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41. 发明授权

US09435259B2 Gas turbine engine cooling system 有权
标题翻译：燃气轮机发动机冷却系统
公开(公告)号：US09435259B2
公开(公告)日：2016-09-06
申请号：US13405527
申请日：2012-02-27
申请人： Gabriel L. Suciu , Ioannis Alvanos
发明人： Gabriel L. Suciu , Ioannis Alvanos
IPC分类号： F02C6/08 , F01D5/08 , F02C7/08
CPC分类号： F02C6/08 , F01D5/08 , F02C7/08
摘要： A gas turbine engine includes a heat exchanger, a diffuser case, a passageway and a nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The diffuser case includes a plenum that receives the conditioned airflow. The passageway is fluidly connected between the heat exchanger and the diffuser case, and the conditioned airflow is communicated through the passageway and into the plenum. The nozzle assembly is in fluid communication with the plenum of the diffuser case to receive the conditioned airflow from the plenum.
摘要翻译：燃气涡轮发动机包括热交换器，扩散器壳体，通道和喷嘴组件。热交换器与放气气流交换热量以提供调节气流。扩散器壳体包括容纳调节气流的增压室。通道流体地连接在热交换器和扩散器壳体之间，并且经调节的气流通过通道连通并进入通风室。喷嘴组件与扩散器壳体的气室流体连通以接收来自气室的经调节的气流。

42. 发明授权

US09045990B2 Integrated ceramic matrix composite rotor disk geometry for a gas turbine engine 有权
标题翻译：用于燃气涡轮发动机的集成陶瓷基体复合转子盘几何形状
公开(公告)号：US09045990B2
公开(公告)日：2015-06-02
申请号：US13116102
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： F01D11/00 , F01D5/28 , F01D5/34 , F01D5/06
CPC分类号： F01D5/282 , F01D5/066 , F01D5/284 , F01D5/34 , F01D11/001 , F05D2300/6033
摘要： A CMC disk for a gas turbine engine includes a CMC hub defined about an axis and a multiple of CMC airfoils integrated with the CMC hub.
摘要翻译：用于燃气涡轮发动机的CMC盘包括围绕轴定义的CMC轮毂和与CMC集线器集成的CMC翼型的多个。

43. 发明授权

US09038398B2 Gas turbine engine buffer cooling system 有权
标题翻译：燃气轮机发动机缓冲冷却系统
公开(公告)号：US09038398B2
公开(公告)日：2015-05-26
申请号：US13405466
申请日：2012-02-27
申请人： Gabriel L. Suciu , Ioannis Alvanos
发明人： Gabriel L. Suciu , Ioannis Alvanos
IPC分类号： F02C6/08 , F01D5/08 , F02C7/06 , F02C7/18
CPC分类号： F02C7/185 , F01D5/081 , F01D25/125 , F02C6/08 , F02C7/06 , F05D2220/32 , F05D2260/232
摘要： A gas turbine engine includes a heat exchanger, a bearing compartment, and a nozzle assembly in fluid communication with the bearing compartment. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The bearing compartment is in fluid communication with the heat exchanger. A first passageway communicates the conditioned airflow from the heat exchanger to the bearing compartment. A second passageway communicates the conditioned airflow from the bearing compartment to the nozzle assembly.
摘要翻译：燃气涡轮发动机包括热交换器，轴承室和与轴承室流体连通的喷嘴组件。热交换器与放气气流交换热量以提供调节气流。轴承室与热交换器流体连通。第一通道将经调节的气流从热交换器传递到轴承室。第二通道将经调节的气流从轴承室传送到喷嘴组件。

44. 发明申请

US20130287565A1 TEC Mount Redundant Fastening 有权
标题翻译： TEC安装冗余紧固件
公开(公告)号：US20130287565A1
公开(公告)日：2013-10-31
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： F02C7/20
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。

45. 发明申请

US20130219920A1 GAS TURBINE ENGINE COOLING SYSTEM 有权
标题翻译：气体涡轮发动机冷却系统
公开(公告)号：US20130219920A1
公开(公告)日：2013-08-29
申请号：US13405527
申请日：2012-02-27
申请人： Gabriel L. Suciu , Ioannis Alvanos
发明人： Gabriel L. Suciu , Ioannis Alvanos
IPC分类号： F02C6/08
CPC分类号： F02C6/08 , F01D5/08 , F02C7/08
摘要： A gas turbine engine includes a heat exchanger, a diffuser case, a passageway and a nozzle assembly. The heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The diffuser case includes a plenum that receives the conditioned airflow. The passageway is fluidly connected between the heat exchanger and the diffuser case, and the conditioned airflow is communicated through the passageway and into the plenum. The nozzle assembly is in fluid communication with the plenum of the diffuser case to receive the conditioned airflow from the plenum.
摘要翻译：燃气涡轮发动机包括热交换器，扩散器壳体，通道和喷嘴组件。热交换器与放气气流交换热量以提供调节气流。扩散器壳体包括容纳调节气流的增压室。通道流体地连接在热交换器和扩散器壳体之间，并且经调节的气流通过通道连通并进入通风室。喷嘴组件与扩散器壳体的气室流体连通以接收来自气室的经调节的气流。

46. 发明申请

US20130004314A1 RADIAL SPLINE ARRANGEMENT FOR LPT VANE CLUSTERS 审中-公开
标题翻译： LPT VANE集群的径向安排
公开(公告)号：US20130004314A1
公开(公告)日：2013-01-03
申请号：US13172279
申请日：2011-06-29
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： F01D25/246 , Y10T29/49321
摘要： A full hoop stator vane cluster includes an inner hoop and an outer hoop both being substantially cylindrical and coaxial. A plurality of airfoils extend radially between the hoops, and a plurality of vane splines extend radially outward from the outer hoop for attaching the vane cluster to a gas turbine engine.
摘要翻译：一个完整的环形定子叶片组包括一个内圈和一个外圈，它们都是大致圆柱形和同轴的。多个翼型件在环之间径向延伸，并且多个叶片花键从外环径向向外延伸，用于将叶片簇附接到燃气涡轮发动机。

47. 发明申请

US20120301315A1 CERAMIC MATRIX COMPOSITE AIRFOIL FOR A GAS TURBINE ENGINE 有权
标题翻译：用于气体涡轮发动机的陶瓷基体复合气翼
公开(公告)号：US20120301315A1
公开(公告)日：2012-11-29
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： F01D5/14 , B29C43/02
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。

48. 发明授权

US08899924B2 Non-mechanically fastened TOBI heat shield 有权
标题翻译：非机械固定TOBI隔热罩
公开(公告)号：US08899924B2
公开(公告)日：2014-12-02
申请号：US13164234
申请日：2011-06-20
申请人： Ioannis Alvanos
发明人： Ioannis Alvanos
IPC分类号： F04D31/00 , F01D5/08 , F02C7/18
CPC分类号： F01D5/081 , F02C7/18 , F05D2260/30 , Y02T50/676 , Y10T29/49327
摘要： A high pressure turbine includes a stator, a rotor, a tangential on-board injector, and a heat shield. The rotor is located downstream of the stator and the tangential on-board injector directs cooling air to the rotor. The heat shield is retained by abutment with the stator and the tangential on-board injector.
摘要翻译：高压涡轮机包括定子，转子，切向的车载喷射器和隔热罩。转子位于定子的下游，切向的车载喷射器将冷却空气引导到转子。隔热板通过与定子和切向机载喷射器的邻接保持。

49. 发明授权

US07708520B2 Gas turbine engine with concave pocket with knife edge seal 有权
标题翻译：带凹口的燃气轮机，带刀口密封
公开(公告)号：US07708520B2
公开(公告)日：2010-05-04
申请号：US11605678
申请日：2006-11-29
申请人： Roger E. Paolillo , Ioannis Alvanos , Cheng-Zhang Wang
发明人： Roger E. Paolillo , Ioannis Alvanos , Cheng-Zhang Wang
IPC分类号： F01D11/02
CPC分类号： F01D11/001 , F01D11/02 , F05D2250/712
摘要： A gas turbine engine is provided with turbine sealing structures including knife edge seals which extend at an angle relative to an axial center line of the engine. Each knife edge seal is associated with a concave pocket defined between a radially inner surface and a spaced radially outer surface. The concave pockets and their associated knife edge seals create a pair of vortices which prevent leakage into radially inner portions of the turbine section.
摘要翻译：燃气涡轮发动机设置有涡轮机密封结构，其包括相对于发动机的轴向中心线以一定角度延伸的刀刃密封件。每个刀刃密封件与限定在径向内表面和间隔开的径向外表面之间的凹槽相关联。凹口袋及其相关的刀刃密封件产生一对涡流，防止泄漏到涡轮部分的径向内部。

50. 发明申请

US20090257877A1 ASYMMETRICAL ROTOR BLADE FIR-TREE ATTACHMENT 有权
标题翻译：不对称转子叶片FIR-TREE附件
公开(公告)号：US20090257877A1
公开(公告)日：2009-10-15
申请号：US12103673
申请日：2008-04-15
申请人： Ioannis Alvanos , John J. OConnor
发明人： Ioannis Alvanos , John J. OConnor
IPC分类号： F01D5/02 , F01D5/30
CPC分类号： F01D5/3007
摘要： A rotor blade for a gas turbine engine includes an asymmetric attachment section received within a rotor disk rim with an asymmetric slot.
摘要翻译：用于燃气涡轮发动机的转子叶片包括容纳在具有不对称槽的转子盘形边缘内的非对称附接部分。

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