. A third rib may also be positioned axially forward of the operational position of the leading edge of the fan blade. Also described are various ratios of the reinforcing ribs and the casing shell thickness to provide and improved lightweight casing.
摘要翻译：一种用于燃气涡轮发动机的容纳壳体，包括与燃气涡轮发动机的旋转轴线同轴地布置的基本上刚性的壳体壳体。围绕围绕发动机轴线旋转的风扇转子叶片阵列周向延伸的壳体。在壳体的在风扇叶片故障的情况下被预测的叶片冲击的区域中，存在至少一个从壳体径向延伸并且限制壳体外周的加强肋。这些肋骨提供了改进的套管强化。优选地，第一肋围绕壳体定位在后缘的操作位置和风扇叶片的中间弦点之间。第二肋轴向地定位在中和点的操作位置和风扇叶片的前缘之间。第三肋也可以轴向位于风扇叶片的前缘的操作位置的前方。还描述了加强肋和壳体壳体厚度的各种比例，以提供和改进的轻质外壳。

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