公开(公告)号：US07410610B2

公开(公告)日：2008-08-12

申请号：US10987887

申请日：2004-11-12

申请人： Andrew Philip Woodfield ,  Eric Allen Ott ,  Clifford Earl Shamblen ,  Michael Francis Xavier Gigliotti ,  David Alan Utah ,  Alan Glen Turner

发明人： Andrew Philip Woodfield ,  Eric Allen Ott ,  Clifford Earl Shamblen ,  Michael Francis Xavier Gigliotti ,  David Alan Utah ,  Alan Glen Turner

IPC分类号： B22F3/00 ,  B22F9/18

CPC分类号： F01D5/28 ,  B22F9/20 ,  B22F9/28 ,  C22C1/1031 ,  F04D29/023 ,  F05D2300/133 ,  F05D2300/174 ,  F05D2300/30 ,  F05D2300/502 ,  Y02T50/672

摘要： An article made of constituent elements is prepared by furnishing at least one nonmetallic precursor compound, wherein all of the nonmetallic precursor compounds collectively contain the constituent elements. The constituent elements include a titanium-base metallic composition, boron present at a level greater than its room-temperature solid solubility limit, and, optionally, a stable-oxide-forming additive element present at a level greater than its room-temperature solid solubility limit. The precursor compounds are chemically reduced to produce a material comprising a titanium-base metallic composition having titanium boride particles therein, without melting the titanium-base metallic composition. The titanium-base metallic composition having the titanium boride particles therein is consolidated without melting.

摘要翻译： 通过提供至少一种非金属前体化合物制备由构成元素制成的制品，其中所有非金属前体化合物共同含有构成元素。 组成元素包括钛基金属组合物，以大于其室温固溶度极限的水平存在的硼，以及任选地，以大于其室温固溶度的水平存在的稳定氧化物形成添加元素 限制。 前体化合物被化学还原以产生包含其中具有钛硼化物颗粒的钛基金属组合物，而不熔化钛基金属组合物的材料。 其中具有硼化钛颗粒的钛基金属组合物被固化而不熔化。

公开(公告)号：US07842231B2

公开(公告)日：2010-11-30

申请号：US12105800

申请日：2008-04-18

申请人： Andrew Philip Woodfield ,  Eric Allen Ott ,  Clifford Earl Shamblen ,  Michael Francis Gigliotti ,  David Alan Utah ,  Alan Glen Turner

发明人： Andrew Philip Woodfield ,  Eric Allen Ott ,  Clifford Earl Shamblen ,  Michael Francis Gigliotti ,  David Alan Utah ,  Alan Glen Turner

IPC分类号： B22F3/00 ,  B22F9/18

CPC分类号： F01D5/28 ,  B22F9/20 ,  B22F9/28 ,  C22C1/1031 ,  F04D29/023 ,  F05D2300/133 ,  F05D2300/174 ,  F05D2300/30 ,  F05D2300/502 ,  Y02T50/672

摘要： An article made of constituent elements is prepared by furnishing at least one nonmetallic precursor compound, wherein all of the nonmetallic precursor compounds collectively contain the constituent elements. The constituent elements include a titanium-base metallic composition, boron present at a level greater than its room-temperature solid solubility limit, and, optionally, a stable-oxide-forming additive element present at a level greater than its room-temperature solid solubility limit. The precursor compounds are chemically reduced to produce a material comprising a titanium-base metallic composition having titanium boride particles therein, without melting the titanium-base metallic composition. The titanium-base metallic composition having the titanium boride particles therein is consolidated without melting.

摘要翻译： 通过提供至少一种非金属前体化合物制备由构成元素制成的制品，其中所有非金属前体化合物共同含有构成元素。 组成元素包括钛基金属组合物，以大于其室温固溶度极限的水平存在的硼，以及任选地，以大于其室温固溶度的水平存在的稳定氧化物形成添加元素 限制。 前体化合物被化学还原以产生包含其中具有钛硼化物颗粒的钛基金属组合物，而不熔化钛基金属组合物的材料。 其中具有硼化钛颗粒的钛基金属组合物被固化而不熔化。

公开(公告)号：US20100180572A1

公开(公告)日：2010-07-22

申请号：US11496676

申请日：2006-07-31

申请人： Aspi Rustom Wadia ,  Alan Glen Turner ,  Aaron Michael Dziech ,  Peter Nicholas Szucs ,  John Jared Decker

发明人： Aspi Rustom Wadia ,  Alan Glen Turner ,  Aaron Michael Dziech ,  Peter Nicholas Szucs ,  John Jared Decker

IPC分类号： F02K3/072 ,  F02C3/00

CPC分类号： F01D5/022 ,  F02K3/072 ,  F02K3/077 ,  Y02T50/671 ,  Y02T50/673

摘要： A FLADE fan assembly includes radially inner and outer airfoils extending radially inwardly and outwardly respectively from an annular shroud circumferentially disposed about a centerline. Inner and outer chords extend between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively. Inner and outer stagger angles between the inner and outer chords respectively at the shroud and the centerline are different. The radially outer airfoils may outnumber the radially inner airfoils and particularly by a ratio in a range of 1.5:1 to about 4:1. Load paths or radii may extend radially through the inner and outer airfoils and through the rotating shroud between the inner and outer airfoils and may pass near or through the inner and outer leading edges and through the inner and outer trailing edges.

摘要翻译： FLADE风扇组件包括分别从围绕中心线周向设置的环形护罩径向向内和向外延伸的径向内部和外部翼型件。 内部和外部弦杆分别在径向内部和外部翼型的内部和外部翼型截面的内部和外部前缘和后缘之间延伸。 分别在护罩和中心线处的内外弦之间的内外交角是不同的。 径向外部翼型件可以超过径向内部翼型件，特别是在1.5:1至约4:1的范围内的比例。 载荷路径或半径可以径向延伸穿过内部和外部翼型件并且穿过内部和外部翼型之间的旋转护罩，并且可以通过内部和外部前缘附近或穿过内部和外部后缘。

公开(公告)号：US20140064955A1

公开(公告)日：2014-03-06

申请号：US13607147

申请日：2012-09-07

申请人： Thurmond Douglas Senter ,  Mark Joseph Mielke ,  Alan Glen Turner ,  Thomas Becker

发明人： Thurmond Douglas Senter ,  Mark Joseph Mielke ,  Alan Glen Turner ,  Thomas Becker

IPC分类号： F01D9/04

CPC分类号： F01D9/04 ,  F01D9/042 ,  F01D17/162 ,  F02K3/077 ,  Y02T50/673

摘要： A guide vane assembly for a gas turbine engine includes: a strut having: a root, a tip, a leading edge, a trailing edge wall, and opposed sidewalls extending between the leading edge and the trailing edge wall; and a pair of spaced-apart prongs extending axially aft from the trailing edge wall, each prong having an outer wall that is flush with a respective one of the sidewalls; and a flap positioned axially aft of the strut, the flap having a root, a tip, a leading edge, a trailing edge, and opposed sides extending between the leading and trailing edge, wherein a portion of the leading edge is disposed between the prongs, and wherein a disk-like flap button is disposed at the tip of the flap adjacent its leading edge, the flap button including a pair of spaced-apart notches formed therein.

摘要翻译： 用于燃气涡轮发动机的导叶组件包括：支柱，其具有：根部，尖端，前缘，后缘壁和在前缘和后缘壁之间延伸的相对的侧壁; 以及一对从后缘壁轴向延伸的间隔开的叉，每个叉具有与相应一个侧壁齐平的外壁; 以及位于所述支柱的轴向后方的翼片，所述翼片具有根部，尖端，前缘，后缘和在所述前缘和所述后缘之间延伸的相对侧，其中所述前缘的一部分设置在所述插脚之间 并且其中盘形折片按钮设置在靠近其前缘的翼片的尖端处，所述翼片按钮包括在其中形成的一对间隔开的凹口。

公开(公告)号：US07758311B2

公开(公告)日：2010-07-20

申请号：US11548745

申请日：2006-10-12

申请人： Kenneth Loehle ,  James A. Huffman ,  Charles K. Christopherson ,  Alan Glen Turner ,  Jeffrey F. Wessels ,  Gary Edward Trewiler ,  Peter J. Rock ,  Paul S. Manicke ,  Joseph Capozzi ,  Jeffrey Howard Nussbaum ,  Leslie M Pommer

发明人： Kenneth Loehle ,  James A. Huffman ,  Charles K. Christopherson ,  Alan Glen Turner ,  Jeffrey F. Wessels ,  Gary Edward Trewiler ,  Peter J. Rock ,  Paul S. Manicke ,  Joseph Capozzi ,  Jeffrey Howard Nussbaum ,  Leslie M Pommer

IPC分类号： F01D5/22

CPC分类号： F01D5/22 ,  F01D5/34 ,  F04D29/321 ,  F05B2230/239 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2230/232 ,  Y02T50/672 ,  Y02T50/673 ,  Y10S416/50

摘要： Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the plurality of airfoils and configured to attach to a corresponding airfoil of the plurality of airfoils and a plurality of wear surfaces, where at least one wear surface of the plurality of wear surfaces is configured and disposed to prevent excessive wear between the adjacent shroud segments. Each shroud segment of the plurality of shroud segments may be attached to a corresponding airfoil by weld connections to permit clearance during translation friction welding of the airfoil to the disk hub are located to avoid high stress areas.

摘要翻译： 包括盘，多个从圆盘径向向外延伸的周向间隔开的翼型件，多个护罩段，其周向设置在多个翼型件之间，并且构造成附接到多个翼型件的相应翼面和多个磨损表面 其中所述多个磨损表面中的至少一个磨损表面被构造和设置以防止相邻护罩段之间的过度磨损。 多个护罩段的每个护罩区段可以通过焊接连接件附接到相应的翼型件，以允许间隙在翼型平移期间摩擦焊接到盘毂以避免高应力区域。

公开(公告)号：US06619916B1

公开(公告)日：2003-09-16

申请号：US10086018

申请日：2002-02-28

申请人： Joseph Capozzi ,  Ruby Lasandra Zenon ,  Alan Glen Turner ,  Carol Vaczy Wallis ,  Peter Nicholas Szucs

发明人： Joseph Capozzi ,  Ruby Lasandra Zenon ,  Alan Glen Turner ,  Carol Vaczy Wallis ,  Peter Nicholas Szucs

IPC分类号： F01D1716

CPC分类号： F04D29/644 ,  F01D5/148 ,  F01D17/162 ,  F02C7/042 ,  F04D29/563 ,  Y10T29/49323

摘要： A method for assembling an articulated fan front frame for a gas turbine engine facilitates improving engine performance. The method includes forming a strut including a pair of sidewalls connected at a leading edge and a trailing edge, forming a flap including a first sidewall and a second sidewall connected at a leading edge and a trailing edge, and extending in radial span between a root endwall and a tip endwall, wherein each endwall extends between the first and second sidewalls, and wherein at least one of the root endwall and the tip endwall is contoured in a radial direction extending between the flap leading and trailing edges, and pivotally coupling the flap downstream from the strut such that a gap is defined between the flap and the strut.

摘要翻译： 用于组装用于燃气涡轮发动机的铰接式风扇前框架的方法有助于提高发动机性能。 该方法包括形成支柱，该支柱包括连接在前缘和后缘处的一对侧壁，形成包括第一侧壁和在前缘和后缘连接的第二侧壁的翼片，并且在径向跨度之间延伸 端壁和末端壁，其中每个端壁在第一和第二侧壁之间延伸，并且其中根端壁和尖端端壁中的至少一个沿着在翼片前缘和后缘之间延伸的径向方向成轮廓，并且枢转地联接翼片 在支柱的下游，使得在翼片和支柱之间限定间隙。

公开(公告)号：US07758303B1

公开(公告)日：2010-07-20

申请号：US11496676

申请日：2006-07-31

申请人： Aspi Rustom Wadia ,  Alan Glen Turner ,  Aaron Michael Dziech ,  Peter Nicholas Szucs ,  John Jared Decker

发明人： Aspi Rustom Wadia ,  Alan Glen Turner ,  Aaron Michael Dziech ,  Peter Nicholas Szucs ,  John Jared Decker

IPC分类号： F01D1/26

CPC分类号： F01D5/022 ,  F02K3/072 ,  F02K3/077 ,  Y02T50/671 ,  Y02T50/673

摘要： A FLADE fan assembly includes radially inner and outer airfoils extending radially inwardly and outwardly respectively from an annular shroud circumferentially disposed about a centerline. Inner and outer chords extend between inner and outer leading and trailing edges of inner and outer airfoil cross-sections of the radially inner and outer airfoils respectively. Inner and outer stagger angles between the inner and outer chords respectively at the shroud and the centerline are different. The radially outer airfoils may outnumber the radially inner airfoils and particularly by a ratio in a range of 1.5:1 to about 4:1. Load paths or radii may extend radially through the inner and outer airfoils and through the rotating shroud between the inner and outer airfoils and may pass near or through the inner and outer leading edges and through the inner and outer trailing edges.

摘要翻译： FLADE风扇组件包括分别从围绕中心线周向设置的环形护罩径向向内和向外延伸的径向内部和外部翼型件。 内部和外部弦杆分别在径向内部和外部翼型的内部和外部翼型截面的内部和外部前缘和后缘之间延伸。 分别在护罩和中心线处的内外弦之间的内外交角是不同的。 径向外部翼型件可以超过径向内部翼型件，特别是在1.5:1至约4:1的范围内的比例。 载荷路径或半径可以径向延伸穿过内部和外部翼型件并且穿过内部和外部翼型之间的旋转护罩，并且可以通过内部和外部前缘附近或穿过内部和外部后缘。

公开(公告)号：US20080089788A1

公开(公告)日：2008-04-17

申请号：US11548745

申请日：2006-10-12

申请人： Kenneth Loehle ,  James A. Huffman ,  Charles K. Christopherson ,  Alan Glen Turner ,  Jeffrey F. Wessels ,  Gary Edward Trewiler ,  Peter J, Rock ,  Paul S. Manicke ,  Joseph Capozzi ,  Jeffrey Howard Nussbaum ,  Leslie M. Pommer

发明人： Kenneth Loehle ,  James A. Huffman ,  Charles K. Christopherson ,  Alan Glen Turner ,  Jeffrey F. Wessels ,  Gary Edward Trewiler ,  Peter J, Rock ,  Paul S. Manicke ,  Joseph Capozzi ,  Jeffrey Howard Nussbaum ,  Leslie M. Pommer

IPC分类号： F01D5/22

CPC分类号： F01D5/22 ,  F01D5/34 ,  F04D29/321 ,  F05B2230/239 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2230/232 ,  Y02T50/672 ,  Y02T50/673 ,  Y10S416/50

摘要： Including a disk, a plurality of circumferentially spaced apart airfoils extending radially outwardly from the disk, a plurality of shroud segments being disposed circumferentially between the plurality of airfoils and configured to attach to a corresponding airfoil of the plurality of airfoils and a plurality of wear surfaces, where at least one wear surface of the plurality of wear surfaces is configured and disposed to prevent excessive wear between the adjacent shroud segments. Each shroud segment of the plurality of shroud segments may be attached to a corresponding airfoil by weld connections to permit clearance during translation friction welding of the airfoil to the disk hub are located to avoid high stress areas.

摘要翻译： 包括盘，多个从圆盘径向向外延伸的周向间隔开的翼型件，多个护罩段，其周向设置在多个翼型件之间，并且构造成附接到多个翼型件的相应翼面和多个磨损表面 其中所述多个磨损表面中的至少一个磨损表面被构造和设置以防止相邻护罩段之间的过度磨损。 多个护罩段的每个护罩区段可以通过焊接连接件附接到相应的翼型件，以允许间隙在翼型平移期间摩擦焊接到盘毂以避免高应力区域。