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公开(公告)号：US07726944B2
公开(公告)日：2010-06-01
申请号：US11524102
申请日：2006-09-20
申请人： Richard H. Page , Wieslaw A. Chlus
发明人： Richard H. Page , Wieslaw A. Chlus
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F05D2240/307 , F05D2260/20 , F05D2260/2214 , Y02T50/676
摘要： A gas turbine engine has a turbine blade having a tip cap to close off internal cooling passages. The tip cap is formed with a plurality of purge holes, with there being at least two rows of purge holes. The increased number of purge holes spreads the cooling air outwardly across more of the surface area of the tip cap, and provides the tip cap with a better ability to withstand the extreme temperatures it faces in use.
摘要翻译： 燃气涡轮发动机具有涡轮叶片，其具有尖端盖以封闭内部冷却通道。 尖端盖形成有多个吹扫孔，其中至少有两排吹扫孔。 吹扫孔数量的增加将冷却空气向外扩散到尖端盖的更多表面区域，并且提供顶盖具有更好的耐受其使用的极端温度的能力。
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公开(公告)号：US20100080711A1
公开(公告)日：2010-04-01
申请号：US11524102
申请日：2006-09-20
申请人： Richard H. Page , Wieslaw A. Chlus
发明人： Richard H. Page , Wieslaw A. Chlus
IPC分类号： F01D5/18
CPC分类号： F01D5/20 , F05D2240/307 , F05D2260/20 , F05D2260/2214 , Y02T50/676
摘要： A gas turbine engine has a turbine blade having a tip cap to close off internal cooling passages. The tip cap is formed with a plurality of purge holes, with there being at least two rows of purge holes. The increased number of purge holes spreads the cooling air outwardly across more of the surface area of the tip cap, and provides the tip cap with a better ability to withstand the extreme temperatures it faces in use.
摘要翻译： 燃气涡轮发动机具有涡轮叶片，其具有尖端盖以封闭内部冷却通道。 尖端盖形成有多个吹扫孔，其中至少有两排吹扫孔。 吹扫孔数量的增加将冷却空气向外扩散到尖端盖的更多表面区域，并且提供顶盖具有更好的耐受其使用的极端温度的能力。
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公开(公告)号：US07175386B2
公开(公告)日：2007-02-13
申请号：US10738842
申请日：2003-12-17
申请人： Anthony Cherolis , Wieslaw A. Chlus
发明人： Anthony Cherolis , Wieslaw A. Chlus
IPC分类号： F01D5/14
CPC分类号： F01D5/187 , F05D2260/2212 , Y02T50/676
摘要： A blade for a gas turbine engine includes a trailing edge cooling chamber, wherein the pressure and suction sides are connected by an array of spaced pedestals. The pedestals in a region most subject to thermal stresses are formed to be elliptical, such that the thermal stresses are spread over a larger area. Thus, stress concentrations are reduced. Also, various sized cylindrical pedestals may be used at other locations.
摘要翻译： 用于燃气涡轮发动机的叶片包括后缘冷却室，其中压力和吸力侧通过间隔开的基座的阵列连接。 最受热应力的区域中的基座形成为椭圆形，使得热应力分布在更大的面积上。 因此，应力集中减少。 此外，可以在其他位置使用各种尺寸的圆柱形基座。
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公开(公告)号：US4971272A
公开(公告)日：1990-11-20
申请号：US373969
申请日：1989-06-29
CPC分类号： F16L3/137 , Y10T24/141
摘要： A support structure 10 for positioning a conduit 12 for various environments including that of an aircraft gas turbine engine is disclosed. Various construction details are developed for the support structure which facilitate assembly of portions of the support structure. The support structure includes a clamp assembly 18 and a clip 22 for orienting the clamp assembly in the proper direction. Orientation of the clamp assembly is facilitated by features of the clip. These features include a pair of tabs 32, 34 which face each other from either side of the clamp assembly. In one detailed embodiment, the clamp includes a laterally extending tab 92 to block the channel formed between the pair of longitudinally extending tabs.
摘要翻译： 公开了一种用于定位用于包括飞机燃气涡轮发动机的各种环境的管道12的支撑结构10。 开发了用于支撑结构的各种构造细节，其有利于组装支撑结构的部分。 支撑结构包括用于使夹具组件沿正确方向定向的夹具组件18和夹子22。 夹子组件的方向由夹具的特征促进。 这些特征包括从夹具组件的任一侧彼此面对的一对翼片32,34。 在一个详细的实施例中，夹具包括横向延伸的突片92，以阻挡形成在一对纵向延伸突片之间的通道。
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公开(公告)号：US4747750A
公开(公告)日：1988-05-31
申请号：US819943
申请日：1986-01-17
CPC分类号： F02C7/28 , F01D11/025
摘要： An inner wall for a transition duct between the high pressure and low pressure turbines of a multirotor gas turbine engine in which the wall structure itself is made up of multiple aligned segments which are bolted to the inner shrouds of the vane clusters of the low pressure turbine and in which the segments are secured to forward and rearward cone elements with one of said elements bolted securely to the segments and the other cone having free axial and radial movement with respect to the segments with the cone elements supporting at their inner edges a seal element to cooperate with a rotating element on a low pressure rotor.
摘要翻译： 用于多转轮燃气涡轮发动机的高压和低压涡轮机之间的过渡管道的内壁，其中壁结构本身由多个对准的段组成，该多个对准的段螺栓连接到低压涡轮机的叶片组的内护罩 并且其中所述段被固定到前后锥形元件，其中一个所述元件牢固地螺栓固定到所述段，并且所述另一个锥体相对于所述段具有自由的轴向和径向运动，所述锥形元件在其内边缘处支撑有密封元件 与低压转子上的旋转元件配合。
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公开(公告)号：US06824359B2
公开(公告)日：2004-11-30
申请号：US10355664
申请日：2003-01-31
申请人： Wieslaw A. Chlus , Stanley J. Funk
发明人： Wieslaw A. Chlus , Stanley J. Funk
IPC分类号： F01D518
CPC分类号： F01D5/187 , F01D5/189 , F01D5/20 , F05D2230/10 , F05D2230/13 , F05D2240/122 , F05D2240/304 , F05D2250/191 , F05D2250/192 , F05D2250/712 , F05D2260/22141 , F05D2260/607
摘要： A turbine blade has a platform and an airfoil extending from a root at the platform to a tip. The airfoil has an internal cooling passageway network including at least one trailing edge cavity. A group of trailing edge holes extends from the trailing edge to the trailing edge cavity and a group of tip holes extends from the tip to the trailing edge cavity.
摘要翻译： 涡轮叶片具有平台和从平台上的根延伸到尖端的翼型件。 翼型件具有包括至少一个后缘腔的内部冷却通道网络。 一组后缘孔从后缘延伸到后缘腔，并且一组尖端孔从尖端延伸到后缘腔。
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公开(公告)号：US5284421A
公开(公告)日：1994-02-08
申请号：US980848
申请日：1992-11-24
申请人： Wieslaw A. Chlus , David P. Houston
发明人： Wieslaw A. Chlus , David P. Houston
CPC分类号： F01D5/22 , Y10S416/50
摘要： A rotor blade having axially spaced gussets disposed between a root portion and a platform is disclosed. Various construction details are developed which provide a gusset providing both platform support and damper positioning means. In one particular embodiment, a rotor blade assembly includes a plurality of circumferentially spaced rotor blades having dampers disposed between adjacent blades, wherein each blade includes an axially spaced pair of gussets extending laterally from the rotor blade. The gussets extend from a root portion of the rotor blade to a platform and provide radial support of the platform during rotation of the rotor assembly. The gussets include a curved lateral edge which, during rotation of the rotor assembly, urges the damper away from the root portion of the blade.
摘要翻译： 公开了一种具有设置在根部和平台之间的具有轴向间隔的角撑板的转子叶片。 开发了各种构造细节，其提供提供平台支撑和阻尼器定位装置的角撑板。 在一个具体实施例中，转子叶片组件包括多个周向间隔开的转子叶片，其具有设置在相邻叶片之间的阻尼器，其中每个叶片包括从转子叶片横向延伸的轴向间隔开的一对角撑板。 角撑板从转子叶片的根部延伸到平台并且在转子组件旋转期间提供平台的径向支撑。 角撑板包括弯曲的侧边缘，其在转子组件的旋转期间促使阻尼器远离叶片的根部。
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公开(公告)号：US5228835A
公开(公告)日：1993-07-20
申请号：US981146
申请日：1992-11-24
申请人： Wieslaw A. Chlus
发明人： Wieslaw A. Chlus
CPC分类号： F01D11/006 , F01D5/22 , Y10S416/50
摘要： An underplatform damper contact portion 54 is rigid, and provides a loose seal between the underplatform cooling air 46 and the gas stream 40. At the aft end of the blade platform the pressure difference increases and a more effective seal is provided by the snap-in flexible seal 71.
摘要翻译： 底板式阻尼器接触部分54是刚性的，并且在底板冷却空气46和气流40之间提供松散的密封。在叶片平台的后端处，压力差增加，并且由咬合器提供更有效的密封 柔性密封件71。
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公开(公告)号：US07575416B2
公开(公告)日：2009-08-18
申请号：US11437189
申请日：2006-05-18
申请人： Stanley J. Funk , Wieslaw A. Chlus
发明人： Stanley J. Funk , Wieslaw A. Chlus
IPC分类号： F01D5/30
CPC分类号： F01D5/3007 , F01D11/006
摘要： A rotor assembly having a seal member in the root section of a rotor blade is disclosed. Various construction details are developed for blocking the flow of gases between adjacent rotor blades. In one detailed embodiment, a deformable seal member formed of a high temperature material is disposed between the root sections of adjacent rotor blades and engages the blades under operative conditions.
摘要翻译： 公开了一种转子组件，其具有在转子叶片的根部中的密封构件。 开发了各种结构细节来阻止相邻转子叶片之间的气体流动。 在一个详细的实施例中，由高温材料形成的可变形的密封件设置在相邻的转子叶片的根部之间并在操作条件下与叶片接合。
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公开(公告)号：US07175391B2
公开(公告)日：2007-02-13
申请号：US10888125
申请日：2004-07-08
IPC分类号： B64C11/24
CPC分类号： F01D5/20 , F05D2230/80 , F05D2250/60 , F05D2260/202 , F05D2260/94 , F05D2260/941
摘要： A blade has an airfoil body having an internal cooling passageway network and a body tip pocket. At least one plate is secured within the body tip pocket and has inboard and outboard surfaces. A recess is in the outboard surface and an associated protrusion is on the inboard surface.
摘要翻译： 叶片具有具有内部冷却通道网络和主体尖端口袋的翼型件本体。 至少一个板固定在主体尖端口袋内并具有内侧和外侧表面。 凹槽位于外侧表面，相关的凸起位于内侧表面。
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