公开(公告)号：US20120177503A1

公开(公告)日：2012-07-12

申请号：US12985553

申请日：2011-01-06

Applicant: Ching-Pang Lee ,  John J. Marra ,  Gary B. Merrill ,  Benjamine E. Heneveld ,  Jill Klinger

Inventor： Ching-Pang Lee ,  John J. Marra ,  Gary B. Merrill ,  Benjamine E. Heneveld ,  Jill Klinger

IPC: F01D5/18 ,  F28F7/00

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2240/304 ,  F05D2250/13 ,  F05D2260/2214 ,  F28F3/048 ,  F28F7/02

Abstract: A cooling channel (36, 36B) cools an exterior surface (40 or 42) or two opposed exterior surfaces (40 and 42). The channel has a near-wall inner surface (48, 50) with a width (W1). Interior side surfaces (52, 54) may converge to a reduced channel width (W2). The near-wall inner surface (48, 50) may have fins (44) aligned with a coolant flow (22). The fins may highest at mid-width of the near-wall inner surface. A two-sided cooling channel (36) may have two near-wall inner surfaces (48, 50) parallel to two respective exterior surfaces (40, 42), and may have an hourglass shaped transverse sectional profile. The tapered channel width (W1, W2) and the fin height profile (56A, 56B) increases cooling flow (22) into the corners (C) of the channel for more uniform and efficient cooling.

Abstract translation: 冷却通道（36,36B）冷却外表面（40或42）或两个相对的外表面（40和42）。 通道具有宽度（W1）的近壁内表面（48,50）。 内侧表面（52,54）可以会聚到减小的通道宽度（W2）。 近壁内表面（48,50）可以具有与冷却剂流（22）对准的翅片（44）。 翅片在近壁内表面的中间宽度处可能最高。 双面冷却通道（36）可以具有两个平行于两个相应的外表面（40,42）的近壁内表面（48,50），并且可以具有沙漏形横截面轮廓。 锥形通道宽度（W1，W2）和翅片高度轮廓（56A，56B）将冷却流（22）增加到通道的拐角（C），以实现更均匀和有效的冷却。

公开(公告)号：US20120051900A1

公开(公告)日：2012-03-01

申请号：US12872485

申请日：2010-08-31

Applicant: Jeffery Donald Clements ,  Vidhu Shekhar Pandey ,  Ching-Pang Lee

Inventor： Jeffery Donald Clements ,  Vidhu Shekhar Pandey ,  Ching-Pang Lee

IPC: F01D1/02

CPC classification number: F01D9/02 ,  F01D9/04

Abstract: A turbine nozzle includes an array of turbine vanes between inner and outer bands. Each vane includes opposed pressure and suction sides extending between opposed leading and trailing edges. The vanes define a plurality of flow passages each of which is bounded between the inner band, the outer band, and adjacent first and second vanes. A surface of the inner band in each of the passages is contoured in a non-axisymmetric shape including a peak of relatively higher radial height adjoining the pressure side of the first vane adjacent its leading edge, and a trough of relatively lower radial height is disposed parallel to and spaced-away from the suction side of the second vane aft of its leading edge. The peak and trough define cooperatively define an arcuate channel extending axially along the inner band between the first and second vanes.

Abstract translation: 涡轮喷嘴包括在内带和外带之间的涡轮叶片阵列。 每个叶片包括在相对的前缘和后缘之间延伸的相对的压力和吸力侧。 叶片限定多个流动通道，每个流动通道限定在内带，外带和相邻的第一和第二叶片之间。 每个通道中的内带表面的轮廓是非轴对称的形状，包括邻近第一叶片邻近其前缘的压力侧相对较高的径向高度的峰，并且设置相对较低径向高度的槽 平行于其前缘的第二叶片后部的吸入侧并与其间隔开。 峰和槽限定协同地限定沿着第一和第二叶片之间的内带轴向延伸的弓形通道。

公开(公告)号：US20120051894A1

公开(公告)日：2012-03-01

申请号：US12872770

申请日：2010-08-31

Applicant: Jeffrey Donald Clements ,  Vidhu Shekhar Pandey ,  Ching-Pang Lee

Inventor： Jeffrey Donald Clements ,  Vidhu Shekhar Pandey ,  Ching-Pang Lee

IPC: F04D29/44

CPC classification number: F01D9/041 ,  F01D5/143

Abstract: A turbine apparatus includes: A first nozzle comprising an array of first vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; A rotor downstream from the first nozzle comprising a plurality of blades carried by a rotatable disk; and a second nozzle disposed downstream from the rotor comprising an array of second vanes each including a concave pressure side, a convex suction side, and leading and trailing edges; wherein the first and second vanes of the first and second nozzles are circumferentially clocked relative to each other such that, in a predetermined operating condition, wakes discharged from the first vanes are aligned in a circumferential direction with the leading edges of the second vanes, wherein a stacking axis of the first vanes is nonlinear. An inner band of the first nozzle is contoured in a non-axisymmetric shape.

Abstract translation: 涡轮装置包括：第一喷嘴，包括第一叶片阵列，每个叶片包括凹压侧，凸吸入侧，以及前缘和后缘; 第一喷嘴下游的转子包括由可旋转盘承载的多个叶片; 以及设置在所述转子的下游的第二喷嘴，包括第二叶片的阵列，每个叶片包括凹压侧，凸吸入侧以及前缘和后缘; 其中所述第一和第二喷嘴的所述第一和第二叶片相对于彼此沿圆周方向定时，使得在预定操作条件下，从所述第一叶片排出的骤冷器沿周向与所述第二叶片的前缘对齐，其中 第一叶片的堆叠轴线是非线性的。 第一喷嘴的内带是非轴对称的形状。

公开(公告)号：US08104292B2

公开(公告)日：2012-01-31

申请号：US11957653

申请日：2007-12-17

Applicant: Ching-Pang Lee ,  Geoffrey Douglas Robinson ,  Robert Joseph Orlando

Inventor： Ching-Pang Lee ,  Geoffrey Douglas Robinson ,  Robert Joseph Orlando

IPC: F03B11/00

CPC classification number: F01D9/04 ,  F01D5/186 ,  F01D5/187 ,  F01D25/08 ,  F05D2240/11 ,  F05D2260/201 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A gas turbine engine shroud includes a row of different first and second shroud segments alternating circumferentially therearound. The first segments have a first pattern of first cooling holes extending therethrough. The second segments have a second pattern of second cooling holes extending therethrough. The corresponding patterns have different collective flowrate capabilities.

Abstract translation: 燃气涡轮发动机护罩包括一排不同的第一和第二护罩段，沿周向交替排列。 第一段具有延伸穿过其中的第一冷却孔的第一图案。 第二段具有延伸穿过其中的第二冷却孔的第二图案。 相应的模式具有不同的集体流量能力。

公开(公告)号：US20120006518A1

公开(公告)日：2012-01-12

申请号：US12832124

申请日：2010-07-08

Applicant: Ching-Pang Lee ,  Humberto A. Zuniga ,  Jay A. Morrison

Inventor： Ching-Pang Lee ,  Humberto A. Zuniga ,  Jay A. Morrison

IPC: F28F7/00

CPC classification number: F23R3/005 ,  F01D9/023 ,  F23R3/06 ,  F23R2900/03042 ,  F23R2900/03043 ,  F23R2900/03044 ,  F23R2900/03045

Abstract: A conduit through which hot combustion gases pass in a gas turbine engine. The conduit includes a wall structure having an inner surface, an outer surface, a region, an inlet, and an outlet. The inner surface defines an inner volume of the conduit. The region extends between the inner and outer surfaces and includes cooling fluid structure defining a plurality of cooling passageways. The inlet extends inwardly from the outer surface and provides fluid communication between the inlet and the passageways. The outlet extends from the passageways to the inner surface to provide fluid communication between the passageways and the inner volume. At least one first cooling passageway intersects with at least one second cooling passageway such that cooling fluid flowing through the first cooling passageway interacts with cooling fluid flowing through the second cooling passageway.

Abstract translation: 热燃气通过燃气涡轮发动机的导管。 导管包括具有内表面，外表面，区域，入口和出口的壁结构。 内表面限定导管的内部容积。 该区域在内表面和外表面之间延伸并且包括限定多个冷却通道的冷却流体结构。 入口从外表面向内延伸，并在入口和通道之间提供流体连通。 出口从通道延伸到内表面以在通道和内部容积之间提供流体连通。 至少一个第一冷却通道与至少一个第二冷却通道相交，使得流过第一冷却通道的冷却流体与流过第二冷却通道的冷却流体相互作用。

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：US20110171023A1

公开(公告)日：2011-07-14

申请号：US12908029

申请日：2010-10-20

Applicant: Ching-Pang Lee ,  John J. Marra

Inventor： Ching-Pang Lee ,  John J. Marra

IPC: F01D5/18 ,  B28B7/28

CPC classification number: F01D5/187 ,  B22C9/103 ,  F05D2230/21 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/18 ,  F05D2250/292

Abstract: A gas turbine engine (10) and an airfoil (50) for use therein, the airfoil (50) having a structure (128) containing cooling passageways (110, 120) extending between a chamber (100) and a series of apertures (78) positioned along the trailing edge (72) through which cooling fluid (144) received from the chamber (100) exits the airfoil (50), wherein the structure (128) is characterized by a variable thickness (t) between the pressure and suction sidewalls (74, 76) of the airfoil as a function of position along the cooling passageways (110, 120) such that each in a plurality of cooling passageways are characterized by a cross sectional flow area (170, 174) which decreases as a function of distance from the chamber (100).

Abstract translation: 一种用于其中的燃气涡轮发动机（10）和翼型件（50），所述翼型件（50）具有包括在室（100）和一系列孔（78）之间延伸的冷却通道（110,120）的结构 ），其沿着所述后缘（72）定位，冷却流体（144）从所述腔室（100）接收的所述后缘离开所述翼型件（50），其中所述结构（128）的特征在于所述压力和抽吸 作为沿着冷却通道（110,120）的位置的函数的翼型件的侧壁（74,76），使得在多个冷却通道中的每一个的特征在于作为功能而减小的横截面流动面积（170,174） 距离室（100）的距离。

公开(公告)号：US07976274B2

公开(公告)日：2011-07-12

申请号：US11297699

申请日：2005-12-08

Applicant: Ching-Pang Lee ,  Joseph M. Guentert ,  Wenfeng Lu ,  Mitchell E. Iles

Inventor： Ching-Pang Lee ,  Joseph M. Guentert ,  Wenfeng Lu ,  Mitchell E. Iles

IPC: F01D9/04

CPC classification number: F01D9/041 ,  F01D5/143 ,  F01D5/145 ,  F01D9/02 ,  F05D2240/81 ,  Y02T50/673 ,  Y02T50/676

Abstract: A method facilitates the assembly of a gas turbine engine. The method of assembly comprises providing a turbine nozzle including an inner band, an outer band, at least one vane extending between the inner and outer bands, and at least one leading edge fillet extending between the at least one vane and at least one of the inner and outer bands, wherein a leading edge of the at least one vane is downstream from the leading edges of the inner and outer bands, and coupling the turbine nozzle within the gas turbine engine such that the leading edge fillet is configured to facilitate minimizing vortex formation along the vane leading edge adjacent at least one of the inner and outer bands.

Abstract translation: 一种方法有助于燃气涡轮发动机的组装。 组装方法包括提供涡轮喷嘴，该涡轮喷嘴包括内带，外带，在内带和外带之间延伸的至少一个叶片，以及在至少一个叶片和至少一个叶片之间延伸的至少一个前缘圆角 内部和外部带，其中所述至少一个叶片的前缘在所述内部和外部带的前缘的下游，以及将所述涡轮喷嘴连接在所述燃气涡轮发动机内，使得所述前缘圆角被配置为有助于最小化涡旋 沿着与内带和外带中的至少一个相邻的叶片前缘的形成。

公开(公告)号：US07870742B2

公开(公告)日：2011-01-18

申请号：US11595606

申请日：2006-11-10

Applicant: Ching-Pang Lee ,  Thomas Ory Moniz ,  Robert Joseph Orlando

Inventor： Ching-Pang Lee ,  Thomas Ory Moniz ,  Robert Joseph Orlando

IPC: F02C6/08

CPC classification number: F01D5/088 ,  F01D5/082 ,  F05D2260/20 ,  Y02T50/672 ,  Y02T50/676

Abstract: A gas turbine engine includes a compressor, combustor, and high pressure (HP) turbine operatively joined together. An interstage cooling circuit is joined in flow communication from an intermediate stage of the compressor to a forward face of an HP disk supporting a row of turbine blades for channeling interstage bleed cooling air thereto.

Abstract translation: 燃气涡轮发动机包括可操作地连接在一起的压缩机，燃烧器和高压（HP）涡轮机。 级间冷却回路从压缩机的中间阶段流动连接到支撑一排涡轮机叶片的HP盘的前面，用于将级间排放冷却空气引导到其中。

公开(公告)号：US07819626B2

公开(公告)日：2010-10-26

申请号：US11580789

申请日：2006-10-13

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Scott Michael Carson

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Scott Michael Carson

IPC: F01D11/20 ,  F01D11/24

CPC classification number: F01D11/20 ,  F05D2270/172 ,  Y02T50/671 ,  Y10S415/914

Abstract: A gas turbine engine plasma blade tip clearance control system includes an annular shroud surrounding rotatable blade tips and an annular plasma generator spaced radially outwardly and apart from the blade tips. An exemplary embodiment of the annular plasma generator is mounted to the annular shroud and includes radially inner and outer electrodes separated by a dielectric material disposed within an annular groove in a radially inwardly facing surface of the annular shroud. The plasma generator is operable for producing an annular plasma between the annular shroud and blade tips and an effective clearance produced by the annular plasma between the annular shroud and blade tips that is smaller than a clearance between the annular shroud and blade tips.

Abstract translation: 燃气涡轮发动机等离子体叶片顶端间隙控制系统包括围绕可旋转叶片尖端的环形护罩和沿径向向外并与叶片尖端分开的环形等离子体发生器。 环形等离子体发生器的示例性实施例安装到环形护罩，并且包括径向内部和外部电极，该电极由设置在环形护罩的径向向内的表面中的环形槽内的电介质材料隔开。 等离子体发生器可操作用于在环形护罩和叶片尖端之间产生环形等离子体，以及由环形护罩和叶片尖端之间的环形等离子体产生的有效间隙小于环形罩和叶片尖端之间的间隙。