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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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2.发明申请公开(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
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。
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3.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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4.发明申请INTEGRATED CERAMIC MATRIX COMPOSITE ROTOR MODULE FOR A GAS TURBINE ENGINE 审中-公开用于气体涡轮发动机的集成陶瓷基体复合转子模块公开(公告)号：US20120301275A1
公开(公告)日：2012-11-29
申请号：US13116129
申请日：2011-05-26
CPC分类号： F01D5/34 , C04B37/001 , C04B2237/38 , C04B2237/76 , C04B2237/84 , F01D5/282 , F01D5/284 , F01D11/001 , F05D2300/6033 , Y10T29/4932
摘要： A rotor module for a gas turbine engine includes a multiple of CMC airfoil rows which extend from a common CMC drum.
摘要翻译： 用于燃气涡轮发动机的转子模块包括从公共CMC鼓延伸的多个CMC翼型排。
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公开(公告)号：US08162605B2
公开(公告)日：2012-04-24
申请号：US12013617
申请日：2008-01-14
IPC分类号： F01D25/28
CPC分类号： F01D25/24 , F01D25/243 , F01D25/246 , F05D2230/60 , Y02T50/671 , Y10T29/49826
摘要： A case for a gas turbine engine includes a single-piece case that includes a combustor case portion and a turbine case portion that is integrally formed with the combustor case portion as one piece. In one example, the single-piece case includes a transition duct/mid-turbine frame case portion is integrally formed with the combustor and turbine case portions.
摘要翻译： 燃气涡轮发动机的壳体包括单件壳体，其包括燃烧器壳体部分和与燃烧器壳体部分一体形成为一体的涡轮壳体部分。 在一个示例中，单件式壳体包括过渡管道/中涡轮机壳体部分，其与燃烧器和涡轮机壳体部分整体形成。
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公开(公告)号：US09334743B2
公开(公告)日：2016-05-10
申请号：US13116246
申请日：2011-05-26
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。
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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
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。
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8.发明授权Ceramic matrix composite continuous “I”-shaped fiber geometry airfoil for a gas turbine engine 有权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
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。
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公开(公告)号：US20130232768A1
公开(公告)日：2013-09-12
申请号：US13417615
申请日：2012-03-12
IPC分类号： B23P17/04
CPC分类号： F02C7/20 , B64D27/10 , B64D27/26 , B64D2027/262 , B64D2027/266 , F05D2220/323 , F05D2230/60 , F05D2240/90 , Y02T50/44 , Y10T29/49947
摘要： A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.
摘要翻译： 一种用于安装具有压缩机部分，燃烧器部分，涡轮机部分，塔架和后部安装支架的燃气涡轮发动机的方法，包括将安装支架定位在燃气涡轮发动机和塔架之间。 安装支架连接到涡轮机壳体，使至少垂直载荷，侧向载荷，推力载荷和来自燃气涡轮发动机的转矩载荷通过安装支架反应。 安装支架连接到塔架，使来自燃气涡轮发动机的相同负载反应。
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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。
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