公开(公告)号：US09004866B2

公开(公告)日：2015-04-14

申请号：US13311630

申请日：2011-12-06

Applicant: Ching-Pang Lee ,  Glenn E. Brown ,  Benjamin E. Heneveld

Inventor： Ching-Pang Lee ,  Glenn E. Brown ,  Benjamin E. Heneveld

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/186 ,  F05D2240/122 ,  F05D2240/304

Abstract: A turbine blade (10) including an airfoil (12) having multiple interior wall portions (70) each separating at least one chamber from another one of multiple chambers (46, 48, 50, 58, 60). In one embodiment a first wall portion (70-2) between first and second chambers (60, 52) includes first and second pluralities of flow paths (86P, 86S) extending through the first wall portion. The first wall portion includes a first region R1 having a first thickness, t, measurable as a distance between the chambers. One of the paths extends a first path distance, d, as measured from an associated path opening (78) in the first chamber (60), through the first region and to an exit opening (82) in the second chamber (52) which path distance is greater than the first thickness.

Abstract translation: 一种涡轮机叶片（10），包括具有多个内壁部分（70）的翼型件（12），每个内壁部分（70）将至少一个腔室与多个腔室（46,48,50,58,60）中的另一个分隔开。 在一个实施例中，第一和第二腔室（60,52）之间的第一壁部分（70-2）包括延伸穿过第一壁部分的第一和第二多个流动路径（86P，86S）。 第一壁部分包括具有第一厚度t的第一区域R1，其可测量为腔室之间的距离。 路径中的一个沿着第一腔室（60）中的相关联的路径开口（78）测量的第一路径距离（d）延伸穿过第一区域并延伸到第二腔室（52）中的出口开口（82） 路径距离大于第一厚度。

公开(公告)号：US08959886B2

公开(公告)日：2015-02-24

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: F23R3/06 ,  F23R3/00 ,  F01D9/02

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：US08951004B2

公开(公告)日：2015-02-10

申请号：US13657923

申请日：2012-10-23

Applicant: Ching-Pang Lee ,  Benjamin E. Heneveld

Inventor： Ching-Pang Lee ,  Benjamin E. Heneveld

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2250/185 ,  F05D2260/22141

Abstract: A cooling arrangement (82) for a gas turbine engine component, the cooling arrangement (82) having a plurality of rows (92, 94, 96) of airfoils (98), wherein adjacent airfoils (98) within a row (92, 94, 96) define segments (110, 130, 140) of cooling channels (90), and wherein outlets (114, 134) of the segments (110, 130) in one row (92, 94) align aerodynamically with inlets (132, 142) of segments (130, 140) in an adjacent row (94, 96) to define continuous cooling channels (90) with non continuous walls (116, 120), each cooling channel (90) comprising a serpentine shape.

Abstract translation: 一种用于燃气涡轮发动机部件的冷却装置（82），所述冷却装置（82）具有多排（92,94,96）的翼型件（98），其中在一排（92,94）内相邻的翼型件 ，96）限定冷却通道（90）的段（110,130,140），并且其中一排（92,94）中的段（110,130）的出口（114,134）在空气动力学上与入口（132， 142）在相邻排（94,96）中的段（130,140），以限定具有非连续壁（116,120）的连续冷却通道（90），每个冷却通道（90）包括蛇形形状。

公开(公告)号：US08920122B2

公开(公告)日：2014-12-30

申请号：US13417714

申请日：2012-03-12

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F01D5/182 ,  F01D5/186

Abstract: A turbine airfoil usable in a turbine engine and having at least one cooling system is disclosed. At least a portion of the cooling system may include one or more cooling channels having a plurality of turbulators protruding from an inner surface and positioned generally nonorthogonal and nonparallel to a longitudinal axis of the airfoil cooling channel. The configuration of turbulators may create a higher internal convective cooling potential for the blade cooling passage, thereby generating a high rate of internal convective heat transfer and attendant improvement in overall cooling performance. This translates into a reduction in cooling fluid demand and better turbine performance.

Abstract translation: 公开了一种可用于涡轮发动机并具有至少一个冷却系统的涡轮机翼型。 冷却系统的至少一部分可以包括一个或多个冷却通道，其具有从内表面突出并且大致非正交且不平行于翼型冷却通道的纵向轴线定位的多个紊流器。 紊流器的结构可能会为叶片冷却通道产生更高的内部对流冷却潜力，从而产生较高的内部对流热传递速率，并提高总体冷却性能。 这意味着冷却液需求的减少和涡轮机性能的提高。

公开(公告)号：US08894367B2

公开(公告)日：2014-11-25

申请号：US12884464

申请日：2010-09-17

Applicant: Ching-Pang Lee ,  Nan Jiang ,  John J. Marra ,  Ronald J. Rudolph

Inventor： Ching-Pang Lee ,  Nan Jiang ,  John J. Marra ,  Ronald J. Rudolph

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/187 ,  F05D2250/181 ,  F05D2250/60 ,  F05D2250/611 ,  F05D2250/70 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: Multi-scale turbulation features, including first turbulators (46, 48) on a cooling surface (44), and smaller turbulators (52, 54, 58, 62) on the first turbulators. The first turbulators may be formed between larger turbulators (50). The first turbulators may be alternating ridges (46) and valleys (48). The smaller turbulators may be concave surface features such as dimples (62) and grooves (54), and/or convex surface features such as bumps (58) and smaller ridges (52). An embodiment with convex turbulators (52, 58) in the valleys (48) and concave turbulators (54, 62) on the ridges (46) increases the cooling surface area, reduces boundary layer separation, avoids coolant shadowing and stagnation, and reduces component mass.

Abstract translation: 多尺度紊流特征，包括在冷却表面（44）上的第一湍流器（46,48）和在第一湍流器上的较小湍流器（52,54,58,62）。 可以在较大的湍流器（50）之间形成第一湍流器。 第一个紊流器可以是交替的脊（46）和谷（48）。 较小的湍流器可以是诸如凹坑（62）和凹槽（54）的凹表面特征，和/或诸如凸块（58）和较小脊（52）的凸表面特征。 在脊（46）上的谷（48）和凹形湍流器（54,62）中具有凸起的湍流器（52,58）的实施例增加了冷却表面面积，减少了边界层分离，避免了冷却剂遮蔽和停滞，并且减少了部件 质量

公开(公告)号：US08894352B2

公开(公告)日：2014-11-25

申请号：US13213459

申请日：2011-08-19

Applicant: Eric C. Berrong ,  Ching-Pang Lee ,  Akash Bhatia ,  Ryan S. Yamane ,  Stefan Tschirren ,  Leonard J. Meyer

Inventor： Eric C. Berrong ,  Ching-Pang Lee ,  Akash Bhatia ,  Ryan S. Yamane ,  Stefan Tschirren ,  Leonard J. Meyer

IPC: F01D25/08 ,  F01D11/08

CPC classification number: F01D11/08 ,  F05D2250/70 ,  F05D2260/20

Abstract: A ring segment is provided for a gas turbine engine includes a panel and a cooling system. Cooling fluid is provided to an outer side of the panel and an inner side of the panel defines at least a portion of a hot gas flow path through the engine. The cooling system is located within that panel and receives cooling fluid from the outer side of the panel for cooling the panel. The cooling system includes a plurality of cooling fluid passages that receive cooling fluid from the outer side of the panel. The cooling fluid passages each have a generally axially extending portion that includes at least one fork. The fork(s) divide each cooling fluid passage into at least two downstream portions that each receives cooling fluid from the respective axially extending portion.

Abstract translation: 提供了一种用于燃气涡轮发动机的环段，其包括面板和冷却系统。 冷却流体设置在面板的外侧，并且面板的内侧限定通过发动机的热气体流路的至少一部分。 冷却系统位于该面板内并从面板的外侧接收冷却流体以冷却面板。 冷却系统包括从板的外侧接收冷却流体的多个冷却流体通道。 冷却流体通道各自具有包括至少一个叉的大致轴向延伸的部分。 叉子将每个冷却流体通道分成至少两个下游部分，每个下游部分从相应的轴向延伸部分接收冷却流体。

公开(公告)号：US08882448B2

公开(公告)日：2014-11-11

申请号：US14048074

申请日：2013-10-08

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18

CPC classification number: F01D5/18 ,  F01D5/186 ,  F01D5/187 ,  F05D2240/122 ,  F05D2240/304 ,  F05D2250/183 ,  F05D2260/202

Abstract: An airfoil in a gas turbine engine includes an outer wall, a cooling fluid cavity, a plurality of cooling fluid passages, and a plurality of radial passageways. The outer wall has leading and trailing edges, pressure and suction sides, and radially inner and outer ends. The cooling fluid cavity is defined in the outer wall and receives cooling fluid for cooling the outer wall. The cooling fluid passages are in fluid communication with the cooling fluid cavity and include alternating angled sections, each section having both a radial component and a chordal component. The cooling fluid passages extend from the cooling fluid cavity toward the trailing edge of the outer wall and receive cooling fluid from the cooling fluid cavity for cooling the outer wall near the trailing edge. The radial passageways interconnect radially adjacent cooling fluid passages.

Abstract translation: 燃气涡轮发动机中的翼型件包括外壁，冷却流体腔，多个冷却流体通道和多个径向通道。 外壁具有前缘和后缘，压力和吸力侧以及径向内外端。 冷却流体腔被限定在外壁中并且接收用于冷却外壁的冷却流体。 冷却流体通道与冷却流体腔流体连通，并且包括交替成角度的部分，每个部分都具有径向分量和弦状分量。 冷却流体通道从冷却流体腔朝向外壁的后缘延伸，并接收来自冷却流体腔的冷却流体，用于冷却靠近后缘的外壁。 径向通道将径向相邻的冷却流体通道相互连接。

公开(公告)号：US08866084B2

公开(公告)日：2014-10-21

申请号：US13604668

申请日：2012-09-06

Applicant: Erwan Baleine ,  James F. Landy ,  Ching-Pang Lee ,  Stephanie Stinelli

Inventor： Erwan Baleine ,  James F. Landy ,  Ching-Pang Lee ,  Stephanie Stinelli

IPC: G01J5/02

CPC classification number: G01J5/522 ,  G01J5/0088 ,  G01J2005/0048 ,  G01J2005/0077 ,  G01J2005/0081 ,  G01N25/72

Abstract: A method of nondestructive evaluation and related system. The method includes arranging a test piece (14) having an internal passage (18) and an external surface (15) and a thermal calibrator (12) within a field of view (42) of an infrared sensor (44); generating a flow (16) of fluid characterized by a fluid temperature; exposing the test piece internal passage (18) and the thermal calibrator (12) to fluid from the flow (16); capturing infrared emission information of the test piece external surface (15) and of the thermal calibrator (12) simultaneously using the infrared sensor (44), wherein the test piece infrared emission information includes emission intensity information, and wherein the thermal calibrator infrared emission information includes a reference emission intensity associated with the fluid temperature; and normalizing the test piece emission intensity information against the reference emission intensity.

Abstract translation: 一种无损检测方法及相关系统。 该方法包括在红外传感器（44）的视场（42）内布置具有内部通道（18）和外表面（15）和热校准器（12）的测试件（14）。 产生以流体温度为特征的流体流（16）; 将测试件内部通道（18）和热校准器（12）暴露于来自流动（16）的流体; 使用红外传感器（44）同时捕获测试件外表面（15）和热校准器（12）的红外发射信息，其中测试件红外发射信息包括发射强度信息，并且其中热校准器红外发射信息 包括与流体温度相关联的参考发射强度; 并根据参考发射强度对测试片发射强度信息进行归一化。

公开(公告)号：US08827632B1

公开(公告)日：2014-09-09

申请号：US14084708

申请日：2013-11-20

Applicant: Ching-Pang Lee ,  Kerri Santucci ,  Gilles Carrier

Inventor： Ching-Pang Lee ,  Kerri Santucci ,  Gilles Carrier

IPC: F01D5/18

CPC classification number: F01D5/188 ,  F01D5/288 ,  F01D9/065

Abstract: An integrated thermal barrier coating and cooling flow metering plate for a turbine vane are disclosed. On an existing vane design, the thickness of the thermal barrier coating is increased in order to provide more thermal protection around the vane material itself. The increased insulation around the vane allows the volume of cooling air flow to be reduced, while still maintaining the vane temperature within specification. The reduced cooling air flow is obtained by adding a flow metering plate at the inlet of a vane trailing edge cooling circuit, thereby increasing turbine efficiency via reduced cooling air flow requirements, while allowing an existing vane casting design to be used.

Abstract translation: 公开了一种用于涡轮叶片的集成热障涂层和冷却流量计量板。 在现有的叶片设计上，增加了隔热涂层的厚度，以便在叶片材料本身周围提供更多的热保护。 在叶片周围增加的绝缘体允许降低冷却空气流量，同时仍保持叶片温度在规定范围内。 通过在叶片后缘冷却回路的入口处添加流量计量板来获得减少的冷却空气流，从而通过降低冷却空气流量要求来提高涡轮机效率，同时允许使用现有的叶片铸造设计。

公开(公告)号：US08820091B2

公开(公告)日：2014-09-02

申请号：US13670788

申请日：2012-11-07

Applicant: Kok-Mun Tham ,  Ching-Pang Lee ,  Vincent P. Laurello ,  Abdullatif M. Chehab ,  David A. Kemp ,  John A. Fussner ,  Yan Yin ,  Bijay K. Sultanian ,  Weidong Cai

Inventor： Kok-Mun Tham ,  Ching-Pang Lee ,  Vincent P. Laurello ,  Abdullatif M. Chehab ,  David A. Kemp ,  John A. Fussner ,  Yan Yin ,  Bijay K. Sultanian ,  Weidong Cai

IPC: F02C6/04 ,  F02C7/12

CPC classification number: F02C7/12 ,  F01D5/088 ,  F01D21/00 ,  F01D25/12 ,  F01D25/34 ,  F05D2270/3032

Abstract: A cooling fluid air injection system for use in a gas turbine engine includes at an external cooling fluid source, at least one rotor cooling pipe, which is used to inject cooling fluid from the source into a rotor chamber, a piping system that provides fluid communication between the source and the rotor cooling pipe(s), a blower system for conveying the cooling fluid through the piping system and the rotor cooling pipe(s) into the rotor chamber, and a valve system. The valve system is closed during full load engine operation to prevent cooling fluid from the source from passing through the piping system, and open during less than full load engine operation to allow cooling fluid from the source to pass through the piping system.

Abstract translation: 用于燃气涡轮发动机的冷却流体空气喷射系统包括在外部冷却流体源处的至少一个转子冷却管，其用于将来自所述源的冷却流体注入到转子室中;提供流体连通的管道系统 在源和转子冷却管之间，用于将冷却流体通过管道系统和转子冷却管输送到转子室中的鼓风机系统和阀系统。 在全负载发动机运行期间，阀系统关闭，以防止来自源的冷却流体通过管道系统，并且在小于满载发动机运行期间打开以允许来自源的冷却流体通过管道系统。