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21. 发明申请

US20120301306A1 HYBRID ROTOR DISK ASSEMBLY FOR A GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的混合转子盘组件
公开(公告)号：US20120301306A1
公开(公告)日：2012-11-29
申请号：US13116199
申请日：2011-05-26
申请人： Ioannis Alvanos , Gabriel L. Suciu , Christopher M. Dye , Glenn Levasseur
发明人： Ioannis Alvanos , Gabriel L. Suciu , Christopher M. Dye , Glenn Levasseur
IPC分类号： F01D5/30
CPC分类号： F01D5/3046 , F01D5/225 , F01D5/282 , F01D5/284 , F05D2300/6033
摘要： A rotor disk assembly for a gas turbine engine includes a rotor hub defined about an axis of rotation, the rotor hub includes a blade mount section with a first radial flange having a multiple of first apertures and a second radial flange with a multiple of second apertures.
摘要翻译：用于燃气涡轮发动机的转子盘组件包括围绕旋转轴限定的转子毂，转子毂包括具有第一径向凸缘的叶片安装部分，第一径向凸缘具有多个第一孔，第二径向凸缘具有多个第二孔。

22. 发明授权

US08851853B2 Hybrid rotor disk assembly for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的混合转子盘组件
公开(公告)号：US08851853B2
公开(公告)日：2014-10-07
申请号：US13116199
申请日：2011-05-26
申请人： Ioannis Alvanos , Gabriel L. Suciu , Christopher M. Dye , Glenn Levasseur
发明人： Ioannis Alvanos , Gabriel L. Suciu , Christopher M. Dye , Glenn Levasseur
IPC分类号： F01D5/32 , F01D5/28 , F01D5/30 , F01D5/22
CPC分类号： F01D5/3046 , F01D5/225 , F01D5/282 , F01D5/284 , F05D2300/6033
摘要： A rotor disk assembly for a gas turbine engine includes a rotor hub defined about an axis of rotation, the rotor hub includes a blade mount section with a first radial flange having a multiple of first apertures and a second radial flange with a multiple of second apertures.
摘要翻译：用于燃气涡轮发动机的转子盘组件包括围绕旋转轴限定的转子毂，转子毂包括具有第一径向凸缘的叶片安装部分，第一径向凸缘具有多个第一孔，第二径向凸缘具有多个第二孔。

23. 发明授权

US08834125B2 Hybrid rotor disk assembly with a ceramic matrix composite airfoil for a gas turbine engine 有权
标题翻译：具有用于燃气涡轮发动机的陶瓷基体复合翼型的混合转子盘组件
公开(公告)号：US08834125B2
公开(公告)日：2014-09-16
申请号：US13116188
申请日：2011-05-26
申请人： Ioannis Alvanos , Gabriel L. Suciu , Christopher M. Dye , Glenn Levasseur
发明人： Ioannis Alvanos , Gabriel L. Suciu , Christopher M. Dye , Glenn Levasseur
IPC分类号： F01D5/30 , F01D5/28 , F01D5/22 , C04B37/00
CPC分类号： F01D5/3046 , C04B37/00 , C04B2235/5244 , C04B2237/365 , C04B2237/38 , C04B2237/76 , F01D5/225 , F01D5/282 , F01D5/284 , F05D2240/12 , F05D2300/6033
摘要： A Ceramic Matrix Composite (CMC) airfoil for a gas turbine engine includes a CMC root section which extends to form a CMC airfoil section, the CMC root section defines a bore along a non-linear axis.
摘要翻译：用于燃气涡轮发动机的陶瓷基体复合材料（CMC）翼型件包括延伸以形成CMC翼型部分的CMC根部，CMC根部沿着非线性轴线限定孔。

24. 发明申请

US20120301303A1 HYBRID CERAMIC MATRIX COMPOSITE VANE STRUCTURES FOR A GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的混合陶瓷基体复合材料结构
公开(公告)号：US20120301303A1
公开(公告)日：2012-11-29
申请号：US13116144
申请日：2011-05-26
申请人： Ioannis Alvanos , Gabriel L. Suciu
发明人： Ioannis Alvanos , Gabriel L. Suciu
IPC分类号： F01D5/22 , B21K25/00
CPC分类号： F01D5/284 , C04B37/001 , C04B2237/38 , C04B2237/86 , F01D5/282 , F01D9/041 , F01D11/001 , F01D25/246 , F05D2300/6033 , Y10T29/49321 , Y10T29/49323
摘要： A vane structure for a gas turbine engine includes a multiple of CMC airfoil sections integrated between a CMC outer ring and a metal alloy inner ring.
摘要翻译：用于燃气涡轮发动机的叶片结构包括集成在CMC外环和金属合金内圈之间的多个CMC翼型部分。

25. 发明授权

US09334743B2 Ceramic matrix composite airfoil for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的陶瓷基复合翼型
公开(公告)号：US09334743B2
公开(公告)日：2016-05-10
申请号：US13116246
申请日：2011-05-26
申请人： Ioannis Alvanos , Gabriel L. Suciu , Douglas M. Berczik , John D. Riehl , Kevin L. Rugg
发明人： Ioannis Alvanos , Gabriel L. Suciu , Douglas M. Berczik , John D. Riehl , Kevin L. Rugg
IPC分类号： F01D5/28 , F01D9/04 , F01D5/34 , F01D11/00 , F01D25/24
CPC分类号： F01D5/284 , F01D5/282 , F01D5/34 , F01D9/041 , F01D11/001 , F01D25/246 , F05D2240/12 , F05D2300/6033
摘要： A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes a first multiple of CMC plies which define a suction side, a first airfoil portion of the first multiple of CMC plies at least partially parallel to an airfoil axis. A second multiple of CMC plies define a pressure side, a second airfoil portion of the second multiple of CMC plies at least partially parallel to the airfoil axis and bonded to the first airfoil portion.
摘要翻译：用于燃气涡轮发动机的陶瓷基体复合材料（CMC）翼型件包括限定吸力侧的CMC层的第一倍数，至少部分平行于翼型轴线的CMC层的第一倍数的第一翼型部分。 CMC层的第二倍数限定了压力侧，CMC层的第二倍数的第二翼型部分至少部分地平行于翼型轴线并结合到第一翼型部分。

26. 发明授权

US09091210B2 TEC mount redundant fastening 有权
标题翻译： TEC安装冗余紧固
公开(公告)号：US09091210B2
公开(公告)日：2015-07-28
申请号：US13456436
申请日：2012-04-26
申请人： Gabriel L. Suciu , Ioannis Alvanos
发明人： Gabriel L. Suciu , Ioannis Alvanos
IPC分类号： F01D25/28 , F02C7/20 , B64D27/26
CPC分类号： F02C7/20 , B64D27/26 , B64D2027/264
摘要： A mounting apparatus for a turbine exhaust case (TEC) is provided. The mounting apparatus may include a neck, support links and a plurality of fastening pins. The neck may include an upper portion that is receivable within a pylon associated with the TEC and at least one neck aperture extending therethrough. The support links may downwardly extend from a lower portion of the neck. The support links may be configured to at least partially receive a section of the TEC. Each support link may include at least one link aperture extending therethrough. The fastening pins may include at least one neck pin extending through the neck aperture and at least one link pin extending through the link aperture of each support link.
摘要翻译：提供了一种用于涡轮机排气箱（TEC）的安装装置。安装设备可以包括颈部，支撑连杆和多个紧固销。颈部可以包括可接收在与TEC相关联的挂架内的上部和延伸穿过其的至少一个颈孔。支撑连杆可以从颈部的下部向下延伸。支持链路可以被配置为至少部分地接收TEC的一部分。每个支撑连杆可以包括延伸穿过其中的至少一个连杆孔。紧固销可以包括延伸穿过颈部孔的至少一个颈销和延伸穿过每个支撑连杆的连杆孔的至少一个连杆销。

27. 发明授权

US09011085B2 Ceramic matrix composite continuous “I”-shaped fiber geometry airfoil for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的陶瓷基复合连续“I”形纤维几何翼型
公开(公告)号：US09011085B2
公开(公告)日：2015-04-21
申请号：US13116156
申请日：2011-05-26
申请人： Gabriel L. Suciu , Ioannis Alvanos
发明人： Gabriel L. Suciu , Ioannis Alvanos
IPC分类号： F01D9/04 , F01D25/24 , F01D5/28 , F01D11/00
CPC分类号： F01D25/246 , F01D5/282 , F01D5/284 , F01D9/041 , F01D11/008 , F05D2240/12 , F05D2300/6033 , Y10T29/49323 , Y10T29/49337
摘要： A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes at least one CMC ply which defines a suction side, an outer platform, a pressure side and an inner platform with a continuous “I”-shaped fiber geometry.
摘要翻译：用于燃气涡轮发动机的陶瓷基复合材料（CMC）翼型件包括至少一个CMC层，其限定吸力侧，外平台，压力侧和具有连续“I”形纤维几何形状的内平台。

28. 发明申请

US20130119617A1 TURBOMACHINERY SEAL 有权
标题翻译： TURBOMACHINERY密封
公开(公告)号：US20130119617A1
公开(公告)日：2013-05-16
申请号：US13294787
申请日：2011-11-11
申请人： Ioannis Alvanos , Gabriel L. Suciu
发明人： Ioannis Alvanos , Gabriel L. Suciu
IPC分类号： F16J15/02
CPC分类号： F01D11/001 , F01D11/122 , F01D11/127 , F05D2230/64 , F05D2250/184 , F05D2260/38
摘要： A seal for sealing a rotor of a rotary machine to a stator thereof which circumscribes the rotor and is separated therefrom by a gap comprises a nonrotational sealing element received within an annular slot in the stator and radially translatable with respect thereto, and extending into the gap for sealing to rotational sealing element carried by the rotor. A resilient biasing element received between the nonrotational sealing element and a floor of the slot biases the nonrotational sealing element radially inwardly toward the rotational sealing element and limits radially outward movement of the nonrotational sealing element. A guide extending into said gap from the slot engages the nonrotational sealing element to prevent axial misalignment thereof with the machine's rotor.
摘要翻译：用于将旋转机械的转子密封到其定子上的用于将转子环绕并通过间隙分离的密封件包括：非旋转密封元件，其接收在定子的环形槽内并且可相对于其径向平移并延伸到间隙用于密封转子承载的旋转密封元件。容纳在非旋转密封元件和狭槽的底板之间的弹性偏置元件将非旋转密封元件径向向内朝向旋转密封元件偏压并且限制非旋转密封元件的径向向外移动。从狭槽延伸到所述间隙中的引导件接合非旋转密封元件以防止其与机器转子的轴向不对准。

29. 发明申请

US20120301313A1 CERAMIC MATRIX COMPOSITE CONTINUOUS "I"-SHAPED FIBER GEOMETRY AIRFOIL FOR A GAS TURBINE ENGINE 有权
标题翻译：陶瓷基复合材料连续式“I”型用于气体涡轮发动机的光纤几何式
公开(公告)号：US20120301313A1
公开(公告)日：2012-11-29
申请号：US13116156
申请日：2011-05-26
申请人： Gabriel L. Suciu , Ioannis Alvanos
发明人： Gabriel L. Suciu , Ioannis Alvanos
IPC分类号： F01D5/14 , B65H81/00
CPC分类号： F01D25/246 , F01D5/282 , F01D5/284 , F01D9/041 , F01D11/008 , F05D2240/12 , F05D2300/6033 , Y10T29/49323 , Y10T29/49337
摘要： A Ceramic Matrix Composites (CMC) airfoil for a gas turbine engine includes at least one CMC ply which defines a suction side, an outer platform, a pressure side and an inner platform with a continuous “I”-shaped fiber geometry.
摘要翻译：用于燃气涡轮发动机的陶瓷基体复合材料（CMC）翼型件包括至少一个CMC层，其限定吸力侧，外平台，压力侧和具有连续I形纤维几何形状的内平台。

30. 发明申请

US20120301269A1 CLEARANCE CONTROL WITH CERAMIC MATRIX COMPOSITE ROTOR ASSEMBLY FOR A GAS TURBINE ENGINE 审中-公开
标题翻译：用于气体涡轮发动机的陶瓷基体复合材料转子组件的间隙控制
公开(公告)号：US20120301269A1
公开(公告)日：2012-11-29
申请号：US13116207
申请日：2011-05-26
申请人： Ioannis Alvanos , Gabriel L. Suciu
发明人： Ioannis Alvanos , Gabriel L. Suciu
IPC分类号： F01D25/24
摘要： A gas turbine engine includes a CMC static structure and a rotor module with a multiple of CMC airfoils, a radial growth of said rotor module matched with said CMC static structure.
摘要翻译：燃气涡轮发动机包括CMC静态结构和具有多个CMC翼型的转子模块，所述转子模块的径向生长与所述CMC静态结构匹配。

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