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公开(公告)号：US20130026338A1
公开(公告)日：2013-01-31
申请号：US13192716
申请日：2011-07-28
申请人： Lea Kennard Castle , Mario P. Bochiechio , Carl R. Verner , Steven J. Bullied , John Joseph Marcin , Kevin W. Chittenden , Hector M. Pinero , Agnes Klucha , Michael C. Reiter
发明人： Lea Kennard Castle , Mario P. Bochiechio , Carl R. Verner , Steven J. Bullied , John Joseph Marcin , Kevin W. Chittenden , Hector M. Pinero , Agnes Klucha , Michael C. Reiter
CPC分类号： B22C9/04 , B22C9/10 , B22F3/1055 , B22F3/115 , B33Y10/00 , B33Y80/00 , Y02P10/292 , Y02P10/295
摘要： A method of manufacturing a casting article for use in a casting process includes rapidly forming the casting article out of a metallic material. A ceramic coating is applied to an exterior surface of the casting article.
摘要翻译： 制造用于铸造工艺的铸造制品的方法包括从金属材料快速地形成铸造制品。 将陶瓷涂层施加到铸件的外表面。
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公开(公告)号：US20090238683A1
公开(公告)日：2009-09-24
申请号：US12079048
申请日：2008-03-24
申请人： Ioannis Alvanos , Hector M. Pinero
发明人： Ioannis Alvanos , Hector M. Pinero
CPC分类号： F01D11/001 , F01D11/122 , F05D2240/55 , F05D2250/283 , Y02T50/671
摘要： A stator vane segment for a gas turbine engine includes at least one airfoil joined to an outer shroud and an inner platform. A sealing element having a first platform radially inward of the inner platform and an abradable material covering at least a portion of the first platform is integrally joined to the inner platform.
摘要翻译： 用于燃气涡轮发动机的定子叶片段包括连接到外护罩和内平台的至少一个翼型件。 具有内平台径向内侧的第一平台和覆盖第一平台的至少一部分的可磨损材料的密封元件与内平台整体连接。
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公开(公告)号：US08434997B2
公开(公告)日：2013-05-07
申请号：US11843112
申请日：2007-08-22
IPC分类号： F03B11/02
CPC分类号： F01D11/24 , F01D25/14 , F01D25/26 , F05D2230/21 , Y02T50/671 , Y02T50/675
摘要： A gas turbine engine includes an active clearance control (ACC) system within the engine casing. The case includes a wall structure with a cast-in cooling configuration through Refractory Metal Core technology which is tailored to address traditional hot spots and improve discrete control of case growth.
摘要翻译： 燃气涡轮发动机包括发动机壳体内的主动间隙控制（ACC）系统。 该案例包括通过耐火金属核心技术具有铸造冷却配置的墙体结构，该技术专为解决传统热点而改进了病例生长的离散控制。
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公开(公告)号：US20090053041A1
公开(公告)日：2009-02-26
申请号：US11843112
申请日：2007-08-22
IPC分类号： F04D29/58
CPC分类号： F01D11/24 , F01D25/14 , F01D25/26 , F05D2230/21 , Y02T50/671 , Y02T50/675
摘要： A gas turbine engine includes an active clearance control (ACC) system within the engine casing. The case includes a wall structure with a cast-in cooling configuration through Refractory Metal Core technology which is tailored to address traditional hot spots and improve discrete control of case growth.
摘要翻译： 燃气涡轮发动机包括发动机壳体内的主动间隙控制（ACC）系统。 该案例包括通过耐火金属核心技术具有铸造冷却配置的墙体结构，该技术专为解决传统热点而改进了病例生长的离散控制。
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公开(公告)号：US09091173B2
公开(公告)日：2015-07-28
申请号：US13485579
申请日：2012-05-31
申请人： John H. Mosley , Ioannis Alvanos , Phililp S. Stripinis , Douglas Paul Freiberg , Hector M. Pinero , John J. O'Connor , Jon Pietrobon
发明人： John H. Mosley , Ioannis Alvanos , Phililp S. Stripinis , Douglas Paul Freiberg , Hector M. Pinero , John J. O'Connor , Jon Pietrobon
摘要： A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.
摘要翻译： 构造成围绕延伸穿过燃气涡轮发动机的中心的轴线在圆周方向上旋转的燃气涡轮发动机包括涡轮级。 涡轮级包括盘，多个叶片和小型盘。 盘包括具有槽的外径边缘，围绕轴线的内径孔，前表面和后表面。 多个叶片耦合到槽。 微型盘联接到转子的后表面以在其间限定冷却室，以便将冷却空气引导到狭槽。 在本发明的一个实施例中，冷却气室通过所有旋转部件连接到径向内部的压缩机排放空气入口，使得冷却空气抵靠内径孔。
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公开(公告)号：US20130323010A1
公开(公告)日：2013-12-05
申请号：US13485579
申请日：2012-05-31
申请人： John H. Mosley , Ioannis Alvanos , Phililp S. Stripinis , Douglas Paul Freiberg , Hector M. Pinero , John J. O'Connor , Jon Pietrobon
发明人： John H. Mosley , Ioannis Alvanos , Phililp S. Stripinis , Douglas Paul Freiberg , Hector M. Pinero , John J. O'Connor , Jon Pietrobon
IPC分类号： F01D5/18
摘要： A gas turbine engine configured to rotate in a circumferential direction about an axis extending through a center of the gas turbine engine comprises a turbine stage. The turbine stage comprises a disk, a plurality of blades and a mini-disk. The disk comprises an outer diameter edge having slots, an inner diameter bore surrounding the axis, a forward face, and an aft face. The plurality of blades is coupled to the slots. The mini-disk is coupled to the aft face of the rotor to define a cooling plenum therebetween in order to direct cooling air to the slots. In one embodiment of the invention, the cooling plenum is connected to a radially inner compressor bleed air inlet through all rotating components so that cooling air passes against the inner diameter bore.
摘要翻译： 构造成围绕延伸穿过燃气涡轮发动机的中心的轴线在圆周方向上旋转的燃气涡轮发动机包括涡轮级。 涡轮级包括盘，多个叶片和小型盘。 盘包括具有槽的外径边缘，围绕轴线的内径孔，前表面和后表面。 多个叶片耦合到槽。 微型盘联接到转子的后表面以在其间限定冷却室，以便将冷却空气引导到狭槽。 在本发明的一个实施例中，冷却气室通过所有旋转部件连接到径向内部的压缩机排放空气入口，使得冷却空气抵靠内径孔。
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公开(公告)号：US08517666B2
公开(公告)日：2013-08-27
申请号：US11224613
申请日：2005-09-12
CPC分类号： F01D5/081 , F01D11/001 , F01D25/12 , F02C7/18 , F02C7/28
摘要： A turbine engine section has a stationary vane stage and a rotating blade stage. The blade stage is spaced from the vane stage to form an annular chamber therebetween. A manifold delivers a pressurized fluid to the chamber. An outer diameter (OD) sealing system restricts leakage of the pressurized fluid from the chamber. An inner diameter (ID) sealing system restricts leakage of the pressurized fluid from the chamber. A flow guide extends radially between the inner diameter sealing system and the manifold. The flow guide bisects the chamber to form a stationary chamber portion and a rotating chamber portion, the rotating chamber portion at least partially along a disk of the first blade stage.
摘要翻译： 涡轮发动机部分具有静止叶片台和旋转叶片台。 叶片台与叶片台间隔开以在它们之间形成环形室。 歧管将加压流体输送到腔室。 外径（OD）密封系统限制加压流体从腔室泄漏。 内径（ID）密封系统限制加压流体从腔室泄漏。 流动引导件在内径密封系统和歧管之间径向延伸。 流动导向装置将室平分成一个固定室部分和一个旋转室部分，旋转室部分至少部分地沿着第一叶片台的圆盘。
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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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