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公开(公告)号：US20090148271A1
公开(公告)日：2009-06-11
申请号：US12001130
申请日：2007-12-10
申请人： Ioannis Alvanos , Gabriel L. Suciu
发明人： Ioannis Alvanos , Gabriel L. Suciu
IPC分类号： F02C7/06
CPC分类号： F02C7/06 , F01D25/16 , F05D2220/321 , Y02T50/671
摘要： A bearing mounting system for use in a gas turbine engine having a low pressure turbine supported on a low pressure shaft through a support rotor comprises a low pressure turbine case, a forward bearing and an aft bearing, and a forward support structure and an aft support structure. The low pressure turbine case surrounds the low pressure turbine. The forward bearing and the aft bearing are positioned on the low pressure shaft to straddle the support rotor. The forward support structure and the aft support structure connect the forward bearing and the aft bearing, respectively, to the low pressure turbine case. The low pressure shaft extends axially between the forward bearing and the aft bearing. In one embodiment, the turbine comprises a plurality of adjacent rotor disks, and the support rotor comprises a conical support connecting one of the rotor disks with the shaft.
摘要翻译： 用于具有通过支撑转子支撑在低压轴上的低压涡轮机的燃气涡轮发动机的轴承安装系统包括低压涡轮壳体，前轴承和后轴承以及前支撑结构和后支撑件 结构体。 低压涡轮机壳体围绕低压涡轮机。 前轴承和后轴承定位在低压轴上以跨越支撑转子。 前支撑结构和后支撑结构分别将前轴承和后轴承分别连接到低压涡轮箱。 低压轴在前轴承和后轴承之间轴向延伸。 在一个实施例中，涡轮机包括多个相邻的转子盘，并且支撑转子包括将转子盘中的一个与轴连接的圆锥形支撑件。
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公开(公告)号：US07114339B2
公开(公告)日：2006-10-03
申请号：US10813520
申请日：2004-03-30
申请人： Ioannis Alvanos , Rajendra Agrawal , Hector M. Pinero , Jin Hu
发明人： Ioannis Alvanos , Rajendra Agrawal , Hector M. Pinero , Jin Hu
CPC分类号： F01D25/12 , F01D5/081 , F02C7/18 , F05D2240/81 , F05D2260/60 , F05D2260/6022 , Y02T50/676
摘要： A gas turbine engine having a turbine section cooling system is disclosed which is able to cool the turbine section of the gas turbine engine to an optimal operating temperature range, while at the same time not substantially degrading engine performance. The disclosure provides a number of different structures for doing so including the provision of turning foils, turning holes, and turning grooves within a secondary air flow cavity which turns or directs cooling and parasitic leakage air into the turbine section in a direction in substantial alignment with a gas flow path through the turbine section.
摘要翻译： 公开了一种具有涡轮部分冷却系统的燃气涡轮发动机，其能够将燃气涡轮发动机的涡轮部分冷却到最佳工作温度范围，同时基本上不降低发动机性能。 本公开提供了许多不同的结构，包括在二次空气流动空腔内提供转动箔，转动孔和转动槽，其将冷却和寄生的泄漏空气转向或引导到与涡轮部分基本对准的方向 通过涡轮机部分的气体流动路径。
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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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44.发明授权公开(公告)号：US09157325B2
公开(公告)日：2015-10-13
申请号：US13405502
申请日：2012-02-27
申请人： Gabriel L. Suciu , Ioannis Alvanos , Camelia Galos
发明人： Gabriel L. Suciu , Ioannis Alvanos , Camelia Galos
摘要： A gas turbine engine includes a buffer cooling system having a first heat exchanger, a first passageway, a second passageway and a third passageway. The first heat exchanger exchanges heat with a bleed airflow to provide a conditioned airflow. The first passageway communicates a first portion of the conditioned airflow to a high pressure compressor of the gas turbine engine, the second passageway communicates a second portion of the conditioned airflow to a high pressure turbine of the gas turbine engine, and the third passageway communicates a third portion of the conditioned airflow to a low pressure turbine of the gas turbine engine.
摘要翻译： 燃气涡轮发动机包括具有第一热交换器，第一通道，第二通道和第三通道的缓冲冷却系统。 第一热交换器与放气气流交换热量以提供调节气流。 第一通道将调节气流的第一部分与燃气涡轮发动机的高压压缩机连通，第二通道将调节气流的第二部分连通到燃气涡轮发动机的高压涡轮机，并且第三通道 调节气流的第三部分到燃气涡轮发动机的低压涡轮机。
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45.发明授权公开(公告)号：US08770931B2
公开(公告)日：2014-07-08
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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公开(公告)号：US08511986B2
公开(公告)日：2013-08-20
申请号：US12001130
申请日：2007-12-10
申请人： Ioannis Alvanos , Gabriel L. Suciu
发明人： Ioannis Alvanos , Gabriel L. Suciu
IPC分类号： F04D29/04
CPC分类号： F02C7/06 , F01D25/16 , F05D2220/321 , Y02T50/671
摘要： A bearing mounting system for use in a gas turbine engine having a low pressure turbine supported on a low pressure shaft through a support rotor comprises a low pressure turbine case, a forward bearing and an aft bearing, and a forward support structure and an aft support structure. The low pressure turbine case surrounds the low pressure turbine. The forward bearing and the aft bearing are positioned on the low pressure shaft to straddle the support rotor. The forward support structure and the aft support structure connect the forward bearing and the aft bearing, respectively, to the low pressure turbine case. The low pressure shaft extends axially between the forward bearing and the aft bearing. In one embodiment, the turbine comprises a plurality of adjacent rotor disks, and the support rotor comprises a conical support connecting one of the rotor disks with the shaft.
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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：US20130000324A1
公开(公告)日：2013-01-03
申请号：US13172316
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： F02C3/04
CPC分类号： F01D9/044 , F01D9/041 , F01D25/24 , F01D25/243 , F01D25/246 , F05D2230/53 , F05D2300/6033 , Y02T50/672
摘要： A gas turbine engine includes a compressor, a combustor section, and a turbine. The turbine includes an integrated case/stator segment that is comprised of a ceramic matrix composite material.
摘要翻译： 燃气涡轮发动机包括压缩机，燃烧器部分和涡轮机。 涡轮机包括由陶瓷基体复合材料组成的集成壳体/定子段。
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公开(公告)号：US20120321453A1
公开(公告)日：2012-12-20
申请号：US13164234
申请日：2011-06-20
申请人： Ioannis Alvanos
发明人： Ioannis Alvanos
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。
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