公开(公告)号：US07353647B2

公开(公告)日：2008-04-08

申请号：US10845032

申请日：2004-05-13

申请人： Robert Joseph Orlando ,  Thomas Ory Moniz ,  John C. Brauer ,  John Leslie Henry ,  Raymond Felix Patt ,  Randy Marinus Vondrell ,  James Patrick Dolan ,  Erich Alois Krammer ,  David Cory Kirk

发明人： Robert Joseph Orlando ,  Thomas Ory Moniz ,  John C. Brauer ,  John Leslie Henry ,  Raymond Felix Patt ,  Randy Marinus Vondrell ,  James Patrick Dolan ,  Erich Alois Krammer ,  David Cory Kirk

IPC分类号： F02C3/04 ,  F02K3/04

CPC分类号： F02C3/13 ,  F02C3/04 ,  F05D2230/60

摘要： A method facilitates assembling a gas turbine engine including a compressor and a rotor assembly coupled in axial flow communication downstream from the compressor. The method comprises coupling a bypass system in flow communication with the compressor to channel a portion of flow discharged from the compressor towards the rotor assembly is channeled through the bypass system, and coupling a downstream end of the bypass system within the gas turbine engine such that the flow entering the bypass system flows past the rotor assembly and is discharged downstream from the rotor assembly.

摘要翻译： 一种方法有利于组装燃气涡轮发动机，该燃气涡轮发动机包括压缩机和在压缩机下游的轴向流动连通中联接的转子组件。 该方法包括将与压缩机流体连通的旁路系统联接以将从压缩机排出的一部分流向转子组件引导通过旁路系统，并将旁路系统的下游端连接在燃气涡轮发动机内，使得 进入旁路系统的流量流过转子组件，并从转子组件的下游排出。

公开(公告)号：US07007488B2

公开(公告)日：2006-03-07

申请号：US10885147

申请日：2004-07-06

申请人： Robert Joseph Orlando ,  Thomas Ory Moniz ,  John Christopher Brauer ,  Ian Francis Prentice ,  Erich Alois Krammer ,  James Patrick Dolan ,  Robert Alan Frederick

发明人： Robert Joseph Orlando ,  Thomas Ory Moniz ,  John Christopher Brauer ,  Ian Francis Prentice ,  Erich Alois Krammer ,  James Patrick Dolan ,  Robert Alan Frederick

IPC分类号： F02C7/12

CPC分类号： F01D9/065 ,  F02C6/08

摘要： A gas turbine engine includes a compressor powered by a turbine. The turbine includes a nozzle having vanes extending between outer and inner bands. Each vane includes an internal cooling plenum and a bypass tube extending through the bands. First and second manifolds surround the outer band and are disposed in flow communication with the plenums and bypass tubes, respectively. A bleed circuit joins the compressor to the manifolds for providing pressurized air thereto. A control valve modulates airflow to the first manifold and in turn through the cooling plenums of the vanes.

摘要翻译： 燃气涡轮发动机包括由涡轮机供电的压缩机。 涡轮机包括具有在外带和内带之间延伸的叶片的喷嘴。 每个叶片包括一个内部冷却通风室和一个延伸穿过该带的旁通管。 第一和第二歧管围绕外部带并分别设置成与集气室和旁通管流动连通。 泄放回路将压缩机连接到歧管，以向其提供加压空气。 控制阀调节到第一歧管的气流，并依次通过叶片的冷却增压室。

公开(公告)号：US08388308B2

公开(公告)日：2013-03-05

申请号：US11928199

申请日：2007-10-30

申请人： Apostolos Pavlos Karafillis ,  Kalyanasundaram Muruganathan ,  Samuel Rulli ,  David Cory Kirk ,  Donald Charles Slavik ,  Erich Alois Krammer ,  Manish Kumar

发明人： Apostolos Pavlos Karafillis ,  Kalyanasundaram Muruganathan ,  Samuel Rulli ,  David Cory Kirk ,  Donald Charles Slavik ,  Erich Alois Krammer ,  Manish Kumar

IPC分类号： F01B25/00

CPC分类号： F01D17/105 ,  F04D29/522

摘要： A system for asymmetric flow extraction is described and claimed, the system comprising a flow path, a bleed slot in the flow path, a bleed cavity for receiving at least a portion of the fluid extracted from the flow path and a bleed passage in flow communication with the bleed slot and the bleed cavity wherein the bleed passage has at least one deflector having a shape such that the width of the bleed passage cross section varies in a direction normal to the direction of fluid flow in the bleed passage. In another embodiment, the deflector has an aerodynamic surface having a shape such that the flow passage between the aerodynamic surface and a surface located away from it has a cross sectional shape that is non-axisymmetric. In another embodiment, the bleed passage comprises an assembly of a plurality deflectors, arranged circumferentially.

摘要翻译： 一种用于不对称流提取的系统被描述和要求保护，该系统包括流路，流路中的排放槽，用于接收从流路中提取的流体的至少一部分的流出腔和流通 具有排出狭槽和排出腔，其中排出通道具有至少一个导流器，其具有使得排放通道横截面的宽度在垂直于排出通道中的流体流动方向的方向上变化的形状。 在另一个实施例中，偏转器具有空气动力学表面，该空气动力学表面的形状使得空气动力学表面与远离其的表面之间的流动通道具有非轴对称的横截面形状。 在另一个实施例中，排放通道包括沿圆周布置的多个偏转器的组件。

公开(公告)号：US06981841B2

公开(公告)日：2006-01-03

申请号：US10718149

申请日：2003-11-20

申请人： Erich Alois Krammer ,  Richard Clay Haubert ,  Ching-Pang Lee ,  Harvey Michael Maclin

发明人： Erich Alois Krammer ,  Richard Clay Haubert ,  Ching-Pang Lee ,  Harvey Michael Maclin

IPC分类号： F03D11/00

CPC分类号： F01D25/12 ,  F01D5/082 ,  F01D5/084 ,  F01D5/085 ,  F02C7/18 ,  Y02T50/673 ,  Y02T50/676

摘要： A turbofan engine includes in serial flow communication a first fan, second fan, multistage compressor, combustor, first turbine, second turbine, and third turbine. The first turbine is joined to the compressor by a first shaft. The second turbine is joined to the second fan by a second shaft. And, the third turbine is joined to the first fan by a third shaft. First, second, and third cooling circuits are joined to different stages of the compressor for cooling the forward and aft sides and center bore of the first turbine with different pressure air.

摘要翻译： 涡轮风扇发动机包括串联流动连通的第一风扇，第二风扇，多级压缩机，燃烧器，第一涡轮机，第二涡轮机和第三涡轮机。 第一涡轮机通过第一轴连接到压缩机。 第二涡轮机通过第二轴连接到第二风扇。 并且，第三涡轮机通过第三轴接合到第一风扇。 第一，第二和第三冷却回路连接到压缩机的不同阶段，用不同的压力空气冷却第一涡轮机的前后侧和中心孔。