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公开(公告)号：US08784062B2
公开(公告)日：2014-07-22
申请号：US13283710
申请日：2011-10-28
CPC分类号： F01D5/02 , F01D5/022 , F01D5/025 , F01D5/027 , F01D5/066 , F01D5/14 , F01D5/147 , F01D11/006 , F05D2240/20 , F05D2260/15 , Y10T29/49316 , Y10T29/4932
摘要： A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface.
摘要翻译： 用于燃气涡轮发动机的间隔件包括沿着旋转轴线限定的转子环，转子环限定限定第一厚度的前周向凸缘和限定第二厚度的后周向凸缘，第一厚度不同于第二厚度 。 多个核心气体路径密封件，其从转子环延伸，与斜坡界面相对。
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公开(公告)号：US08961132B2
公开(公告)日：2015-02-24
申请号：US13459474
申请日：2012-04-30
申请人： Gabriel L. Suciu , Christopher M. Dye , William K. Ackermann , Stephen P. Muron , Ioannis Alvanos , Brian D. Merry , Arthur M. Salve , James W. Norris
发明人： Gabriel L. Suciu , Christopher M. Dye , William K. Ackermann , Stephen P. Muron , Ioannis Alvanos , Brian D. Merry , Arthur M. Salve , James W. Norris
CPC分类号： F01D11/006 , F01D5/066
摘要： A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk and at least one spacer adjacent to the plurality of blades. A flow passage is defined between the rotor disk and the blades and spacer. A plurality of inlets are formed within the spacer to pump air into the flow passage.
摘要翻译： 用于燃气涡轮发动机的转子包括从转子盘和与多个叶片相邻的至少一个间隔件延伸的多个叶片。 流动通道限定在转子盘和叶片和间隔件之间。 在间隔件内形成多个入口以将空气泵送到流动通道中。
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公开(公告)号：US09938831B2
公开(公告)日：2018-04-10
申请号：US13283689
申请日：2011-10-28
申请人： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve , James W. Norris
发明人： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve , James W. Norris
摘要： A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, each of the plurality of blades extend from the rotor disk at an interface, the interface defined along a spoke.
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公开(公告)号：US20130108466A1
公开(公告)日：2013-05-02
申请号：US13283710
申请日：2011-10-28
CPC分类号： F01D5/02 , F01D5/022 , F01D5/025 , F01D5/027 , F01D5/066 , F01D5/14 , F01D5/147 , F01D11/006 , F05D2240/20 , F05D2260/15 , Y10T29/49316 , Y10T29/4932
摘要： A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface.
摘要翻译： 用于燃气涡轮发动机的间隔件包括沿着旋转轴线限定的转子环，转子环限定限定第一厚度的前周向凸缘和限定第二厚度的后周向凸缘，第一厚度不同于第二厚度 。 多个核心气体路径密封件，其从转子环延伸，与斜坡界面相对。
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公开(公告)号：US20130108445A1
公开(公告)日：2013-05-02
申请号：US13283689
申请日：2011-10-28
申请人： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve , James W. Norris
发明人： Gabriel L. Suciu , Stephen P. Muron , Ioannis Alvanos , Christopher M. Dye , Brian D. Merry , Arthur M. Salve , James W. Norris
摘要： A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk, each of the plurality of blades extend from the rotor disk at an interface, the interface defined along a spoke.
摘要翻译： 用于燃气涡轮发动机的转子包括从转子盘延伸的多个叶片，所述多个叶片中的每一个叶片在接合处从转子盘延伸，所述界面沿辐条限定。
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公开(公告)号：US20130108413A1
公开(公告)日：2013-05-02
申请号：US13459474
申请日：2012-04-30
申请人： Gabriel L. Suciu , Christopher M. Dye , William K. Ackermann , Stephen P. Muron , loannis Alvanos , Brian D. Merry , Arthur M. Salve , James W. Norris
发明人： Gabriel L. Suciu , Christopher M. Dye , William K. Ackermann , Stephen P. Muron , loannis Alvanos , Brian D. Merry , Arthur M. Salve , James W. Norris
IPC分类号： F01D5/08
CPC分类号： F01D11/006 , F01D5/066
摘要： A rotor for a gas turbine engine includes a plurality of blades which extend from a rotor disk and at least one spacer adjacent to the plurality of blades. A flow passage is defined between the rotor disk and the blades and spacer. A plurality of inlets are formed within the spacer to pump air into the flow passage.
摘要翻译： 用于燃气涡轮发动机的转子包括从转子盘和与多个叶片相邻的至少一个间隔件延伸的多个叶片。 流动通道限定在转子盘和叶片和间隔件之间。 在间隔件内形成多个入口以将空气泵送到流动通道中。
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7.发明申请CERAMIC MATRIX COMPOSITE VANE STRUCTURES FOR A GAS TURBINE ENGINE TURBINE 有权用于气体涡轮发动机涡轮机的陶瓷基体复合材料结构公开(公告)号：US20120301285A1
公开(公告)日：2012-11-29
申请号：US13116053
申请日：2011-05-26
IPC分类号： F01D9/04
CPC分类号： F01D5/284 , F01D5/147 , F01D5/282 , F01D9/041 , F01D11/001 , F01D25/246 , F05D2240/12 , F05D2300/6033
摘要： A vane structure for a gas turbine engine according includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a CMC inner ring.
摘要翻译： 一种用于燃气涡轮发动机的叶片结构，其包括集成在CMC外环和CMC内环之间的多个CMC翼型部分。
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8.发明授权Integrated ceramic matrix composite rotor disk hub geometry for a gas turbine engine 有权用于燃气轮机的集成陶瓷基体复合转子盘毂几何形状公开(公告)号：US08944770B2
公开(公告)日：2015-02-03
申请号：US13116076
申请日：2011-05-26
摘要： A rotor disk for a gas turbine engine includes a CMC hub and a rail integrated with the CMC hub opposite the multiple of CMC airfoils, the rail defines a rail platform section that tapers to a rail inner bore.
摘要翻译： 用于燃气涡轮发动机的转子盘包括CMC轮毂和与CMC轮毂相对的多个CMC翼型件集成的轨道，轨道限定了轨道平台部分，该轨道平台部分向轨道内孔逐渐变细。
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9.发明申请INTEGRATED CERAMIC MATRIX COMPOSITE ROTOR DISK HUB GEOMETRY FOR A GAS TURBINE ENGINE 有权集成陶瓷基复合材料转子盘式汽油发动机几何公开(公告)号：US20120301305A1
公开(公告)日：2012-11-29
申请号：US13116076
申请日：2011-05-26
IPC分类号： F01D5/30
摘要： A rotor disk for a gas turbine engine includes a CMC hub and a rail integrated with the CMC hub opposite the multiple of CMC airfoils, the rail defines a rail platform section that tapers to a rail inner bore.
摘要翻译： 用于燃气涡轮发动机的转子盘包括CMC轮毂和与CMC轮毂相对的多个CMC翼型件集成的轨道，轨道限定了轨道平台部分，该轨道平台部分向轨道内孔逐渐变细。
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10.发明授权Ceramic matrix composite vane structures for a gas turbine engine turbine 有权用于燃气涡轮发动机涡轮机的陶瓷基体复合叶片结构公开(公告)号：US08905711B2
公开(公告)日：2014-12-09
申请号：US13116053
申请日：2011-05-26
CPC分类号： F01D5/284 , F01D5/147 , F01D5/282 , F01D9/041 , F01D11/001 , F01D25/246 , F05D2240/12 , F05D2300/6033
摘要： A vane structure for a gas turbine engine according includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a CMC inner ring.
摘要翻译： 一种用于燃气涡轮发动机的叶片结构，其包括集成在CMC外环和CMC内环之间的多个CMC翼型部分。
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