公开(公告)号：US07377746B2

公开(公告)日：2008-05-27

申请号：US11062001

申请日：2005-02-21

Applicant: Steven Robert Brassfield ,  Ching-Pang Lee ,  Roger Lee Doughty ,  Richard William Jendrix ,  Cory Michael Williams

Inventor： Steven Robert Brassfield ,  Ching-Pang Lee ,  Roger Lee Doughty ,  Richard William Jendrix ,  Cory Michael Williams

IPC: F03D11/02

CPC classification number: F01D5/18 ,  B22C9/043 ,  F05D2230/21 ,  Y02T50/676 ,  Y10T29/49243 ,  Y10T29/49245

Abstract: An airfoil is disclosed having at least first and second cast, axially-stacked internal airflow cooling circuits. Each circuit defines multiple air flow passages positioned laterally between a pressure sidewall side and a suction sidewall side of respective ones of the circuits. Each of the circuits is formed by a separate casting core. Methods of forming a axially-stacked core and an airfoil are also disclosed.

Abstract translation: 公开了一种具有至少第一和第二铸造，轴向堆叠的内部气流冷却回路的翼型件。 每个回路限定了多个气流通道，其横向位于各个电路的压力侧壁侧和吸力侧壁侧之间。 每个电路由单独的铸造芯形成。 还公开了形成轴向堆叠的芯和翼型的方法。

公开(公告)号：US20080101913A1

公开(公告)日：2008-05-01

申请号：US11591264

申请日：2006-10-31

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  David Glenn Cherry ,  Je-Chin Han

IPC: F04D27/02

CPC classification number: F01D5/145 ,  F01D9/041 ,  F01D17/162 ,  F05D2260/20 ,  F05D2270/17 ,  F05D2270/172 ,  Y02T50/673 ,  Y02T50/676 ,  Y10S415/914

Abstract: A plasma boundary layer lifting system includes at least one gas turbine engine vane having a spanwise extending airfoil with an outer surface extending in a chordwise direction between opposite leading and trailing edges and chordwise spaced apart plasma generators for producing a plasma extending in the chordwise direction along the outer surface. Each plasma generator may include inner and outer electrodes separated by a dielectric material disposed within a spanwise extending groove in the outer surface. The airfoil may be hollow having an outer wall and the plasma generators being mounted on the outer wall. A method for operating the system includes forming a plasma extending in the chordwise direction along the outer surface of the airfoil. The method may further include operating the plasma generators in steady state or unsteady modes.

Abstract translation: 等离子体边界层提升系统包括至少一个燃气涡轮发动机叶片，其具有翼展方向延伸的翼型件，其外表面沿相反的前缘和后缘之间的弦向延伸，以及弦向间隔开的等离子体发生器，用于产生沿着弦方向延伸的等离子体 外表面。 每个等离子体发生器可以包括由设置在外表面中的翼展方向延伸凹槽内的电介质材料隔开的内电极和外电极。 翼型件可以是中空的，具有外壁，等离子体发生器安装在外壁上。 用于操作该系统的方法包括形成沿着翼型的外表面沿着弦方向延伸的等离子体。 该方法还可以包括以稳态或不稳定模式操作等离子体发生器。

公开(公告)号：US20080031738A1

公开(公告)日：2008-02-07

申请号：US11069869

申请日：2005-03-01

Applicant: Ching-Pang Lee

Inventor： Ching-Pang Lee

IPC: F01D5/18

CPC classification number: F01D5/186 ,  F01D5/18 ,  F05D2200/24 ,  F05D2250/20 ,  F05D2250/26 ,  F05D2250/292 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine airfoil a plurality of cooling holes formed in the external surface of the airfoil in fluid communication with a cooling circuit. The cooling holes have a metering section and a diffuser section opening to the external surface of the airfoil. The diffuser section has top, bottom and opposed side walls, where at least the opposed side walls and one or the other of the top and bottom walls of the diffuser section have a downstream diverging, bell-shaped configuration for achieving a flow of the cooling film from the cooling circuit with enhanced spread, enhanced attachment and less turbulence to a downstream surface of the airfoil local to each respective cooling hole.

Abstract translation: 涡轮机翼型件形成在与冷却回路流体连通的翼型件的外表面中的多个冷却孔。 冷却孔具有通向翼型件的外表面的计量部分和扩散部分。 扩散器部分具有顶部，底部和相对的侧壁，其中至少相对的侧壁和扩散器部分的顶壁和底壁中的一个或另一个具有下游发散的钟形构造，用于实现冷却 来自冷却回路的膜具有增强的扩散，增强的附着和较少的湍流到局部于每个相应的冷却孔的翼型的下游表面。

公开(公告)号：US07296973B2

公开(公告)日：2007-11-20

申请号：US11294063

申请日：2005-12-05

Applicant: Ching-Pang Lee ,  Aspi Rustom Wadia ,  Steven Robert Brassfield

Inventor： Ching-Pang Lee ,  Aspi Rustom Wadia ,  Steven Robert Brassfield

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2250/185 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade includes an airfoil having opposite pressure and suction sidewalls joined together at opposite leading and trailing edges and extending longitudinally from root to tip. A plurality of independent cooling circuits are disposed inside the airfoil correspondingly along the pressure and suction sidewalls thereof. A first serpentine circuit is disposed along the pressure sidewall. A second serpentine circuit is disposed along the suction sidewall in parallel with the first circuit. And a third impingement circuit is disposed at the leading edge forward of the first and second circuits.

Abstract translation: 涡轮机叶片包括具有相对的压力和抽吸侧壁的翼型件，其在相对的前缘和后缘处连接在一起并且从根部到尖端纵向延伸。 多个独立的冷却回路相应地沿其压力和吸力侧壁设置在翼型内。 第一蛇形电路沿着压力侧壁设置。 第二蛇形电路沿着吸力侧壁与第一回路并联设置。 并且第三冲击电路设置在第一和第二电路的前方的前缘。

公开(公告)号：US20070237637A1

公开(公告)日：2007-10-11

申请号：US11211391

申请日：2005-08-25

Applicant: Ching-Pang Lee ,  Nicholas Palmer ,  Kevin Kirkeng

Inventor： Ching-Pang Lee ,  Nicholas Palmer ,  Kevin Kirkeng

IPC: F01D5/18

CPC classification number: F01D5/20 ,  F01D11/08 ,  F05D2240/307 ,  F05D2250/292 ,  F05D2250/38 ,  F05D2260/20 ,  F05D2260/202 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine blade includes a hollow airfoil having a plurality of bowed tip holes extending through a tip floor thereof and skewed toward a squealer rib extending outwardly from the floor.

Abstract translation: 涡轮机叶片包括具有延伸穿过其尖端底部的多个弓形尖端孔的中空翼型件，并且朝着从地板向外延伸的尖叫肋条倾斜。

公开(公告)号：US20070214795A1

公开(公告)日：2007-09-20

申请号：US11376507

申请日：2006-03-15

Applicant: Paul Cooker ,  Robert Orlando ,  Ching-Pang Lee ,  Kattalaicheri Venkataramani

Inventor： Paul Cooker ,  Robert Orlando ,  Ching-Pang Lee ,  Kattalaicheri Venkataramani

IPC: F02C1/00

CPC classification number: F02K1/06 ,  F02C9/22 ,  F02C9/28 ,  F02K1/08 ,  F02K1/09 ,  F02K3/06 ,  F05D2270/112 ,  F05D2270/303 ,  F05D2270/3032

Abstract: A method and system for maintaining a limiting gas temperature in a gas turbine engine working fluid flowpath by monitoring the gas temperature and adjusting one or more parameters when the gas temperature exceeds a predetermined or a calculated temperature limit during engine operation. The parameters include one or more of a group of engine parameters including high and low pressure turbine nozzle flow areas, fan and core flow areas, and a rotor speed. The one or more parameters are adjusted to lower the gas temperature to below the temperature limit during engine operation. The limiting gas temperature may be a turbine exhaust gas temperature such as a high pressure turbine exhaust gas temperature. The turbine nozzle flow areas may be adjusted with variable nozzle vanes and the fan and core exhaust nozzle flow areas with a translatable fan nozzle cowling and a translatable core nozzle plug, respectively.

Abstract translation: 一种用于通过监测气体温度并在发动机运行期间当气体温度超过预定或计算的温度极限时调节一个或多个参数来维持燃气涡轮发动机工作流体流路中的限制气体温度的方法和系统。 这些参数包括一组发动机参数中的一个或多个，包括高压和低压涡轮喷嘴流动区域，风扇和核心流动区域以及转子速度。 调节一个或多个参数以在发动机运行期间将气体温度降低到温度极限以下。 限制气体温度可以是涡轮机废气温度，例如高压汽轮机废气温度。 涡轮喷嘴流动面积可以分别用可变喷嘴叶片和风扇和核心排气喷嘴流动区域调节，其中分别具有可平移的风扇喷嘴罩和可平移的芯喷嘴塞。

公开(公告)号：US20070128034A1

公开(公告)日：2007-06-07

申请号：US11294218

申请日：2005-12-05

Applicant: Ching-Pang Lee ,  Aspi Wadia ,  Steven Brassfield

Inventor： Ching-Pang Lee ,  Aspi Wadia ,  Steven Brassfield

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2240/121 ,  F05D2240/303 ,  F05D2250/185 ,  F05D2260/201 ,  Y02T50/671 ,  Y02T50/673 ,  Y02T50/676

Abstract: A turbine airfoil includes pressure and suction sidewalls spaced apart to define flow channels extending in span and separated by ribs. Side channels are disposed along one sidewall and spaced from the opposite sidewall by the ribs, and a mid channel bridges the sidewalls. The side and mid channels are arranged in a zigzag serpentine cooling circuit alternating therebetween for transferring heat from the sidewall into the mid channel.

公开(公告)号：US20070089424A1

公开(公告)日：2007-04-26

申请号：US11256786

申请日：2005-10-24

Applicant: Kattalaicheri Venkataramani ,  William Myers ,  Robert Orlando ,  Paul Cooker ,  Ching-Pang Lee

Inventor： Kattalaicheri Venkataramani ,  William Myers ,  Robert Orlando ,  Paul Cooker ,  Ching-Pang Lee

IPC: F02C9/26

CPC classification number: F02C9/263 ,  F05D2270/112 ,  F05D2270/3032 ,  F23K5/005 ,  F23K5/06 ,  F23K2203/105 ,  F23N1/00 ,  F23N1/002 ,  F23N5/02 ,  F23N5/022 ,  F23N5/24 ,  F23N5/242

Abstract: A gas turbine engine combustion system includes a plurality of fuel injectors circumferentially disposed around a combustor in a one to one fuel supply relationship with a plurality of fuel nozzle valves, and an electronic controller for controlling the fuel nozzle valves to eliminate and/or reduce hot streaking in response to sensed hot streak conditions. The fuel nozzle valves may be modulating valves. The electronic controller may be used to individually control the fuel nozzle valves. The hot streak conditions may be sensed with temperature sensors such as temperature sensors operably mounted in the combustor. A program in the electronic controller may be used for determining broken or malfunctioning sensors by calculating a combustor temperature and comparing it to measured temperatures from the sensors and comparing the measured fuel pressures in the individual fuel nozzle circuits with the simulated or calculated fuel pressures.

Abstract translation: 燃气涡轮发动机燃烧系统包括多个燃料喷射器，其周向地设置在与多个燃料喷嘴阀一对一燃料供给关系中的燃烧器周围;以及电子控制器，用于控制燃料喷嘴阀以消除和/或减少热量 响应于感测到的热条件条件。 燃料喷嘴阀可以是调节阀。 电子控制器可以用于单独地控制燃料喷嘴阀。 温度传感器可以感测热条纹条件，诸如可操作地安装在燃烧器中的温度传感器。 电子控制器中的程序可用于通过计算燃烧器温度并将其与来自传感器的测量温度进行比较并将各个燃料喷嘴回路中测量的燃料压力与模拟或计算的燃料压力进行比较来确定破坏或故障的传感器。

公开(公告)号：US07182576B2

公开(公告)日：2007-02-27

申请号：US10881506

申请日：2004-06-29

Applicant: Ronald Scott Bunker ,  Ching-Pang Lee

Inventor： Ronald Scott Bunker ,  Ching-Pang Lee

IPC: F01D5/18

CPC classification number: F28F13/12 ,  F01D5/187 ,  F05D2230/90 ,  F05D2250/28 ,  F05D2260/2212 ,  F05D2260/2214 ,  F05D2260/22141 ,  F28F3/022 ,  F28F3/044 ,  Y02T50/67 ,  Y02T50/671 ,  Y02T50/676 ,  Y10T29/4932

Abstract: A component includes at least one wall having an inner portion and an outer portion. A number of pins extend between the inner and outer portions. The pins define a mesh cooling arrangement with a number of flow channels. The inner portion of the wall defines a number of dimples. A method for forming a number of cooling holes in a component is described. The component has at least one wall with inner and outer portions. The inner portion defines a number of dimples. The method includes centering a drilling tool on a dimple, drilling at least one impingement cooling hole through the inner portion of the wall at the dimple using the drilling tool, and repeating the centering and drilling steps for a number of dimples to drill a number of impingement cooling holes in the inner portion of the wall.

Abstract translation: 一个部件包括至少一个具有内部部分和外部部分的壁。 多个销在内部和外部之间延伸。 销钉定义了具有多个流动通道的网状冷却装置。 壁的内部部分限定了多个凹坑。 描述了在部件中形成多个冷却孔的方法。 该部件具有至少一个具有内部和外部部分的壁。 内部部分限定了一些凹坑。 该方法包括将钻孔工具定中在凹坑上，使用钻孔工具在凹坑处穿过壁的内部部分的至少一个冲击冷却孔钻孔，并重复多个凹坑的定中心和钻孔步骤以钻出若干个 在壁的内部的冲击冷却孔。

公开(公告)号：US20070031240A1

公开(公告)日：2007-02-08

申请号：US11161500

申请日：2005-08-05

Applicant: Glenn Nichols ,  Kurt Brink ,  Ching-Pang Lee

Inventor： Glenn Nichols ,  Kurt Brink ,  Ching-Pang Lee

IPC: F03B11/00

CPC classification number: F01D9/04 ,  F01D5/288 ,  F01D11/08 ,  F01D11/24 ,  F01D25/12 ,  F01D25/246 ,  F05D2230/90 ,  F05D2240/11

Abstract: A cooled turbine shroud includes an arcuate flow path surface adapted to surround a row of rotating turbine blades, and an opposed interior surface; a forward overhang defining an axially-facing leading edge, an outwardly-extending forward wall and an outwardly-extending aft wall; opposed first and second sidewalls, wherein the forward and aft walls and the sidewalls define an open shroud plenum; at least one leading edge cooling hole extending from the shroud plenum to the leading edge; and at least one sidewall cooling hole extending from the plenum to one of the sidewalls. The flow path surface is free of cooling holes and may include a protective coating applied thereto.

Abstract translation: 冷却的涡轮机护罩包括适于围绕一排旋转涡轮叶片的弧形流动路径表面和相对的内表面; 向前突出部，其限定面向前的前缘，向外延伸的前壁和向外延伸的后壁; 相对的第一和第二侧壁，其中前壁和后壁以及侧壁限定开放的护罩增压室; 至少一个前缘冷却孔从护罩增压室延伸到前缘; 以及至少一个侧壁冷却孔，其从所述增压室延伸到所述侧壁之一。 流路表面没有冷却孔，并且可以包括施加到其上的保护涂层。