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公开(公告)号：US20080112794A1
公开(公告)日：2008-05-15
申请号：US11595669
申请日：2006-11-10
IPC分类号： F01D1/00
CPC分类号： F02C7/12 , F01D5/189 , F05D2220/3212 , F05D2260/201 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine includes a compressor, combustor, and high pressure turbine operatively joined together. The turbine includes a nozzle followed by a row of rotor blades. A first bleed circuit is joined in flow communication between the last stage of the compressor and a forward cooling channel in vanes of the nozzle for feeding first cooling holes therein with pressurized primary air at a first pressure. A second bleed circuit is joined in flow communication between an intermediate stage of the compressor and aft cooling channels in the nozzle vanes to feed second cooling holes with pressurized secondary air at a second pressure less than the first pressure.
摘要翻译： 燃气涡轮发动机包括可操作地连接在一起的压缩机，燃烧器和高压涡轮机。 涡轮机包括喷嘴，随后是一排转子叶片。 第一泄放回路在压缩机的最后阶段和喷嘴的叶片中的前冷却通道之间流动连通地连接，用于在第一压力下用加压的一次空气向其中供给第一冷却孔。 第二泄放回路在压缩机的中间级与喷嘴叶片中的后冷却通道之间流动连通地连接，以在小于第一压力的第二压力下用加压的二次空气供给第二冷却孔。
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公开(公告)号：US08091334B2
公开(公告)日：2012-01-10
申请号：US13014168
申请日：2011-01-26
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：US20100192595A1
公开(公告)日：2010-08-05
申请号：US12363427
申请日：2009-01-30
IPC分类号： F02C3/10
CPC分类号： F02K3/072 , F02C7/36 , F05D2220/323 , F05D2220/327 , Y10T29/49229
摘要： A turbine engine assembly includes, a core gas turbine engine, a first low-pressure turbine section in serial flow communication with the core gas turbine engine, the first low-pressure turbine section configured to rotate in a first rotational direction, a first gear assembly coupled to the first low-pressure turbine section, a second low-pressure turbine section coupled to the gear assembly, the second low-pressure turbine section configured to rotate in a second rotational direction, and a fan assembly coupled to the second low-pressure turbine section.
摘要翻译： 涡轮发动机组件包括核心燃气涡轮发动机，与核心燃气涡轮发动机串联流动连通的第一低压涡轮机部分，第一低压涡轮机部分构造成沿第一旋转方向旋转，第一齿轮组件 耦合到第一低压涡轮部分，联接到齿轮组件的第二低压涡轮机部分，第二低压涡轮机部分构造成沿第二旋转方向旋转;以及风扇组件，其联接到第二低压涡轮机部分 涡轮段。
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公开(公告)号：US07752836B2
公开(公告)日：2010-07-13
申请号：US11253495
申请日：2005-10-19
IPC分类号： F02K3/00
CPC分类号： F02C3/067 , F02C3/107 , F02C7/36 , F02K3/072 , F05D2260/40311 , Y02T50/671
摘要： A method for assembling a gas turbine engine includes coupling a gearbox to a low-pressure turbine, the gearbox includes a plurality of planetary gears intermeshed with the sun gear, each of the planetary gears includes a first gear portion having a first diameter and a second gear portion having a second diameter that is different than the first diameter.
摘要翻译： 一种用于组装燃气涡轮发动机的方法包括将齿轮箱联接到低压涡轮机，齿轮箱包括与太阳齿轮啮合的多个行星齿轮，每个行星齿轮包括具有第一直径和第二直径的第一齿轮部分 齿轮部分具有与第一直径不同的第二直径。
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公开(公告)号：US07685808B2
公开(公告)日：2010-03-30
申请号：US11254143
申请日：2005-10-19
IPC分类号： F02K3/02
CPC分类号： F02K3/072 , F02C7/36 , F05D2230/60 , Y02T50/671
摘要： A method for assembling a gas turbine engine includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, and coupling a counter-rotating fan assembly to the core gas turbine engine such that air discharged from the counter-rotating fan assembly is channeled directly into an inlet of the gas turbine engine compressor.
摘要翻译： 燃气轮机的组装方法包括：提供包括高压压缩机，燃烧器和涡轮机的核心燃气涡轮发动机，将反向旋转的风扇组件与核心燃气涡轮发动机连接，使得从柜台排出的空气 旋转风扇组件直接引导到燃气涡轮发动机压缩机的入口。
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公开(公告)号：US07526913B2
公开(公告)日：2009-05-05
申请号：US11253416
申请日：2005-10-19
IPC分类号： F02K3/00
CPC分类号： F02K3/072 , F01D1/26 , F05D2230/60 , F05D2260/40311 , Y02T50/671
摘要： A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a gearbox including an input, a first output, and a second output, to the low-pressure turbine, coupling a first fan assembly to the gearbox first output, and coupling a second fan assembly to the gearbox second output.
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联接到核心涡轮发动机，将包括输入，第一输出和第二输出的变速箱联接到低压涡轮机，将第一风扇组件耦合到 变速箱首先输出，并将第二风扇组件连接到变速箱第二输出。
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公开(公告)号：US07513103B2
公开(公告)日：2009-04-07
申请号：US11254016
申请日：2005-10-19
IPC分类号： F02K3/00
CPC分类号： F01D1/26 , F02C3/067 , F02K3/072 , F05D2260/4031
摘要： A method for assembling a gas turbine engine includes coupling a low-pressure turbine to a core turbine engine, coupling a counter-rotating fan assembly including a forward fan assembly and an axially aft fan assembly to the low-pressure turbine such that the forward fan assembly rotates in a first direction and the aft fan assembly rotates in an opposite second direction, and coupling a booster compressor to the low-pressure turbine such that the booster compressor rotates in the first 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，将包括前风扇组件和轴向后风扇组件的反向旋转风扇组件联接到低压涡轮机，使得前风扇 组件沿第一方向旋转，并且后风扇组件沿相反的第二方向旋转，并且将增压压缩机联接到低压涡轮机，使得增压压缩机沿第一方向旋转。
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公开(公告)号：US20080159856A1
公开(公告)日：2008-07-03
申请号：US11648508
申请日：2006-12-29
CPC分类号： F01D25/162 , F01D5/147 , F01D9/041 , F02K3/06 , Y02T50/672 , Y02T50/673 , Y10T29/49337
摘要： A method for fabricating an outlet guide vane includes the steps of fabricating a structural spar from a first material, fabricating a fairing from a second material, and installing the fairing onto the spar so as to at least partially surround the spar and form an airfoil. An outlet guide vane includes an airfoil including a leading edge and a trailing edge, a structural spar formed from a first material located within the airfoil, and a fairing formed from a second material at least partially surrounding the spar. A gas turbine engine assembly includes a core gas turbine engine, a fan assembly including a plurality of fan blades coupled to the core gas turbine engine, and a plurality of outlet guide vanes coupled downstream from the fan blades, at least one of the outlet guide vanes including an airfoil having a leading edge and a trailing edge, a structural spar formed from a first material located within the airfoil, and a fairing formed from a second material at least partially surrounding the spar.
摘要翻译： 一种用于制造出口导向叶片的方法包括以下步骤：从第一材料制造结构翼梁，从第二材料制造整流罩，以及将整流罩安装在翼梁上，以至少部分地围绕翼梁并形成翼型。 出口导向叶片包括包括前缘和后缘的翼型，由位于翼型内的第一材料形成的结构翼梁和由至少部分围绕翼梁的第二材料形成的整流罩。 燃气涡轮发动机组件包括核心燃气涡轮发动机，风扇组件，其包括联接到核心燃气涡轮发动机的多个风扇叶片，以及多个与风扇叶片下游连接的出口导向叶片，出口导向件 叶片包括具有前缘和后缘的翼型，由位于翼型内的第一材料形成的结构翼梁，以及由至少部分围绕翼梁的第二材料形成的整流罩。
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29.发明申请Turbine engine system with shafts for improved weight and vibration characteristic 审中-公开具有轴的涡轮发动机系统，用于改善重量和振动特性公开(公告)号：US20080148708A1
公开(公告)日：2008-06-26
申请号：US11643501
申请日：2006-12-20
IPC分类号： F02K3/00
CPC分类号： F01D5/02 , F05C2201/0466 , F05D2300/121 , F05D2300/133 , F05D2300/171 , F05D2300/603 , F05D2300/614 , F05D2300/702 , Y02T50/67 , Y02T50/672 , Y02T50/6765
摘要： A method for assembling a turbine engine assembly is provided. The turbine engine includes a core engine. The method includes coupling a first rotor spool within the engine assembly wherein the first rotor spool includes a first shaft. The method further includes coupling a second rotor spool within the engine assembly wherein the second rotor spool includes a second shaft. The method also includes coupling a third rotor spool within the engine assembly wherein the third rotor spool includes a third shaft. At least one of the first, second, and third shafts include a first end, an opposing second end, and a tubular portion extending between the first and second ends. A reinforcing layer circumscribes a portion of the tubular portion wherein at least a portion of the reinforcing layer is a metallic matrix composite (MMC) material that includes reinforcing fibers. A turbine engine is also provided.
摘要翻译： 提供了一种用于组装涡轮发动机组件的方法。 涡轮发动机包括核心发动机。 该方法包括将第一转子线轴联接在发动机组件内，其中第一转子线轴包括第一轴。 该方法还包括将第二转子线轴联接在发动机组件内，其中第二转子线轴包括第二轴。 该方法还包括在发动机组件内连接第三转子线轴，其中第三转子线轴包括第三轴。 第一，第二和第三轴中的至少一个包括第一端，相对的第二端和在第一和第二端之间延伸的管状部分。 加强层围绕管状部分的一部分，其中至少一部分增强层是包括增强纤维的金属基复合材料（MMC）材料。 还提供涡轮发动机。
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公开(公告)号：US20080098715A1
公开(公告)日：2008-05-01
申请号：US11554997
申请日：2006-10-31
IPC分类号： F02K3/02
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 counter-rotating fan assembly disposed upstream from the booster compressor, the counter-rotating fan assembly comprising a first fan configured to rotate in a first direction and a second fan configured to rotate in an opposite second direction, and an intermediate-pressure turbine disposed downstream from the core gas turbine engine, wherein the intermediate-pressure turbine drives the booster compressor and the second fan assembly. 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， 所述中压涡轮机设置在所述核心燃气涡轮发动机的下游，配置在所述增压压缩机的上游的反向旋转风扇组件，所述反向旋转风扇组件包括构造成沿第一方向旋转的第一风扇和配置为 在相对的第二方向上旋转，以及设置在所述核心燃气涡轮发动机下游的中压涡轮机，其中所述中压涡轮机驱动所述增压压缩机和所述第二风扇组件。 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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