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61.发明申请公开(公告)号：US20080148881A1
公开(公告)日：2008-06-26
申请号：US11614623
申请日：2006-12-21
IPC分类号： F16H37/00
CPC分类号： F02C7/32 , F05D2220/50 , F05D2220/76 , F05D2260/4031 , Y02T50/671 , Y10T29/4932
摘要： A power take-off system for a gas turbine engine includes a starter coupled to a first spool using a first shaft, and a generator coupled to the second spool using a second shaft, the first shaft is circumferentially offset by the second shaft by an angle α. A method of assembling a gas turbine engine assembly that includes the power take-off system, and a gas turbine engine assembly including the power take-off system are also described.
摘要翻译： 用于燃气涡轮发动机的动力输出系统包括使用第一轴联接到第一阀芯的起动器和使用第二轴联接到第二阀芯的发电机，第一轴由第二轴沿周向偏移一定角度 α。 还描述了组装包括动力输出系统的燃气涡轮发动机组件的方法和包括动力输出系统的燃气涡轮发动机组件。
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公开(公告)号：US20080112802A1
公开(公告)日：2008-05-15
申请号：US11559773
申请日：2006-11-14
IPC分类号： F01D1/02
摘要： A turbofan engine assembly is provided. The turbofan engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, a fan nozzle duct defined between the core cowl and the nacelle, and an inner core cowl baffle assembly positioned within the fan nozzle duct. The inner core cowl baffle assembly includes a first core cowl baffle coupled to a portion of the core cowl within the fan nozzle duct, a second core cowl baffle coupled to a portion of the core cowl and positioned a distance radially inward from the first core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the second core cowl baffle with respect to the first core cowl baffle. A method for operating the turbofan engine assembly is also provided.
摘要翻译： 提供涡轮风扇发动机总成。 涡轮风扇发动机组件包括核心燃气涡轮发动机，外围核心燃气涡轮发动机的核心罩，从核心整流罩径向向外定位的机舱，限定在核心整流罩和机舱之间的风扇喷嘴管道，以及内部核心整流罩 挡板组件位于风扇喷嘴管道内。 内芯整流罩挡板组件包括耦合到风扇喷嘴管道内的核心整流罩的一部分的第一磁芯整流罩挡板，耦合到磁芯整流罩的一部分并且与第一磁芯整流罩径向向内定位的第二磁芯整流罩挡板 挡板和致动器组件，其被配置成通过相对于第一芯导流板挡板选择性地重新定位第二芯面罩挡板来改变风扇喷嘴管道的喉部区域。 还提供了一种用于操作涡扇发动机组件的方法。
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公开(公告)号：US20080098714A1
公开(公告)日：2008-05-01
申请号：US11554993
申请日：2006-10-31
IPC分类号： F02K3/02
CPC分类号： F02K3/072 , F02C7/36 , F16H57/0479 , F16H57/0486
摘要： A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a booster compressor coupled upstream from the core gas turbine engine, an intermediate-pressure turbine coupled to the booster compressor, the intermediate-pressure turbine disposed downstream from the core gas turbine engine, a first fan assembly coupled to a low-pressure turbine, a second fan assembly disposed downstream from the first fan assembly, and a gearbox coupled between the second fan assembly and the low-pressure turbine. A method of assembling the above turbofan engine assembly is also described herein.
摘要翻译： 涡轮风扇发动机组件包括：核心燃气涡轮发动机，其包括高压压缩机，燃烧器和高压涡轮，耦合在核心燃气涡轮发动机上游的增压压缩机，耦合到增压压缩机的中压涡轮机， 设置在核心燃气涡轮发动机下游的中压涡轮机，耦合到低压涡轮机的第一风扇组件，设置在第一风扇组件下游的第二风扇组件，以及联接在第二风扇组件和低压涡轮机之间的齿轮箱 压力涡轮机。 本文还描述了组装上述涡轮风扇发动机组件的方法。
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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
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。
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公开(公告)号：US07334981B2
公开(公告)日：2008-02-26
申请号：US10976590
申请日：2004-10-29
CPC分类号： F01D25/16 , F02K3/072 , Y10T29/4932 , Y10T29/49321
摘要： A method for assembling a gas turbine engine that includes providing a low-pressure turbine inner rotor that includes a first plurality of rows of turbine blades configured to rotate in a first rotational direction, providing a low-pressure turbine outer rotor that includes a second plurality of rows of turbine blades configured to rotate in a rotational direction that is opposite the first rotational direction, and coupling a support structure between the outer rotor and a turbine mid-frame such that the support structure supports a forward end of the outer rotor, and wherein the support structure includes a first portion that has a first coefficient of thermal expansion and a second portion that has a second coefficient of thermal expansion that is different than the first coefficient of thermal expansion.
摘要翻译： 一种用于组装燃气涡轮发动机的方法，包括提供低压涡轮内转子，所述低转速涡轮内转子包括构造成沿第一旋转方向旋转的第一多排涡轮叶片，提供包括第二多个的低压涡轮机外转子 涡轮叶片的行被构造成沿与第一旋转方向相反的旋转方向旋转，并且在外转子和涡轮机中间框架之间联接支撑结构，使得支撑结构支撑外转子的前端，以及 其中所述支撑结构包括具有第一热膨胀系数的第一部分和具有不同于所述第一热膨胀系数的第二热膨胀系数的第二部分。
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公开(公告)号：US06935837B2
公开(公告)日：2005-08-30
申请号：US10376892
申请日：2003-02-27
CPC分类号： F01D9/065 , F01D11/005 , F01D25/162 , F01D25/24 , F02C7/20 , F05D2230/60 , F05D2230/642
摘要： A method enables a gas turbine engine including a first rotor assembly and a second rotor assembly coupled in axial flow communication downstream from the first rotor assembly to be assembled. The method comprises coupling an upstream end of an extension duct to an outlet of the first rotor assembly, wherein the extension duct includes a plurality of panels coupled circumferentially, and coupling a downstream end of the extension duct to an inlet of the second rotor assembly using at least one fish mouth seal.
摘要翻译： 一种方法使得能够包括第一转子组件和第二转子组件的燃气涡轮发动机，该第一转子组件和第二转子组件在与第一转子组件的下游轴向流动连通地联接以被组装。 该方法包括将延伸管道的上游端连接到第一转子组件的出口，其中延伸管道包括沿圆周方向连接的多个面板，并且将延伸管道的下游端部与第二转子组件的入口连接，该第二转子组件的入口使用 至少有一个鱼嘴密封。
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67.发明授权公开(公告)号：US06739120B2
公开(公告)日：2004-05-25
申请号：US10134172
申请日：2002-04-29
IPC分类号： F02C706
摘要： A counterrotatable booster compressor assembly for a gas turbine engine having a counterrotatable fan section with a first fan blade row connected to a first drive shaft and a second fan blade row axially spaced from the first fan blade row and connected to a second drive shaft, the counterrotatable booster compressor assembly including a first compressor blade row connected to the first drive shaft and a second compressor blade row interdigitated with the first compressor blade row and connected to the second drive shaft. A portion of each fan blade of the second fan blade row extends through a flowpath of the counterrotatable booster compressor so as to function as a compressor blade in the second compressor blade row. The counterrotatable booster compressor further includes a first platform member integral with each fan blade of the second fan blade row at a first location so as to form an inner flowpath for the counterrotatable booster compressor and a second platform member integral with each fan blade of the second fan blade row at a second location so as to form an outer flowpath for the counterrotatable booster compressor.
摘要翻译： 一种用于燃气涡轮发动机的可逆转增压压缩机组件，其具有可逆转风扇部分，其具有连接到第一驱动轴的第一风扇叶片排和与第一风扇叶片排轴向间隔开并连接到第二驱动轴的第二风扇叶片排， 可逆增压压缩机组件包括连接到第一驱动轴的第一压缩机叶片排和与第一压缩机叶片排交叉并连接到第二驱动轴的第二压缩机叶片排。 第二风扇叶片排的每个风扇叶片的一部分延伸穿过可逆转增压压缩机的流路，以便起到第二压缩机叶片排中的压缩机叶片的作用。 可逆转增压压缩机还包括第一平台构件，其在第一位置处与第二风扇叶片排的每个风扇叶片成一体，以形成用于可逆转增压压缩机的内部流路，以及与第二风扇叶片的第二平台构件成一体的第二平台构件 风扇叶片排在第二位置，以便形成用于可逆转助力式压缩机的外部流路。
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公开(公告)号：US07966806B2
公开(公告)日：2011-06-28
申请号：US11555097
申请日：2006-10-31
CPC分类号： F02C3/067 , F02C7/36 , F05D2260/40311
摘要： A turbofan engine assembly includes a core gas turbine engine including a high-pressure compressor, a combustor, and a high-pressure turbine, a low-pressure turbine coupled to said core gas turbine engine, a counter-rotating booster compressor comprising a first rotor section configured to rotate in a first direction and a second rotor section configured to rotate in an opposite second direction, and a gearbox comprising an input and an output, said gearbox output coupled to at least one of said first and second rotor sections, said gearbox input coupled to said low-pressure turbine. A method of assembling the turbofan engine assembly described herein is also provided.
摘要翻译： 涡轮风扇发动机组件包括：包括高压压缩机，燃烧器和高压涡轮机的核心燃气涡轮发动机，与所述核心燃气涡轮发动机相连的低压涡轮;反向旋转增压压缩机，包括第一转子 其构造成沿第一方向旋转，第二转子部分构造成沿相反的第二方向旋转;以及齿轮箱，包括输入和输出，所述齿轮箱输出联接到所述第一和第二转子部分中的至少一个，所述变速箱 输入端连接到所述低压涡轮。 还提供了一种组装本文所述涡轮风扇发动机组件的方法。
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公开(公告)号：US07886518B2
公开(公告)日：2011-02-15
申请号：US11559747
申请日：2006-11-14
IPC分类号： F02K1/08
CPC分类号： F02K1/08 , Y02T50/671
摘要： An inner core cowl baffle assembly for a turbofan engine assembly is provided. The engine assembly includes a core gas turbine engine, a core cowl which circumscribes the core gas turbine engine, a nacelle positioned radially outward from the core cowl, and a fan nozzle duct defined between the core cowl and the nacelle. The inner core cowl baffle assembly includes an inner core cowl baffle, and an actuator assembly configured to vary the throat area of the fan nozzle duct by selectively repositioning the inner core cowl baffle with respect to the core cowl.
摘要翻译： 提供了一种用于涡扇发动机组件的内芯前罩挡板组件。 发动机组件包括核心燃气涡轮发动机，外围核心燃气涡轮发动机的核心罩，从核心罩的径向外侧定位的机舱，以及限定在核心罩和机舱之间的风扇喷嘴管道。 内芯整流罩挡板组件包括内芯前罩挡板和致动器组件，该致动器组件构造成通过相对于内芯罩来选择性地重新定位内芯整流罩挡板来改变风扇喷嘴管道的喉部区域。
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公开(公告)号：US07726113B2
公开(公告)日：2010-06-01
申请号：US11253934
申请日：2005-10-19
CPC分类号： F02K3/072 , F02C3/107 , F02C7/36 , F05D2240/40 , F05D2260/4031 , Y02T50/671
摘要： A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, and coupling a counter-rotating fan assembly including a first fan assembly and a second fan assembly to the low-pressure turbine such that the first fan assembly rotates in a first direction and the second fan assembly rotates in an opposite second direction.
摘要翻译： 一种用于组装燃气涡轮发动机的方法包括将低压涡轮机耦合到核心涡轮发动机，以及将包括第一风扇组件和第二风扇组件的反向旋转风扇组件耦合到低压涡轮机，使得第一风扇 组件沿第一方向旋转，并且第二风扇组件沿相反的第二方向旋转。
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