-
公开(公告)号：US07334392B2
公开(公告)日：2008-02-26
申请号：US10977075
申请日：2004-10-29
CPC分类号： F02K3/072 , F01D1/24 , F02C3/067 , Y02T50/671
摘要： A method for assembling a gas turbine engine includes providing a first fan assembly including a plurality of rotor blades that are configured to rotate in a first rotational direction at a first rotational speed, rotatably coupling a second fan assembly axially aft of the first fan assembly, wherein the second fan assembly includes a plurality of rotor blades that are configured to rotate in a second rotational direction, and coupling a gearbox to the second fan assembly that is configured to rotate the second fan assembly at a second rotational speed that is different than the first rotational speed.
摘要翻译： 一种用于组装燃气涡轮发动机的方法包括：提供第一风扇组件，其包括多个转子叶片，所述多个转子叶片构造成以第一转速沿第一旋转方向旋转，可旋转地联接第一风扇组件， 其中所述第二风扇组件包括多个转子叶片，所述多个转子叶片被构造成沿第二旋转方向旋转，并且将齿轮箱联接到所述第二风扇组件，所述第二风扇组件被构造成以不同于所述第二风扇组件的第二转速旋转所述第二风扇组件 第一转速。
-
公开(公告)号：US07269938B2
公开(公告)日：2007-09-18
申请号：US10976494
申请日：2004-10-29
IPC分类号： F02C3/067
CPC分类号： F02K3/072 , F01D25/16 , F02C3/067 , F16C17/024 , F16C19/50 , F16C2360/23
摘要： A method for assembling a gas turbine engine includes providing a high pressure turbine, providing a low-pressure turbine inner rotor that includes a first plurality of turbine blade rows configured to rotate in a first direction, providing a low-pressure turbine outer rotor that includes a second plurality of turbine blade rows configured to rotate in a second direction that is opposite the first direction, and coupling a plurality of bearings between the outer rotor and a turbine mid-frame between the high pressure turbine and at least one of the inner and outer rotors such that the plurality of bearings support a forward end of the outer rotor.
摘要翻译： 一种用于组装燃气涡轮发动机的方法包括提供高压涡轮机，提供包括构造成在第一方向上旋转的第一多个涡轮叶片排的低压涡轮机内转子，提供低压涡轮机外转子，其包括 第二组多个涡轮机叶片排，其构造成沿与第一方向相反的第二方向旋转;以及将外转子和涡轮机中间框架之间的多个轴承联接在高压涡轮机与至少一个内部和 外转子使得多个轴承支撑外转子的前端。
-
公开(公告)号：US07096674B2
公开(公告)日：2006-08-29
申请号：US10941546
申请日：2004-09-15
申请人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee , Thomas Ory Moniz , Kurt David Murrow
发明人： Robert Joseph Orlando , Kattalaicheri Srinivasan Venkataramani , Ching-Pang Lee , Thomas Ory Moniz , Kurt David Murrow
IPC分类号： F02C6/08
CPC分类号： F02C7/18 , F02C5/00 , F05D2260/20 , F05D2260/96 , F23R3/005 , F23R3/04 , F23R7/00 , F23R2900/03044 , F23R2900/03281 , Y02T50/676
摘要： A gas turbine engine having a longitudinal centerline axis therethrough, including: a fan section at a forward end of the gas turbine engine including at least a first fan blade row connected to a first drive shaft; a booster compressor positioned downstream of and in at least partial flow communication with the fan section including a plurality of stages, each stage including a stationary compressor blade row and a rotating compressor blade row connected to a drive shaft and interdigitated with the stationary compressor blade row; a core system positioned downstream of the compressor, where the core system further includes an intermediate compressor positioned downstream of and in flow communication with the booster compressor, the intermediate compressor being connected to a second drive shaft, and a combustion system for producing pulses of gas having increased pressure and temperature from a fluid flow provided to an inlet thereof so as to produce a working fluid at an outlet; and, a low pressure turbine positioned downstream of and in flow communication with the core system, the low pressure turbine being utilized to power the first drive shaft. The core system may also include an intermediate turbine positioned downstream of the combustion system in flow communication with the working fluid, where the intermediate turbine is utilized to power the second drive shaft. A first source of compressed air having a predetermined pressure is provided to the combustion system inlet and a second source of compressed air having a pressure greater than the first source of compressed air is provided to cool the combustion system.
摘要翻译： 一种燃气涡轮发动机，其具有穿过其的纵向中心线轴线，包括：在所述燃气涡轮发动机的前端处的风扇部分，至少包括连接到第一驱动轴的第一风扇叶片排; 位于与包括多个级的风扇部分的下游并且至少部分流动连通的增压压缩机，每个级包括固定压缩机叶片排和连接到驱动轴的旋转压缩机叶片排，并与固定压缩机叶片排相互指向 ; 位于压缩机下游的核心系统，其中所述核心系统还包括位于所述增压压缩机下游并与所述增压压缩机流动连通的中间压缩机，所述中间压缩机连接到第二驱动轴，以及用于产生气体脉冲的燃烧系统 从提供给其入口的流体流增加压力和温度，以便在出口处产生工作流体; 以及低压涡轮机，其位于所述核心系统的下游并与所述核心系统流动连通，所述低压涡轮机用于为所述第一驱动轴提供动力。 核心系统还可以包括位于燃烧系统下游的中间涡轮机，其与工作流体流动连通，其中中间涡轮机用于为第二驱动轴提供动力。 具有预定压力的第一压缩空气源被提供给燃烧系统入口，并且提供具有大于第一压缩空气源的压力的第二压缩空气源以冷却燃烧系统。
-
24.发明授权Aircraft gas turbine engine having variable torque split counter rotating low pressure turbines and booster aft of counter rotating fans 有权飞机燃气涡轮发动机具有可变转矩分流反转旋转低压涡轮机和增压器逆向旋转风扇公开(公告)号：US06763654B2
公开(公告)日：2004-07-20
申请号：US10260480
申请日：2002-09-30
IPC分类号： F02K3072
CPC分类号： F01D1/24 , F02C3/067 , F02K3/072 , Y02T50/671
摘要： A gas turbine engine turbine assembly includes a high pressure spool having a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft which is rotatable about an engine centerline. A low pressure turbine has counter rotatable low pressure inner and outer shaft turbines with a row of low pressure variable vanes disposed therebetween and drivingly connected to coaxial low pressure inner and outer shafts respectively which are located radially inwardly of the high pressure spool. The low pressure inner and outer shaft turbines are drivingly connected to a forward and aft fan blade rows by the low pressure inner and outer shafts. A single direction of rotation booster is drivenly connected to the low pressure outer shaft and axially located aft and downstream of the aft fan blade row.
摘要翻译： 一种燃气涡轮发动机涡轮组件包括具有高压涡轮机的高压阀芯，所述高压涡轮机通过可围绕发动机中心线旋转的高压轴驱动地连接到高压压缩机。 低压涡轮机具有反转的低压内外涡轮机，其一排低压可变叶片设置在它们之间并分别驱动地连接到位于高压线轴的径向内侧的同轴低压内外轴和外轴。 低压内外涡轮机通过低压内外轴驱动连接到前风扇叶片和后风扇叶片排。 单向旋转助力器驱动地连接到低压外轴并且轴向位于后风扇叶片排的后部和下游。
-
公开(公告)号：US06763653B2
公开(公告)日：2004-07-20
申请号：US10253156
申请日：2002-09-24
IPC分类号： F02K302
CPC分类号： F02C3/067 , F02K3/072 , Y02T50/671
摘要： A gas turbine engine turbine assembly includes a high pressure spool having a high pressure turbine drivingly connected to a high pressure compressor by a high pressure shaft which is rotatable about an engine centerline. A low pressure turbine has counter rotatable low pressure inner and outer shaft turbines drivingly connected to coaxial low pressure inner and outer shafts respectively which are at least in part rotatably disposed co-axial with and radially inwardly of the high pressure spool. The low pressure inner shaft turbine is drivingly connected to a forward fan blade row by the low pressure inner shaft. The low pressure outer shaft turbine is drivingly connected to a aft fan blade row by the low pressure outer shaft. A single direction of rotation booster is drivenly connected to the low pressure outer shaft and axially located aft and downstream of the aft fan blade row.
摘要翻译： 一种燃气涡轮发动机涡轮组件包括具有高压涡轮机的高压阀芯，所述高压涡轮机通过可围绕发动机中心线旋转的高压轴驱动地连接到高压压缩机。 低压涡轮机具有反转可旋转的低压内外涡轮机，其分别驱动地连接到同轴的低压内外轴和外轴，其至少部分地可旋转地设置成与高压阀芯同轴并且径向向内。 低压内轴涡轮机通过低压内轴与前风扇叶片排驱动连接。 低压外轴涡轮机通过低压外轴与后风扇叶片排驱动连接。 单向旋转助力器驱动地连接到低压外轴并且轴向位于后风扇叶片排的后部和下游。
-
26.发明授权Variable torque split aircraft gas turbine engine counter rotating low pressure turbines 有权可变扭矩分裂飞机燃气涡轮发动机反转低压涡轮机公开(公告)号：US06763652B2
公开(公告)日：2004-07-20
申请号：US10253236
申请日：2002-09-24
IPC分类号： F02G106
CPC分类号： F02C3/067 , Y02T50/671
摘要： An aircraft gas turbine engine includes a low pressure turbine having a low pressure turbine flowpath and low pressure inner and outer shaft turbines with counter rotatable low pressure inner and outer shaft turbine rotors, respectively. The low pressure inner and outer shaft turbine rotors include low pressure first and second turbine blade rows disposed across the turbine flowpath which are drivingly connected to first and second fan blade rows by low pressure inner and outer shafts, respectively. At least one row of low pressure variable vanes is operably disposed across the low pressure turbine flowpath between the low pressure inner and outer shaft turbines. The low pressure first turbine blade rows of the low pressure inner shaft turbine may be in tandem with or interdigitated with the second turbine blade rows of the low pressure outer shaft turbines.
摘要翻译： 飞机燃气涡轮发动机包括分别具有低压涡轮流动路径的低压涡轮机和具有反向可旋转的低压内外涡轮转子的低压内外涡轮机。 低压内外涡轮转子包括横跨涡轮流路设置的低压第一和第二涡轮叶片排，它们分别通过低压内轴和外轴驱动地连接到第一和第二风扇叶片排。 至少一排低压可变叶片可操作地设置在低压内外涡轮机之间的低压涡轮流动路径上。 低压内轴涡轮机的低压第一涡轮机叶片排可以与低压外轴涡轮机的第二涡轮叶片排串联或互相指向。
-
公开(公告)号：US06681558B2
公开(公告)日：2004-01-27
申请号：US09817884
申请日：2001-03-26
申请人： Robert Joseph Orlando , Paul Cooker
发明人： Robert Joseph Orlando , Paul Cooker
IPC分类号： F23R300
CPC分类号： F02K1/06 , F01D9/041 , F01D17/162 , F02C9/00 , F05D2270/11
摘要： A method of extending a useful serviceable life of a gas turbine engine by increasing a limiting exhaust gas temperature margin degraded by engine use without replacing engine hardware. The method includes adjusting at least one engine parameter selected from a first group of engine parameters including a nozzle area and a rotor speed.
摘要翻译： 一种通过增加由发动机使用而劣化的限制性排气温度余量而不替换发动机硬件来延长燃气涡轮发动机的有用可用寿命的方法。 该方法包括调整从包括喷嘴区域和转子速度的第一组发动机参数中选择的至少一个发动机参数。
-
公开(公告)号：US5683225A
公开(公告)日：1997-11-04
申请号：US783668
申请日：1991-10-28
CPC分类号： F01D17/14
摘要： A turbine nozzle for a gas turbine engine subassembly having an axial turbine. The turbine nozzle airfoil-shaped vanes are fixedly attached to one or both of the annular inner and outer casings. Apparatus is provided to vary the vane airflow passage area between the casings and between the pressure side of one vane and the suction side of an adjacent vane. The apparatus varies the area near at least the pressure side of the one vane. Various embodiments of the apparatus include: a small pivotable flap pivotally attached to the outer casing and positioned near the pressure side of the one vane; a small movable flap attached to the outer casing to be movable along the pressure side of the one vane, and a plug member insertable into and withdrawable from the vane airflow passage through the outer casing near at least the pressure side of the one vane.
摘要翻译： 一种用于具有轴向涡轮机的燃气涡轮发动机子组件的涡轮喷嘴。 涡轮喷嘴翼型叶片固定地附接到环形内壳和外壳中的一个或两个。 提供设备以改变壳体之间和一个叶片的压力侧与相邻叶片的吸力侧之间的叶片气流通道面积。 该装置改变至少一个叶片的压力侧附近的区域。 该装置的各种实施例包括：可枢转地附接到外壳并且定位在一个叶片的压力侧附近的小的可枢转翼片; 附接到所述外壳的小活动翼可以沿着所述一个叶片的压力侧移动;以及插塞构件，其可插入并可从所述叶片气流通道通过所述外壳至少靠近所述一个叶片的所述压力侧。
-
公开(公告)号：US08205458B2
公开(公告)日：2012-06-26
申请号：US11967479
申请日：2007-12-31
IPC分类号： F01D5/18
CPC分类号： F01D25/12 , F01D9/041 , F05D2260/202 , Y02T50/673 , Y02T50/676
摘要： A duplex turbine nozzle includes a row of different first and second vanes alternating circumferentially between radially outer and inner bands in vane doublets having axial splitlines therebetween. The vanes have opposite pressure and suction sides spaced apart in each doublet to define an inboard flow passage therebetween, and corresponding outboard flow passages between doublets. The vanes have different patterns of film cooling holes with larger cooling flow density along the outboard passages than along the inboard passages.
摘要翻译： 双相涡轮喷嘴包括一排不同的第一和第二叶片，其在叶片双重体的径向外部和内部带之间周向交替，其间具有轴向分裂线。 叶片具有相反的压力和吸力侧面，每个双层间隔开，以在其间限定内侧流动通道，并且在双层之间具有相应的外侧流动通道。 叶片具有不同于薄膜冷却孔的图案，沿着外侧通道具有比沿内侧通道更大的冷却流动密度。
-
30.发明授权公开(公告)号：US08015828B2
公开(公告)日：2011-09-13
申请号：US11695741
申请日：2007-04-03
CPC分类号： F02C7/275 , F02C7/32 , F02C7/36 , Y02T50/671 , Y10T29/49245
摘要： A power take-off system for a gas turbine engine includes a starter coupled to a second spool, and a clutch assembly coupled between the starter and a first spool, the clutch assembly configured to couple the first spool to the starter when starting the gas turbine engine assembly. 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联接到第二阀芯的起动器和联接在起动器和第一阀芯之间的离合器组件，所述离合器组件构造成当启动燃气轮机时将第一阀芯耦合到起动器 发动机总成。 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。
-
-
-
-
-
-
-
-
-
搜索结果
88 条记录 (耗时 0.018 秒)
