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1. 发明申请

US20050158174A1 Turbine blade attachment lightening holes 失效
标题翻译：涡轮叶片附件减光孔
公开(公告)号：US20050158174A1
公开(公告)日：2005-07-21
申请号：US10761766
申请日：2004-01-21
申请人： Tom Brooks , Richard Seleski , Thomas Churbuck , Thomas Brew
发明人： Tom Brooks , Richard Seleski , Thomas Churbuck , Thomas Brew
IPC分类号： F01D5/14 , F01D5/18 , B63H1/14
CPC分类号： F01D5/147 , F01D5/18
摘要： The present invention seeks to provide a turbine blade with increased creep capability for both uncooled and cooled turbine blades while generally maintaining operating stress levels at an interface region between the turbine blade and a turbine disk. A turbine blade is disclosed having an attachment, a neck, a platform, and an airfoil. Extending radially outward from the attachment, through the neck, and terminating radially inward of the platform is a plurality of first cavities. The turbine blade in accordance with the preferred embodiment of the present invention is cast from a high density nickel base alloy with high temperature capability and improved creep capability. A plurality of first cavities are placed in the attachment and neck region to reduce excess weight of the turbine blade due to the higher density, greater creep capable alloy. Reducing the weight of the blade in this region provides increased creep capability in the turbine blade airfoil while maintaining operating stress levels.
摘要翻译：本发明寻求提供一种涡轮叶片，其具有对未冷却和冷却的涡轮机叶片具有增加的蠕变能力，同时通常维持在涡轮机叶片和涡轮盘之间的界面区域处的操作应力水平。公开了一种具有附件，颈部，平台和翼型的涡轮叶片。从附件径向向外延伸穿过颈部并且从该平台的径向向内延伸的是多个第一腔。根据本发明的优选实施例的涡轮叶片由具有高温能力和改进的蠕变能力的高密度镍基合金铸造。多个第一腔被放置在附接和颈部区域中，以便由于较高的密度，较大的可蠕变的合金而减少涡轮叶片的重量。在该区域中减小叶片的重量在涡轮叶片翼型件中提供增加的蠕变能力，同时保持操作应力水平。

2. 发明授权

US06957948B2 Turbine blade attachment lightening holes 失效
公开(公告)号：US06957948B2
公开(公告)日：2005-10-25
申请号：US10761766
申请日：2004-01-21
申请人： Tom Brooks , Richard Seleski , Thomas Churbuck , Thomas E. Brew, Jr.
发明人： Tom Brooks , Richard Seleski , Thomas Churbuck , Thomas E. Brew, Jr.
IPC分类号： F01D5/14 , F01D5/18
CPC分类号： F01D5/147 , F01D5/18
摘要： The present invention seeks to provide a turbine blade with increased creep capability for both uncooled and cooled turbine blades while generally maintaining operating stress levels at an interface region between the turbine blade and a turbine disk. A turbine blade is disclosed having an attachment, a neck, a platform, and an airfoil. Extending radially outward from the attachment, through the neck, and terminating radially inward of the platform is a plurality of first cavities. The turbine blade in accordance with the preferred embodiment of the present invention is cast from a high density nickel base alloy with high temperature capability and improved creep capability. A plurality of first cavities are placed in the attachment and neck region to reduce excess weight of the turbine blade due to the higher density, greater creep capable alloy. Reducing the weight of the blade in this region provides increased creep capability in the turbine blade airfoil while maintaining operating stress levels.

3. 发明授权

US06824352B1 Vane enhanced trailing edge cooling design 有权
标题翻译：叶片增强后缘冷却设计
公开(公告)号：US06824352B1
公开(公告)日：2004-11-30
申请号：US10673311
申请日：2003-09-29
申请人： Robert P. Moore , Richard Seleski , Dale Lee Cox
发明人： Robert P. Moore , Richard Seleski , Dale Lee Cox
IPC分类号： F01D906
CPC分类号： F01D5/187 , F05D2260/2212 , F05D2260/22141
摘要： There is provided a gas turbine vane with an airfoil cooling circuit incorporating multiple generally radially extending rows of pedestals generally bisected by a plurality of axially extending ribs with the ribs containing a plurality of recessed cavities. The recessed cavities are positioned immediately adjacent pedestals located closest to the ribs such that a cavity passageway is formed to pass sufficient cooling air between the rib and pedestal to increase overall heat transfer and reduce pressure loss of the cooling fluid.
摘要翻译：提供了一种具有机翼冷却回路的燃气轮机叶片，叶片冷却回路包括多个通常径向延伸的一对基座，其大体上被多个轴向延伸的肋分开，其中肋包含多个凹腔。凹入的腔体紧邻邻近肋条的位置定位，使得形成空腔通道以在肋和基座之间通过足够的冷却空气，以增加总体传热并降低冷却流体的压力损失。

4. 发明申请

US20050191182A1 Turbine blade shroud cutter tip 有权
标题翻译：涡轮叶片护罩刀尖
公开(公告)号：US20050191182A1
公开(公告)日：2005-09-01
申请号：US10787558
申请日：2004-02-26
申请人： Richard Seleski
发明人： Richard Seleski
IPC分类号： B63H1/16 , F01D5/20 , F01D11/08
CPC分类号： F01D11/08 , F01D5/225 , F05B2240/33
摘要： A shroud for use with a turbine blade is disclosed wherein the shroud provides at least one knife edge with at least one tooth for cutting a groove in a compliant rub strip that minimizes wear on the knife edge. The tooth is positioned along the knife edge a distance substantially away from the ends of the knife edge such that the moment created by the tooth mass and its effect on shroud bending stress is significantly reduced, thereby resulting in increased turbine blade durability.
摘要翻译：公开了一种与涡轮机叶片一起使用的护罩，其中护罩提供至少一个刀刃与至少一个齿，用于在柔性摩擦带上切割凹槽，使刀刃上的磨损最小化。齿沿着刀刃定位成基本上远离刀刃的端部，使得由齿块产生的力矩及其对护罩弯曲应力的影响显着降低，从而导致涡轮叶片耐久性提高。

5. 发明授权

US07094032B2 Turbine blade shroud cutter tip 有权
标题翻译：涡轮叶片护罩切割刀头
公开(公告)号：US07094032B2
公开(公告)日：2006-08-22
申请号：US10787558
申请日：2004-02-26
申请人： Richard Seleski
发明人： Richard Seleski
IPC分类号： F01D11/12
CPC分类号： F01D11/08 , F01D5/225 , F05B2240/33
摘要： A shroud for use with a turbine blade is disclosed wherein the shroud provides at least one knife edge with at least one tooth for cutting a groove in a compliant rub strip that minimizes wear on the knife edge. The tooth is positioned along the knife edge inward of the ends of the knife edge and a distance from an airfoil stackline such that the moment created by the tooth mass and its effect on shroud bending stress is significantly reduced, thereby resulting in increased turbine blade durability.
摘要翻译：公开了一种与涡轮机叶片一起使用的护罩，其中护罩提供至少一个刀刃与至少一个齿，用于在柔性摩擦带上切割凹槽，使刀刃上的磨损最小化。齿沿刀刃位于刀刃端部的内侧，距离翼型叠层线一定距离，使牙齿质量产生的力矩及其对护罩弯曲应力的影响大大降低，从而提高涡轮叶片耐久性。

6. 发明授权

US06491498B1 Turbine blade pocket shroud 有权
标题翻译：涡轮叶片口袋护罩
公开(公告)号：US06491498B1
公开(公告)日：2002-12-10
申请号：US09971241
申请日：2001-10-04
申请人： Richard Seleski , Remo Chiurato
发明人： Richard Seleski , Remo Chiurato
IPC分类号： F01D522
CPC分类号： F01D5/187 , F01D5/147 , F01D5/225 , F05D2260/232 , F05D2260/2322
摘要： An improved gas turbine blade is disclosed that utilizes a blade tip shroud with tapered shroud pockets to remove excess weight from the shroud while not compromising shroud bending stresses. Excess shroud weight removed by the tapered pockets reduces overall blade pull while maintaining material necessary to increase shroud stiffness. The resulting rib created between the tapered pockets provides a surface, away from possible areas of stress concentration, for drilling radial cooling holes.
摘要翻译：公开了一种改进的燃气轮机叶片，其利用具有锥形护罩袋的叶片梢罩，以从护罩移除多余的重量，同时不损害护罩弯曲应力。通过锥形口袋去除过多的护罩重量会降低整体刀片拉力，同时保持增加护罩刚度所需的材料。在锥形凹坑之间产生的所得肋提供了远离可能的应力集中区域的表面，用于钻出径向冷却孔。

7. 发明授权

US4566059A Converter with lossless snubbing components 失效
标题翻译：转换器与无损缓冲组件
公开(公告)号：US4566059A
公开(公告)日：1986-01-21
申请号：US516146
申请日：1983-07-21
申请人： George C. Gallios , Derek Whitehead , Richard Seleski
发明人： George C. Gallios , Derek Whitehead , Richard Seleski
IPC分类号： H02M7/5387 , H02M3/335
CPC分类号： H02M7/5387 , Y02B70/1441
摘要： The inverter includes a DC to AC converter circuit including a plurality of transistors which are switched on and off to convert a DC signal into an AC signal. The converter circuit also includes diodes which are alternately forward and reverse biased during the operation of the converter circuit, the diode having a reverse recovery period whenever the diode is switched from a forward to a reverse biased condition during which the reverse resistance of the diode is substantially zero. An inductor is connected to the diode for limiting the current through the diode during the reverse recovery period such that shoot through currents which pass through both the diode and the inductor are limited to desired levels.
摘要翻译：逆变器包括DC至AC转换器电路，其包括多个晶体管，其被接通和关断以将DC信号转换成AC信号。转换器电路还包括在转换器电路的操作期间交替地正向和反向偏置的二极管，二极管每当二极管从正向转换到反向偏置状态时具有反向恢复周期，在二极管期间二极管的反向电阻为基本为零。电感器连接到二极管，用于限制在反向恢复周期期间通过二极管的电流，使得通过二极管和电感器的穿通电流被限制到期望的电平。

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