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公开(公告)号：US08944751B2
公开(公告)日：2015-02-03
申请号：US13345776
申请日：2012-01-09
Applicant: Aaron Gregory Winn , Robert Walter Coign , James Stewart Phillips , Thomas Robbins Tipton , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Niranjan Gokuldas Pai
Inventor： Aaron Gregory Winn , Robert Walter Coign , James Stewart Phillips , Thomas Robbins Tipton , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Niranjan Gokuldas Pai
CPC classification number: F01D11/001 , F05D2240/128 , F05D2260/201
Abstract: The present application provides an inner nozzle platform. The inner nozzle platform may include a platform cavity, an impingement plenum positioned within the platform cavity, a retention plate positioned on a first side of the impingement plenum, and a compliant seal positioned on a second side of the impingement plenum.
Abstract translation: 本申请提供了内喷嘴平台。 内部喷嘴平台可以包括平台空腔，位于平台空腔内的冲击气室，定位在冲击气室的第一侧上的保持板，以及定位在冲击气室的第二侧上的柔性密封件。
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公开(公告)号：US20080206063A1
公开(公告)日：2008-08-28
申请号：US11679468
申请日：2007-02-27
Applicant: Lynn Charles Gagne , Graham David Sherlock , Kelvin Aaron , Thomas Robbins Tipton
Inventor： Lynn Charles Gagne , Graham David Sherlock , Kelvin Aaron , Thomas Robbins Tipton
IPC: B64C11/16
CPC classification number: F01D9/042 , F05D2250/191
Abstract: A method for assembling a stator assembly for a turbine engine is provided. The method includes providing a blade with a base including an end wall having at least one hole defined therein and providing a shim having at least one aperture extending therethrough. The shim aperture is aligned with the end wall hole, and the shim is secured to the blade base end wall using a fastener. The fastener is inserted through the shim aperture in an interference fit within the end wall hole. The blade and the shim are coupled to a turbine casing.
Abstract translation: 提供一种用于组装用于涡轮发动机的定子组件的方法。 该方法包括提供具有底座的刀片，底座包括具有限定在其中的至少一个孔的端壁，并提供具有延伸穿过其中的至少一个孔的垫片。 垫片孔与端壁孔对齐，并且垫片使用紧固件固定到刀片底端壁上。 紧固件通过垫片孔以过盈配合插入端壁孔内。 叶片和垫片联接到涡轮机壳体。
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公开(公告)号：US07024744B2
公开(公告)日：2006-04-11
申请号：US10814221
申请日：2004-04-01
Applicant: Nicholas Francis Martin , Thomas Robbins Tipton
Inventor： Nicholas Francis Martin , Thomas Robbins Tipton
CPC classification number: F01D5/16 , F04D29/542 , F04D29/668 , F05D2230/10 , Y10T29/49325 , Y10T29/49336 , Y10T29/49716 , Y10T29/49774
Abstract: A method of tuning a compressor stator blade having a base portion and an airfoil portion to achieve a desired natural frequency, includes a) identifying the natural frequency of the compressor stator blade; b) determining a different target natural frequency for the compressor stator blade; and c) removing material from the base portion of the compressor stator blade in an amount and in a configuration that achieves the target natural frequency. A frequency-tuned compressor stator blade includes an airfoil portion and a base portion, the base portion having a substantially solid rectangular shape; and a groove cut across a width dimension of the base portion, the groove having dimensions selected to obtain a predetermined natural frequency for the airfoil portion.
Abstract translation: 一种调节具有基部和翼型部分的压缩机定子叶片以实现期望的固有频率的方法包括：a）识别压缩机定子叶片的固有频率; b）确定压缩机定子叶片的不同目标固有频率; 以及c）以达到目标固有频率的量和配置来从压缩机定子叶片的基部移除材料。 频率调节压缩机定子叶片包括翼型部分和基部部分，基部具有基本上实心的矩形形状; 以及在基部的宽度尺寸上切割的槽，所述槽的尺寸被选择以获得用于翼型部的预定固有频率。
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公开(公告)号：US20140030098A1
公开(公告)日：2014-01-30
申请号：US13556323
申请日：2012-07-24
Applicant: Michael James Dutka , John Duong , Ya-Tien Chiu , Alexander David Shrum , Kelvin Rono Aaron , Christopher Edward LaMaster , San-Dar Gau , Franco Monteleone , Paul Griffin Delvernois , Matthew John McKeever , Govindarajan Rengarajan , Jeremy Peter Latimer , Marc Edward Blohm , Eric Richard Bonini , Venkata Siva Prasad Chaluvadi , Jamie Dean Lumpkin , Thomas Robbins Tipton
Inventor： Michael James Dutka , John Duong , Ya-Tien Chiu , Alexander David Shrum , Kelvin Rono Aaron , Christopher Edward LaMaster , San-Dar Gau , Franco Monteleone , Paul Griffin Delvernois , Matthew John McKeever , Govindarajan Rengarajan , Jeremy Peter Latimer , Marc Edward Blohm , Eric Richard Bonini , Venkata Siva Prasad Chaluvadi , Jamie Dean Lumpkin , Thomas Robbins Tipton
CPC classification number: F01D5/3038 , F04D29/322 , F05D2250/74
Abstract: An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a. characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
Abstract translation: 制造品具有配置成与涡轮机一起使用的第一部件。 第一部件被配置为附接到第二部件，并且通过修改a来减少与不希望的第三部件的连接的可能性。 第一部分的特征。 该修改由第二组件的互补特性匹配。 第一部件具有基本上根据从由表1-11组成的组中选择的可缩放表格中阐述的X，Y和Z的笛卡尔坐标值的标称翼型分布。 X，Y和Z的笛卡尔坐标值是通过乘以数字可转换为尺寸距离的无量纲值。 X和Y是当通过连续弧连接时在每个Z高度处限定翼型轮廓部分的坐标。 每个Z高度处的翼型轮廓部分彼此连接以形成完整的翼型形状。
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5.发明申请公开(公告)号：US20090007995A1
公开(公告)日：2009-01-08
申请号：US12235054
申请日：2008-09-22
Applicant: Mark Roger Brown , Thomas Robbins Tipton , Liming Xu
Inventor： Mark Roger Brown , Thomas Robbins Tipton , Liming Xu
IPC: C21D1/26
Abstract: A method by which high temperature properties of a ductile iron alloy, including creep and LCF properties, can be increased for pressure-containing components that are subject to creep and low cycle fatigue. The method comprises modifying the ductile iron alloy to contain 0.4 to 0.8 weight percent molybdenum. A casting of the modified ductile iron alloy is produced and then annealed at a temperature of at least 725° C. for not less than five hours to eliminate carbides and/or stabilize pearlite in the casting. The annealed casting of the modified ductile iron alloy exhibits improved creep resistance and low cycle fatigue properties in comparison to an identical casting of a ductile iron alloy that does not contain molybdenum.
Abstract translation: 对于承受蠕变和低循环疲劳的含压组分，可以增加包括蠕变和LCF性能的球墨铸铁合金的高温性能的方法。 该方法包括改性球墨铸铁合金以含有0.4-0.8重量％的钼。 制造改性球墨铸铁合金的铸件，然后在至少725℃的温度下退火不少于5小时以消除铸件中的碳化物和/或稳定珠光体。 与不含钼的球墨铸铁合金的相同铸造相比，改性球墨铸铁合金的退火铸造表现出改善的抗蠕变性和低循环疲劳性能。
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Patent Agency Ranking
公开(公告)号：US20130230407A1
公开(公告)日：2013-09-05
申请号：US13409355
申请日：2012-03-01
Applicant: Bradley Taylor Boyer , Thomas Robbins Tipton
Inventor： Bradley Taylor Boyer , Thomas Robbins Tipton
IPC: F01D5/18
CPC classification number: F01D5/186 , F05D2250/185 , F05D2250/71
Abstract: The present application thus provides a turbine bucket. The turbine bucket may include a platform, an airfoil extending from the platform at an intersection thereof, and a core cavity extending within the platform and the airfoil. The core cavity may include a contoured turn about the intersection so as to reduce thermal stress therein.
Abstract translation: 因此，本申请提供了一种涡轮机桶。 涡轮机桶可以包括平台，在平台的相交处从平台延伸的翼型件和在平台和翼型件内延伸的芯空腔。 芯腔可以包括围绕交点的轮廓转弯，以便减少其中的热应力。
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公开(公告)号：US20130175357A1
公开(公告)日：2013-07-11
申请号：US13345776
申请日：2012-01-09
Applicant: Aaron Gregory Winn , Robert Walter Coign , James S. Phillips , Thomas Robbins Tipton , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Niranjan Gokuldas Pai
Inventor： Aaron Gregory Winn , Robert Walter Coign , James S. Phillips , Thomas Robbins Tipton , Gregory Thomas Foster , Ravichandran Meenakshisundaram , Niranjan Gokuldas Pai
CPC classification number: F01D11/001 , F05D2240/128 , F05D2260/201
Abstract: The present application provides an inner nozzle platform. The inner nozzle platform may include a platform cavity, an impingement plenum positioned within the platform cavity, a retention plate positioned on a first side of the impingement plenum, and a compliant seal positioned on a second side of the impingement plenum.
Abstract translation: 本申请提供了内喷嘴平台。 内部喷嘴平台可以包括平台空腔，位于平台空腔内的冲击气室，定位在冲击气室的第一侧上的保持板，以及定位在冲击气室的第二侧上的柔性密封件。
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公开(公告)号：US09145777B2
公开(公告)日：2015-09-29
申请号：US13556323
申请日：2012-07-24
Applicant: Michael James Dutka , John Duong , Ya-Tien Chiu , Alexander David Shrum , Kelvin Rono Aaron , Christopher Edward LaMaster , San-Dar Gau , Franco Monteleone , Paul Griffin Delvernois , Matthew John McKeever , Govindarajan Rengarajan , Jeremy Peter Latimer , Marc Edward Blohm , Eric Richard Bonini , Venkata Siva Prasad Chaluvadi , Jamie Dean Lumpkin , Thomas Robbins Tipton
Inventor： Michael James Dutka , John Duong , Ya-Tien Chiu , Alexander David Shrum , Kelvin Rono Aaron , Christopher Edward LaMaster , San-Dar Gau , Franco Monteleone , Paul Griffin Delvernois , Matthew John McKeever , Govindarajan Rengarajan , Jeremy Peter Latimer , Marc Edward Blohm , Eric Richard Bonini , Venkata Siva Prasad Chaluvadi , Jamie Dean Lumpkin , Thomas Robbins Tipton
CPC classification number: F01D5/3038 , F04D29/322 , F05D2250/74
Abstract: An article of manufacture has a first component configured for use with a turbomachine. The first component is configured for attachment to a second component, and reduces the possibility of attachment with an undesired third component by modification of a characteristic of the first component. This modification is matched by a complementary characteristic of the second component. The first component has a nominal airfoil profile substantially in accordance with Cartesian coordinate values of X, Y and Z set forth in a scalable table selected from the group consisting of TABLES 1-11. Cartesian coordinate values of X, Y and Z are non-dimensional values convertible to dimensional distances by multiplying by a number. X and Y are coordinates which, when connected by continuing arcs, define airfoil profile sections at each Z height. The airfoil profile sections at each Z height being joined with one another to form a complete airfoil shape.
Abstract translation: 制造品具有配置成与涡轮机一起使用的第一部件。 第一部件被配置为附接到第二部件，并且通过修改第一部件的特性来减少与不需要的第三部件的连接的可能性。 该修改由第二组件的互补特性匹配。 第一部件具有基本上根据从由表1-11组成的组中选择的可缩放表格中阐述的X，Y和Z的笛卡尔坐标值的标称翼型分布。 X，Y和Z的笛卡尔坐标值是通过乘以数字可转换为尺寸距离的无量纲值。 X和Y是当通过连续弧连接时在每个Z高度处限定翼型轮廓部分的坐标。 每个Z高度处的翼型轮廓部分彼此连接以形成完整的翼型形状。
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公开(公告)号：US08974182B2
公开(公告)日：2015-03-10
申请号：US13409355
申请日：2012-03-01
Applicant: Bradley Taylor Boyer , Thomas Robbins Tipton
Inventor： Bradley Taylor Boyer , Thomas Robbins Tipton
IPC: F01D5/18
CPC classification number: F01D5/186 , F05D2250/185 , F05D2250/71
Abstract: The present application thus provides a turbine bucket. The turbine bucket may include a platform, an airfoil extending from the platform at an intersection thereof, and a core cavity extending within the platform and the airfoil. The core cavity may include a contoured turn about the intersection so as to reduce thermal stress therein.
Abstract translation: 因此，本申请提供了一种涡轮机桶。 涡轮机桶可以包括平台，在平台的相交处从平台延伸的翼型件和在平台和翼型件内延伸的芯空腔。 芯腔可以包括围绕交点的轮廓转弯，以便减少其中的热应力。
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10.发明授权Compressor blade platform extension and methods of retrofitting blades of different blade angles 有权压缩机叶片平台延伸和不同叶片角度改装叶片的方法公开(公告)号：US07104759B2
公开(公告)日：2006-09-12
申请号：US10814228
申请日：2004-04-01
Applicant: Thomas Robbins Tipton , Nicholas Francis Martin, Jr.
Inventor： Thomas Robbins Tipton , Nicholas Francis Martin, Jr.
IPC: F03B3/12
CPC classification number: F04D29/322 , F01D5/3007 , F01D25/002 , F05D2240/80
Abstract: Blades of increased blade angle may be retrofitted onto existing compressor rotor wheels as replacement blades whereby higher performance and efficiency without replacing the rotor wheel may be achieved. The base attachments of replacement blades are provided with lateral extensions or flanges and the rim of the compressor wheel is provided with recesses straddling the grooves to accommodate the flanges. The leading edge of the replacement blade is positioned circumferentially for support only by the platform extension thereby limiting the mean and vibratory stresses in the leading edge of the airfoil and maximizing damage tolerance.
Abstract translation: 叶片角度增加的叶片可以作为替换叶片改装到现有的压缩机转子轮上，从而可以实现不更换转子轮的更高的性能和效率。 替换叶片的基座附件设置有侧向延伸部或凸缘，并且压缩机叶轮的边缘设置有跨越凹槽的凹部以容纳凸缘。 替换刀片的前缘定位在圆周方向上，以便仅由平台延伸部支撑，从而限制翼型件前缘中的平均和振动应力并最大化损伤公差。
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