-
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。
-
公开(公告)号：US20080098713A1
公开(公告)日：2008-05-01
申请号：US11553571
申请日：2006-10-27
IPC分类号： F02K3/02
CPC分类号： F02K3/06 , F01D15/12 , F02K3/072 , Y02T50/671
摘要： A method of assembling a gas turbine assembly includes providing a core gas turbine engine including a high-pressure compressor, a combustor, and a turbine, coupling a low-pressure turbine to the core gas turbine engine, coupling a booster compressor to a gearbox, and coupling the gearbox to the low-pressure turbine such that the booster compressor is driven by the low-pressure turbine.
摘要翻译： 一种组装燃气轮机组件的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，将低压涡轮机耦合到核心燃气涡轮发动机，将升压压缩机连接到变速箱， 并且将所述齿轮箱联接到所述低压涡轮机，使得所述增压压缩机由所述低压涡轮机驱动。
-
公开(公告)号：US07290386B2
公开(公告)日：2007-11-06
申请号：US10976497
申请日：2004-10-29
IPC分类号： F02C3/067
CPC分类号： F01D1/26 , F01D5/03 , F02C3/067 , F02K3/072 , F05D2230/60
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 turbine blade rows configured to rotate in a first direction, and rotatably coupling a low-pressure turbine outer rotor to the inner rotor, wherein the outer rotor includes a second plurality of turbine blade rows that are configured to rotate in a second direction that is opposite the first rotational direction of the inner rotor and such that at least one of the second plurality of turbine blade rows is coupled axially forward of the first plurality of turbine blade rows.
摘要翻译： 一种用于组装燃气涡轮发动机的方法，其包括提供低压涡轮机内转子，所述低转速涡轮机内转子包括构造成沿第一方向旋转的第一多个涡轮叶片排，以及将低压涡轮机外转子可旋转地联接到所述内转子， 其中所述外转子包括第二多个涡轮机叶片排，所述第二多个涡轮机叶片排被构造成沿与所述内转子的第一旋转方向相反的第二方向旋转，并且使得所述第二多个涡轮机叶片排中的至少一个轴向向前 的第一组涡轮机叶片排。
-
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
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：US20110120136A1
公开(公告)日：2011-05-26
申请号：US13014168
申请日：2011-01-26
IPC分类号： F02C9/00
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。
-
公开(公告)号：US07883311B2
公开(公告)日：2011-02-08
申请号：US11643502
申请日：2006-12-20
CPC分类号： F04D29/0513 , F16C17/024 , F16C17/042 , F16C2360/23 , Y10T29/49826
摘要： A rotor assembly for a gas turbine engine is provided. The rotor assembly includes a compressor rotor, a compressor stator coupled upstream from the compressor rotor, and a bearing assembly coupled between the compressor rotor and the compressor stator for supporting the compressor rotor. The bearing assembly includes a pair of foil thrust bearings coupled to a portion of the compressor stator and a pair of spring packs coupled substantially co-axially to the pair of foil thrust bearings. A method of assembling the same is also provided.
摘要翻译： 提供了一种用于燃气涡轮发动机的转子组件。 转子组件包括压缩机转子，联接在压缩机转子上游的压缩机定子和联接在压缩机转子和压缩机定子之间以支撑压缩机转子的轴承组件。 轴承组件包括耦合到压缩机定子的一部分的一对箔推力轴承和一对基本上同轴地联接到该对推力轴承的一对弹簧组件。 还提供了一种组装方法。
-
公开(公告)号：US07841165B2
公开(公告)日：2010-11-30
申请号：US11555042
申请日：2006-10-31
CPC分类号： F02K3/072 , F01D15/12 , 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 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 directly 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，并且将增压压缩机直接连接到低压涡轮机，使得增压压缩机沿第一方向旋转。
-
公开(公告)号：US07493754B2
公开(公告)日：2009-02-24
申请号：US11254018
申请日：2005-10-19
IPC分类号： F02K3/00
CPC分类号： F02K3/072 , F01D25/162 , F02C3/107 , F02C7/36 , F05D2230/642 , F05D2250/41 , F05D2260/40311 , F16D1/101 , F16D2001/103
摘要： A method for assembling a gas turbine engine including providing a core gas turbine engine at least partially defined by a frame and having a drive shaft rotatable about a longitudinal axis of the core gas turbine engine. A low-pressure turbine is coupled to a core turbine engine. A counter-rotating fan assembly is coupled to the low-pressure turbine. The counter-rotating fan assembly includes a first fan assembly and a second fan assembly. A booster compressor is coupled to the second fan assembly. A gearbox is securely coupled to the frame so that the gearbox is circumferentially positioned about the drive shaft. The first fan assembly is rotatably coupled to an input of the gearbox such that the first fan assembly rotates in a first direction. The second fan assembly is rotatably coupled to an output of the gearbox such that the second fan assembly rotates in a second direction opposite the first direction.
摘要翻译： 一种用于组装燃气涡轮发动机的方法，包括提供至少部分地由框架限定并具有可围绕核心燃气涡轮发动机的纵向轴线旋转的驱动轴的核心燃气涡轮发动机。 低压涡轮联接到核心涡轮发动机。 反向旋转的风扇组件联接到低压涡轮机。 反向风扇组件包括第一风扇组件和第二风扇组件。 增压压缩机联接到第二风扇组件。 齿轮箱牢固地联接到框架，使得齿轮箱围绕驱动轴周向定位。 第一风扇组件可旋转地联接到齿轮箱的输入端，使得第一风扇组件沿第一方向旋转。 第二风扇组件可旋转地联接到齿轮箱的输出，使得第二风扇组件沿与第一方向相反的第二方向旋转。
-
公开(公告)号：US07490461B2
公开(公告)日：2009-02-17
申请号：US11254017
申请日：2005-10-19
IPC分类号： F02K3/00
CPC分类号： F02K3/072 , F05D2230/60
摘要： A method for assembling a gas turbine engine including providing a core gas turbine engine at least partially defined by a frame. The gas turbine engine has a drive shaft that is rotatable about a longitudinal axis of the core gas turbine engine. A counter-rotating fan assembly is coupled to the low-pressure turbine. The counter-rotating fan includes a first fan assembly that rotates in a first direction and a second fan assembly that rotates in an opposite second direction. A booster compressor is coupled to the second fan assembly. A first bearing assembly is mounted between the drive shaft and the frame and operatively coupled to the first fan assembly to transmit thrust force from the first fan assembly to the frame. A second bearing assembly is mounted with respect to the second fan assembly and operatively coupled to the second fan assembly to transfer thrust force from at least one of the second fan assembly and the booster compressor to the second bearing assembly.
摘要翻译： 一种用于组装燃气涡轮发动机的方法，包括提供至少部分地由框架限定的核心燃气涡轮发动机。 燃气涡轮发动机具有能够围绕核心燃气涡轮发动机的纵向轴线旋转的驱动轴。 反向旋转的风扇组件联接到低压涡轮机。 反向旋转风扇包括沿第一方向旋转的第一风扇组件和沿相反的第二方向旋转的第二风扇组件。 增压压缩机联接到第二风扇组件。 第一轴承组件安装在驱动轴和框架之间并且可操作地联接到第一风扇组件以将推力从第一风扇组件传递到框架。 第二轴承组件相对于第二风扇组件安装并且可操作地联接到第二风扇组件以将推力从第二风扇组件和增压压缩机中的至少一个传递到第二轴承组件。
-
公开(公告)号：US20080152477A1
公开(公告)日：2008-06-26
申请号：US11643502
申请日：2006-12-20
IPC分类号： F01D11/00
CPC分类号： F04D29/0513 , F16C17/024 , F16C17/042 , F16C2360/23 , Y10T29/49826
摘要： A rotor assembly for a gas turbine engine is provided. The rotor assembly includes a compressor rotor, a compressor stator coupled upstream from the compressor rotor, and a bearing assembly coupled between the compressor rotor and the compressor stator for supporting the compressor rotor. The bearing assembly includes a pair of foil thrust bearings coupled to a portion of the compressor stator and a pair of spring packs coupled substantially co-axially to the pair of foil thrust bearings. A method of assembling the same is also provided.
摘要翻译： 提供了一种用于燃气涡轮发动机的转子组件。 转子组件包括压缩机转子，联接在压缩机转子上游的压缩机定子和联接在压缩机转子和压缩机定子之间以支撑压缩机转子的轴承组件。 轴承组件包括耦合到压缩机定子的一部分的一对箔推力轴承和一对基本上同轴地联接到该对推力轴承的一对弹簧组件。 还提供了一种组装方法。
-
-
-
-
-
-
-
-
-
搜索结果
96 条记录 (耗时 0.033 秒)
