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公开(公告)号：US20120006028A1
公开(公告)日：2012-01-12
申请号：US12832116
申请日：2010-07-08
申请人： Ching-Pang Lee , Danning You , Reinhard Schilp , Chander Prakash
发明人： Ching-Pang Lee , Danning You , Reinhard Schilp , Chander Prakash
CPC分类号： F01D9/023 , F02C7/12 , F05D2260/96 , F23R3/06 , F23R2900/00014
摘要： A resonance chamber (42) has an outer wall (32) with coolant inlet holes (34A-C), an inner wall (36) with acoustic holes (38), and side walls (40A-C) between the inner and outer walls. A depression (33A-C) in the outer wall has a bottom portion (50) that is close to the inner wall compared to peaks (37A-C) of the outer wall. The coolant inlet holes may be positioned along the bottom portion of the depression and along a bottom portion of the side walls to direct coolant flows (44, 51) toward impingement locations (43) on the inner wall that are out of alignment with the acoustic holes. This improves impingement cooling efficiency. The peaks (37A-C) of the outer wall provide volume in the resonance chamber for a target resonance.
摘要翻译： 共振室（42）具有外壁（32），其具有冷却剂入口孔（34A-C），具有声孔（38）的内壁（36）和内壁和外壁之间的侧壁（40A-C） 。 外壁上的凹部（33A-C）具有与外壁的顶部（37A-C）相比靠近内壁的底部部分（50）。 冷却剂入口孔可以沿着凹陷的底部部分并且沿着侧壁的底部部分定位，以将冷却剂流（44,41）引向内壁上与声学不对准的冲击位置（43） 孔。 这提高了冲击冷却效率。 外壁的峰（37A-C）在共振室中提供用于目标共振的体积。
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公开(公告)号：US09546558B2
公开(公告)日：2017-01-17
申请号：US12832116
申请日：2010-07-08
申请人： Ching-Pang Lee , Danning You , Reinhard Schilp , Chander Prakash
发明人： Ching-Pang Lee , Danning You , Reinhard Schilp , Chander Prakash
CPC分类号： F01D9/023 , F02C7/12 , F05D2260/96 , F23R3/06 , F23R2900/00014
摘要： A resonance chamber (42) has an outer wall (32) with coolant inlet holes (34A-C), an inner wall (36) with acoustic holes (38), and side walls (40A-C) between the inner and outer walls. A depression (33A-C) in the outer wall has a bottom portion (50) that is close to the inner wall compared to peaks (37A-C) of the outer wall. The coolant inlet holes may be positioned along the bottom portion of the depression and along a bottom portion of the side walls to direct coolant flows (44, 51) toward impingement locations (43) on the inner wall that are out of alignment with the acoustic holes. This improves impingement cooling efficiency. The peaks (37A-C) of the outer wall provide volume in the resonance chamber for a target resonance.
摘要翻译： 共振室（42）具有外壁（32），其具有冷却剂入口孔（34A-C），具有声孔（38）的内壁（36）和内壁和外壁之间的侧壁（40A-C） 。 外壁上的凹部（33A-C）具有与外壁的峰（37A-C）相比靠近内壁的底部部分（50）。 冷却剂入口孔可以沿着凹陷的底部部分并且沿着侧壁的底部部分定位，以将冷却剂流（44,41）引向内壁上与声学不对准的冲击位置（43） 孔。 这提高了冲击冷却效率。 外壁的峰（37A-C）在共振室中提供用于目标共振的体积。
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公开(公告)号：US20110302924A1
公开(公告)日：2011-12-15
申请号：US12813658
申请日：2010-06-11
IPC分类号： F02C7/12
CPC分类号： F01D9/023 , F02K1/822 , F05D2250/13 , F05D2250/324 , F05D2260/202 , F23M20/005 , F23R3/002 , F23R3/06 , F23R2900/00014 , F23R2900/03042 , Y02T50/675
摘要： A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume.
摘要翻译： 热燃气通过燃气涡轮发动机的导管。 导管包括具有中心轴线并且限定导管的内部容积以允许热燃气体通过导管的壁结构。 壁结构包括前端，与前端轴向间隔的后端，后端限定用于通过导管的热燃烧气体的燃烧气体出口，以及形成在壁结构中的多个大致径向向外延伸的突起 。 突起各自包括至少一个通过其形成的冷却流体通道，用于允许冷却流体进入内部容积。 突起中的至少一个被成形为使得冷却流体通过它，当它进入内部体积时沿圆周方向发散。
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公开(公告)号：US09810081B2
公开(公告)日：2017-11-07
申请号：US12813658
申请日：2010-06-11
CPC分类号： F01D9/023 , F02K1/822 , F05D2250/13 , F05D2250/324 , F05D2260/202 , F23M20/005 , F23R3/002 , F23R3/06 , F23R2900/00014 , F23R2900/03042 , Y02T50/675
摘要： A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having a central axis and defining an inner volume of the conduit for permitting hot combustion gases to pass through the conduit. The wall structure includes a forward end, an aft end axially spaced from the forward end, the aft end defining a combustion gas outlet for the hot combustion gases passing through the conduit, and a plurality of generally radially outwardly extending protuberances formed in the wall structure. The protuberances each include at least one cooling fluid passage formed therethrough for permitting cooling fluid to enter the inner volume. At least one of the protuberances is shaped so as to cause cooling fluid passing through it to diverge in a circumferential direction as it enters into the inner volume.
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公开(公告)号：US09334741B2
公开(公告)日：2016-05-10
申请号：US12765004
申请日：2010-04-22
CPC分类号： F01D5/182 , B33Y80/00 , F01D5/183 , F01D5/184 , F05D2230/22 , F05D2230/90 , F05D2250/18 , F05D2250/185 , F05D2250/28 , F05D2250/30 , F05D2260/203 , F05D2260/221 , Y10T428/24273
摘要： A wall structure (32, 42, 68, 70, 80) with layers (A, B, C, D, E) of non-random voids (26A, 26B, 28B, 30B) that interconnect to form discretely defined tortuous passages between an interior (21) and an exterior surface (23) of the wall for transpiration cooling of the wall. A coolant flow (38) through the wall may be metered by restrictions in coolant outlets (31) and/or within the passages to minimize the coolant requirement. Pockets (44) may be formed on the exterior surface of the wall for thermal Insulation (46). The layers may be formed by lamination, additive manufacturing, or casting. Layer geometries include alternating layers (A, B, C) with different overlapping void patterns (42), 3-D lattice structures (70), and offset waffle structures (80).
摘要翻译： 具有非随机空隙（26A，26B，28B，30B）的层（A，B，C，D，E）的壁结构（32,42,68,70,80），其互连以在 所述壁的内部（21）和外表面（23）用于所述壁的蒸发冷却。 通过壁的冷却剂流（38）可以通过冷却剂出口（31）和/或通道内的限制来计量，以使冷却剂需求最小化。 口袋（44）可以形成在隔热壁的外表面上（46）。 层可以通过层压，添加剂制造或铸造形成。 层几何形状包括具有不同重叠空白图案（42），3-D网格结构（70）和偏置华夫饼结构（80）的交替层（A，B，C）。
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公开(公告)号：US20120007318A1
公开(公告)日：2012-01-12
申请号：US12832141
申请日：2010-07-08
CPC分类号： F16J15/3292 , F01D11/02 , F05D2240/57
摘要： A seal member for effecting a seal preventing fluid flow in an axial direction through an annular space formed between two relatively moving components including a rotatable shaft and a stator structure. The seal member includes a plurality of flexible seal strips. Each seal strip includes a planar plate extending radially through the annular space and having a radially outer end supported to the stator structure and a radially inner end defining a tip portion extending widthwise in the axial direction engaged in sliding contact with a peripheral surface of the rotatable shaft. At least one of the seal strips includes a plurality of perforations extending through the seal strip and located between a leading edge and a trailing edge of the seal strip for effecting an increased flexibility of the seal strip adjacent to the tip portion.
摘要翻译： 一种用于实现密封的密封件，其防止流体沿轴向流动通过形成在包括可旋转轴和定子结构的两个相对移动部件之间的环形空间。 密封构件包括多个柔性密封条。 每个密封条包括平面板，该平面板径向地延伸穿过环形空间并且具有支撑到定子结构的径向外端，以及限定沿轴向方向沿宽度方向延伸的尖端部分的径向内端，该尖端部分与可旋转的 轴。 密封条中的至少一个包括延伸穿过密封条并且位于密封条的前缘和后缘之间的多个穿孔，用于实现与尖端部分相邻的密封条的增加的柔性。
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7.发明授权Gas turbine engines including lean stator vanes and methods of assembling the same 有权包括精密定子叶片的燃气涡轮发动机及其组装方法公开(公告)号：US07794201B2
公开(公告)日：2010-09-14
申请号：US11615541
申请日：2006-12-22
申请人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Craig Miller Kuhne
发明人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Craig Miller Kuhne
IPC分类号： F01D1/02
CPC分类号： F01D9/041 , F01D5/141 , F01D5/145 , Y02T50/673 , Y10T29/49321 , Y10T29/49323
摘要： A stator vane that may be used in an engine assembly is provided. The stator vane includes an airfoil that has a first sidewall and a second sidewall, which connects to the first sidewall at a leading edge and at a trailing edge. The airfoil also includes a root portion and a tip portion. The first and second sidewalls both extend from the root portion to the tip portion. The airfoil root portion is formed with a negative lean, and the airfoil tip portion is formed with a positive lean.
摘要翻译： 提供可用于发动机组件中的定子叶片。 定子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处连接到第一侧壁。 翼型件还包括根部部分和尖端部分。 第一和第二侧壁都从根部延伸到尖端部分。 翼面根部形成为负的倾斜，并且翼型前端部形成为正的倾斜。
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8.发明申请GAS TURBINE ENGINES INCLUDING LEAN STATOR VANES AND METHODS OF ASSEMBLING THE SAME 有权气体涡轮发动机，包括精密定子风扇及其组装方法公开(公告)号：US20080152504A1
公开(公告)日：2008-06-26
申请号：US11615541
申请日：2006-12-22
申请人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Craig Miller Kuhne
发明人： Scott Andrew Burton , Chander Prakash , Joseph Machnaim , David Glenn Cherry , Robert John Beacock , Ching-Pang Lee , Craig Miller Kuhne
IPC分类号： F01D9/00
CPC分类号： F01D9/041 , F01D5/141 , F01D5/145 , Y02T50/673 , Y10T29/49321 , Y10T29/49323
摘要： A stator vane that may be used in an engine assembly is provided. The stator vane includes an airfoil that has a first sidewall and a second sidewall, which connects to the first sidewall at a leading edge and at a trailing edge. The airfoil also includes a root portion and a tip portion. The first and second sidewalls both extend from the root portion to the tip portion. The airfoil root portion is formed with a negative lean, and the airfoil tip portion is formed with a positive lean.
摘要翻译： 提供可用于发动机组件中的定子叶片。 定子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处连接到第一侧壁。 翼型件还包括根部部分和尖端部分。 第一和第二侧壁都从根部延伸到尖端部分。 翼面根部形成为负的倾斜，并且翼型前端部形成为正的倾斜。
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公开(公告)号：US20070059182A1
公开(公告)日：2007-03-15
申请号：US11162433
申请日：2005-09-09
IPC分类号： B64C27/46
CPC分类号： F01D5/20 , F05D2250/71 , F05D2250/712 , Y02T50/67
摘要： An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil.
摘要翻译： 用于燃气涡轮发动机的翼型件包括根部，尖端，前缘，后缘以及大致沿径向轴线延伸的相对的压力和吸力侧壁。 翼型件包括在压力侧和吸力侧壁之间延伸的顶盖; 并且间隔开的吸入侧和压力侧尖端壁从尖端帽径向向外延伸以在它们之间限定尖端腔。 压力侧末端壁包括连续凹入的弯曲弧形部分，其至少一部分从翼型件的径向轴向向外延伸。
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公开(公告)号：US06984103B2
公开(公告)日：2006-01-10
申请号：US10718465
申请日：2003-11-20
IPC分类号： F03D11/00
CPC分类号： F01D5/187 , Y02T50/673 , Y02T50/676
摘要： A turbine blade includes an airfoil having pressure and suction sidewalls extending between leading and trailing edges, and from root to tip. A dovetail is joined to the airfoil root at a platform. Three internal cooling circuits extend in span inside the airfoil, and each circuit includes a respective inlet channel commencing in axially adjacent alignment in the dovetail. The inlet channels twist together from the dovetail, through the platform, and into the airfoil behind the leading edge in transverse adjacent alignment across the sidewalls.
摘要翻译： 涡轮叶片包括具有在前缘和后缘之间延伸的压力和吸力侧壁以及从根部到尖端的翼型件。 燕尾榫在平台上连接到翼型根部。 三个内部冷却回路在翼型内部的跨度上延伸，并且每个回路包括相应的入口通道，其从燕尾榫开始轴向相邻对准。 入口通道从燕尾榫通过平台扭转在一起，并且横跨相邻的侧壁横向相邻对齐，并进入前缘的后翼。
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