公开(公告)号：US20070059182A1

公开(公告)日：2007-03-15

申请号：US11162433

申请日：2005-09-09

Applicant: Mark Stegemiller ,  Chander Prakash ,  Leslie Leeke ,  Kevin Klasing ,  Ching-Pang Lee

Inventor： Mark Stegemiller ,  Chander Prakash ,  Leslie Leeke ,  Kevin Klasing ,  Ching-Pang Lee

IPC: B64C27/46

CPC classification number: F01D5/20 ,  F05D2250/71 ,  F05D2250/712 ,  Y02T50/67

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US06984103B2

公开(公告)日：2006-01-10

申请号：US10718465

申请日：2003-11-20

Applicant: Ching-Pang Lee ,  Steven Robert Brassfield ,  Chander Prakash

Inventor： Ching-Pang Lee ,  Steven Robert Brassfield ,  Chander Prakash

IPC: F03D11/00

CPC classification number: F01D5/187 ,  Y02T50/673 ,  Y02T50/676

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US07806653B2

公开(公告)日：2010-10-05

申请号：US11615556

申请日：2006-12-22

Applicant: Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

Inventor： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

IPC: F01D9/00

CPC classification number: F01D5/141 ,  F01D5/145 ,  F01D9/041 ,  F05D2240/301 ,  F05D2250/611 ,  F05D2250/71 ,  Y02T50/673

Abstract: A stator vane that may be used in engine assemblies. The stator vane includes an airfoil having a first sidewall and a second sidewall that is coupled to the first sidewall at a leading edge and at a trailing edge. The airfoil extends radially from a root portion to a tip portion. Each of the leading and trailing edges includes at least one lean directional change and a plurality of sweep directional changes that are defined between the root portion and the tip portion.

Abstract translation: 可用于发动机组件的定子叶片。 定子叶片包括具有第一侧壁和第二侧壁的翼型件，其在前缘和后缘处联接到第一侧壁。 翼型件从根部径向延伸到尖端部分。 前缘和后缘中的每一个包括在根部部分和尖端部分之间限定的至少一个瘦方向改变和多个扫掠方向改变。

公开(公告)号：US20080148564A1

公开(公告)日：2008-06-26

申请号：US11615514

申请日：2006-12-22

Applicant: Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

Inventor： Scott Andrew Burton ,  Chander Prakash ,  Joseph Machnaim ,  David Glenn Cherry ,  Robert John Beacock ,  Ching-Pang Lee ,  Scott Michael Carson

IPC: F01D5/02

CPC classification number: F01D9/041 ,  F01D5/141 ,  F01D5/145 ,  Y02T50/673 ,  Y10T29/49236

Abstract: A turbine assembly for a gas turbine engine. The turbine assembly includes at least one stator assembly including a radially inner band and at least one stator vane that extends radially outward from the inner band. The stator vane includes an airfoil having a root portion adjacent to the inner band and a tip portion. The airfoil also includes at least one lean directional change that is defined between the root portion and the tip portion. The turbine assembly also includes at least one turbine blade assembly that includes at least one rotor blade. The blade assembly is coupled in flow communication with the stator assembly such that an axial spacing is defined therebetween. The axial spacing defined adjacent to the at least one lean directional change is wider than the axial spacing defined adjacent to the root portion.

Abstract translation: 一种用于燃气涡轮发动机的涡轮组件。 涡轮机组件包括至少一个定子组件，其包括径向内部带和至少一个定子叶片，其从内部带径向向外延伸。 定子叶片包括具有与内带相邻的根部部分和尖端部分的翼型件。 翼型件还包括限定在根部部分和尖端部分之间的至少一个精简方向变化。 涡轮组件还包括至少一个包括至少一个转子叶片的涡轮叶片组件。 叶片组件与定子组件流体连通地联接，使得在它们之间限定轴向间隔。 与所述至少一个瘦方向变化相邻限定的轴向间隔比邻近根部限定的轴向间隔宽。

公开(公告)号：US06672829B1

公开(公告)日：2004-01-06

申请号：US10196623

申请日：2002-07-16

Applicant: David Glenn Cherry ,  Ching-Pang Lee ,  Chander Prakash ,  Aspi Rustom Wadia ,  Brian David Keith ,  Steven Robert Brassfield

Inventor： David Glenn Cherry ,  Ching-Pang Lee ,  Chander Prakash ,  Aspi Rustom Wadia ,  Brian David Keith ,  Steven Robert Brassfield

IPC: F01D518

CPC classification number: F01D5/141 ,  F01D5/145 ,  F01D5/20 ,  F05D2250/292

Abstract: A turbine blade for a gas turbine engine, including an airfoil and integral dovetail for mounting the airfoil along a radial axis to a rotor disk inboard of a turbine shroud. The airfoil further includes: first and second sidewalls joined together at a leading edge and a trailing edge, where the first and second sidewalls extend from a root disposed adjacent the dovetail to a tip plate for channeling combustion gases thereover; and, at least one tip rib extending outwardly from the tip plate between the leading and trailing edges. The tip rib is oriented so that an axis extending longitudinally therethrough is at an angle with respect to the radial axis for at least a designated portion of an axial length of the turbine blade. Such angle may be substantially the same across the designated portion or may vary thereacross. Accordingly, a recirculation zone of the combustion gases is formed adjacent a distal end of the tip rib which reduces a leakage flow of the combustion gases between the airfoil and the shroud for at least the designated portion of an axial length of the turbine blade.

Abstract translation: 一种用于燃气涡轮发动机的涡轮机叶片，包括翼型件和整体式燕尾榫，用于将翼型件沿着径向轴线安装到涡轮机外罩内侧的转子盘。 所述翼型件还包括：在前缘和后缘处连接在一起的第一和第二侧壁，其中所述第一和第二侧壁从邻近所述燕尾榫设置的根部延伸到顶板，用于在其上引导燃烧气体; 以及在前缘和后缘之间从顶板向外延伸的至少一个尖端肋。 尖端肋被定向成使得纵向延伸通过的轴线相对于径向轴线成一定角度，用于涡轮叶片的至少一个轴向长度的指定部分。 这种角度在指定部分可以是基本相同的，或者可以在其上变化。 因此，燃烧气体的再循环区域形成在尖端肋的远端附近，这减少了涡轮叶片至少轴向长度的指定部分的翼型和护罩之间的燃烧气体的泄漏流。

公开(公告)号：US06382913B1

公开(公告)日：2002-05-07

申请号：US09783279

申请日：2001-02-09

Applicant: Ching-Pang Lee ,  Chander Prakash

Inventor： Ching-Pang Lee ,  Chander Prakash

IPC: F01D518

CPC classification number: F01D5/20 ,  F01D5/141 ,  F01D5/186 ,  F05D2250/70 ,  F05D2260/202

Abstract: A rotor blade for a gas turbine engine including a tip region that facilitates reducing operating temperatures of the rotor blade is described. The tip region includes a first tip wall and a second tip wall extending radially outward from a tip plate of an airfoil. The tip walls extend from adjacent a leading edge of the airfoil to connect at a trailing edge of the airfoil. A portion of the second tip wall is recessed to define a tip shelf that extends from the airfoil leading edge to the airfoil trailing edge.

Abstract translation: 描述了一种用于燃气涡轮发动机的转子叶片，其包括有助于降低转子叶片的操作温度的尖端区域。 尖端区域包括从翼型件的顶板径向向外延伸的第一顶端壁和第二顶端壁。 尖端壁从翼型的前缘相邻延伸，以在翼型的后缘连接。 第二顶壁的一部分是凹进的，以限定从翼型件前缘延伸到翼型后缘的尖端架。

公开(公告)号：US20110302924A1

公开(公告)日：2011-12-15

申请号：US12813658

申请日：2010-06-11

Applicant: Ching-Pang Lee ,  Chander Prakash ,  Reinhard Schilp ,  David A. Little

Inventor： Ching-Pang Lee ,  Chander Prakash ,  Reinhard Schilp ,  David A. Little

IPC: F02C7/12

CPC classification number: F01D9/023 ,  F02K1/822 ,  F05D2250/13 ,  F05D2250/324 ,  F05D2260/202 ,  F23M20/005 ,  F23R3/002 ,  F23R3/06 ,  F23R2900/00014 ,  F23R2900/03042 ,  Y02T50/675

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US06981840B2

公开(公告)日：2006-01-03

申请号：US10692700

申请日：2003-10-24

Applicant: Ching-Pang Lee ,  Ronald Scott Bunker ,  Chander Prakash

Inventor： Ching-Pang Lee ,  Ronald Scott Bunker ,  Chander Prakash

IPC: F03D11/00

CPC classification number: F01D5/187 ,  F05D2260/22141 ,  Y02T50/676

Abstract: A turbine airfoil includes pressure and suction sidewalls extending in chord between leading and trailing edges and in span between a root and a tip. A septum is spaced between the sidewalls to define two cooling circuits on opposite sides of the septum which converge between the leading and trailing edges. An array of pins extends inwardly from the pressure sidewall at a discharge end of the circuits, and the pins decrease in length to conform with the converging circuit.

Abstract translation: 涡轮机翼片包括在前缘和后缘之间延伸并且在根部和尖端之间的跨度中的压力和抽吸侧壁。 隔膜间隔开在侧壁之间以在隔膜的相对侧上限定两个冷却回路，其在前缘和后缘之间会聚。 引脚阵列在电路的放电端从压力侧壁向内延伸，并且引脚的长度减小以符合会聚电路。

公开(公告)号：US20050111977A1

公开(公告)日：2005-05-26

申请号：US10718465

申请日：2003-11-20

Applicant: Ching-Pang Lee ,  Steven Brassfield ,  Chander Prakash

Inventor： Ching-Pang Lee ,  Steven Brassfield ,  Chander Prakash

IPC: F01D5/18 ,  F02C7/18 ,  B63H1/14

CPC classification number: F01D5/187 ,  Y02T50/673 ,  Y02T50/676

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US09206904B2

公开(公告)日：2015-12-08

申请号：US12832141

申请日：2010-07-08

Applicant: Ching-Pang Lee ,  Vincent P. Laurello ,  Chander Prakash ,  Kok-Mun Tham

Inventor： Ching-Pang Lee ,  Vincent P. Laurello ,  Chander Prakash ,  Kok-Mun Tham

IPC: F16J15/32 ,  F01D11/02

CPC classification number: F16J15/3292 ,  F01D11/02 ,  F05D2240/57

Abstract: 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.

Abstract translation: 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。