公开(公告)号：US08939727B2

公开(公告)日：2015-01-27

申请号：US13227603

申请日：2011-09-08

申请人： Christian X. Campbell ,  Darryl Eng ,  John J. Marra

发明人： Christian X. Campbell ,  Darryl Eng ,  John J. Marra

IPC分类号： F01D5/30 ,  F01D11/00

CPC分类号： F01D11/008 ,  F01D5/3007

摘要： Platforms (36, 38) span between turbine blades (23, 24, 25) on a disk (32). Each platform may be individually mounted to the disk by a pin attachment (42). Each platform (36) may have a rotationally rearward edge portion (50) that underlies a forward portion (45) of the adjacent platform (38). This limits centrifugal bending of the rearward portion of the platform, and provides coolant sealing. The rotationally forward edge (44A, 44B) of the platform overlies a seal element (51) on the pressure side (28) of the forwardly adjacent blade, and does not underlie a shelf on that blade. The pin attachment allows radial mounting of each platform onto the disk via tilting (60) of the platform during mounting to provide mounting clearance for the rotationally rearward edge portion (50). This facilitates quick platform replacement without blade removal.

摘要翻译： 平台（36,38）跨越盘（32）上的涡轮叶片（23,24,25）之间。 每个平台可以通过销附件（42）单独地安装到盘上。 每个平台（36）可以具有在相邻平台（38）的前部（45）下面的旋转后边缘部分（50）。 这限制了平台后部的离心弯曲，并提供冷却剂密封。 平台的旋转前缘（44A，44B）覆盖在前方相邻叶片的压力侧（28）上的密封元件（51）上，并且不位于该刀片上的搁板的下面。 销安装件允许在安装期间通过平台的倾斜（60）将每个平台径向地安装到盘上，以为旋转后边缘部分（50）提供安装间隙。 这有助于快速平台更换，而无需拆卸刀片。

公开(公告)号：US20150003973A1

公开(公告)日：2015-01-01

申请号：US13930482

申请日：2013-06-28

申请人： Ching-Pang Lee ,  Kok-Mun Tham ,  Eric Schroeder ,  Jamie Meeroff ,  Samuel R. Miller, Jr. ,  John J. Marra ,  Christian X. Campbell

发明人： Ching-Pang Lee ,  Kok-Mun Tham ,  Eric Schroeder ,  Jamie Meeroff ,  Samuel R. Miller, Jr. ,  John J. Marra ,  Christian X. Campbell

IPC分类号： F01D11/02 ,  F01D5/18

CPC分类号： F01D11/02 ,  F01D5/082 ,  F01D5/18 ,  F01D5/187 ,  F01D11/04 ,  F05D2260/14

摘要： An outer rim seal arrangement (10), including: an annular rim (70) centered about a longitudinal axis (30) of a rotor disc (31), extending fore and having a fore-end (72), an outward-facing surface (74), and an inward-facing surface (76); a lower angel wing (62) extending aft from a base of a turbine blade (22) and having an aft end (64) disposed radially inward of the rim inward-facing surface to define a lower angel wing seal gap (80); an upper angel wing (66) extending aft from the turbine blade base and having an aft end (68) disposed radially outward of the rim outward-facing surface to define a upper angel wing seal gap (80, 82); and guide vanes (100) disposed on the rim inward-facing surface in the lower angel wing seal gap. Pumping fins (102) may be disposed on the upper angel wing seal aft end in the upper angel wing seal gap.

摘要翻译： 外缘密封装置（10），包括：以转子盘（31）的纵向轴线（30）为中心的环形边缘（70），其在前面延伸并具有前端（72），面向外的表面 （74）和面向内的表面（76）; 从天线叶片（22）的底部向后延伸的下部天使翼（62），并且具有设置在所述边缘向内相对表面的径向内侧的后端（64），以限定下部天使翼密封间隙（80）; 从所述涡轮叶片基部向后延伸的上天使翼（66），并且具有设置在所述轮缘朝外的表面的径向外侧的后端（68），以限定上天使翼密封间隙（80,82）; 以及设置在下天使翼密封间隙中的边缘向内表面上的导向叶片（100）。 抽吸翼（102）可以设置在上天使翼密封间隙中的上天使翼密封后端。

公开(公告)号：US08579593B2

公开(公告)日：2013-11-12

申请号：US12613957

申请日：2009-11-06

申请人： Christian X. Campbell ,  John J. Marra

发明人： Christian X. Campbell ,  John J. Marra

IPC分类号： F01D5/14 ,  F01D5/16 ,  F01D5/18

CPC分类号： F01D5/16 ,  F05D2260/20 ,  F05D2300/21 ,  F05D2300/603

摘要： An airfoil (10) is provided with a tip (12) having an opening (14) to a center channel (24). A damping element (16) is inserted within the opening of the center channel, to reduce an induced vibration of the airfoil. The mass of the damping element, a spring constant of the damping element within the center channel, and/or a mounting location (58) of the damping element within the center channel may be adjustably varied, to shift a resonance frequency of the airfoil outside a natural operating frequency of the airfoil.

摘要翻译： 机翼（10）设置有具有到中心通道（24）的开口（14）的尖端（12）。 阻尼元件（16）插入在中心通道的开口内，以减少翼型的感应振动。 缓冲元件的质量，中心通道内的阻尼元件的弹簧常数和/或中心通道内的阻尼元件的安装位置（58）可以可调地变化，以使翼型件的共振频率向外移动 机翼的自然工作频率。

公开(公告)号：US08485787B2

公开(公告)日：2013-07-16

申请号：US12555096

申请日：2009-09-08

申请人： John J. Marra

发明人： John J. Marra

IPC分类号： F01D5/14

CPC分类号： B23P15/04 ,  B21C23/085 ,  B21C25/08 ,  B21C37/18 ,  B21J5/08 ,  B21K3/04 ,  B23K1/0018 ,  B23K20/023 ,  B23K20/233 ,  B23K31/022 ,  B23K33/004 ,  B23K2101/001 ,  B23P13/04 ,  F01D5/147 ,  F01D5/187 ,  F05D2230/236 ,  F05D2230/237 ,  Y10T29/49339

摘要： An airfoil (30) and fabrication process for turbine blades with cooling channels (26). Tapered tubes (32A-32D) are bonded together in a parallel sequence, forming a leading edge (21), a trailing edge (22), and pressure and suction side walls (23, 24) connected by internal ribs (25). The tapered tubes may be extruded without camber to simplify the extrusion process, then bonded along matching surfaces (34), forming a non-cambered airfoil (28), which may be cambered in a hot forming process and cut (48) to length. The tubes may have tapered walls that are thinner at the blade tip (T1) than at the base (T2), reducing mass. A cap (50) may be attached to the blade tip. A mounting lug (58) may be forged (60) on the airfoil base and then machined, completing the blade for mounting in a turbine rotor disk.

摘要翻译： 一种用于具有冷却通道（26）的涡轮叶片的翼型件（30）和制造方法。 锥形管（32A-32D）以平行顺序结合在一起，形成前缘（21），后缘（22）以及通过内肋（25）连接的压力和吸力侧壁（23,24）。 锥形管可以没有弯曲的挤压而简化挤出过程，然后沿着匹配的表面（34）粘合，形成非弧形翼型件（28），其可以在热成形过程中被弯曲并切割成长度。 管可以具有在叶片尖端（T1）处比在基部（T2）处更薄的锥形壁，从而减小质量。 盖（50）可以附接到叶片尖端。 安装凸耳（58）可以在翼型基础上锻造（60）然后被机加工，从而完成叶片以安装在涡轮转子盘中。

公开(公告)号：US20130156579A1

公开(公告)日：2013-06-20

申请号：US13766909

申请日：2013-02-14

申请人： Ching-Pang Lee ,  Kok-Mun Tham ,  Eric Schroeder ,  Jamie Meeroff ,  Samuel R. Miller, JR. ,  John J. Marra

发明人： Ching-Pang Lee ,  Kok-Mun Tham ,  Eric Schroeder ,  Jamie Meeroff ,  Samuel R. Miller, JR. ,  John J. Marra

IPC分类号： F01D5/18 ,  F01D25/12

CPC分类号： F01D5/187 ,  F01D5/082 ,  F01D5/143 ,  F01D9/065 ,  F01D11/001 ,  F01D25/12 ,  F02C7/12 ,  F05D2240/127

摘要： A gas turbine engine including: an ambient-air cooling circuit (10) having a cooling channel (26) disposed in a turbine blade (22) and in fluid communication with a source (12) of ambient air: and an pre-swirler (18), the pre-swirler having: an inner shroud (38); an outer shroud (56); and a plurality of guide vanes (42), each spanning from the inner shroud to the outer shroud. Circumferentially adjacent guide vanes (46, 48) define respective nozzles (44) there between. Forces created by a rotation of the turbine blade motivate ambient air through the cooling circuit. The pre-swirler is configured to impart swirl to ambient air drawn through the nozzles and to direct the swirled ambient air toward a base of the turbine blade. The end walls (50, 54) of the pre-swirler may be contoured.

摘要翻译： 一种燃气涡轮发动机，包括：环境空气冷却回路（10），其具有设置在涡轮机叶片（22）中并与环境空气源（12）流体连通的冷却通道（26）;以及预旋流器 18），所述预旋转器具有：内罩（38）; 外护罩（56）; 以及多个导向叶片（42），每个导向叶片从内护罩跨越到外护罩。 周向相邻的导向叶片（46,48）在其间限定相应的喷嘴（44）。 通过涡轮叶片的旋转产生的力通过冷却回路激励环境空气。 预旋流器被配置为对通过喷嘴抽吸的环境空气赋予涡流，并且将旋转的环境空气引导到涡轮叶片的基部。 预旋转器的端壁（50,54）可以是轮廓。

公开(公告)号：US20120269647A1

公开(公告)日：2012-10-25

申请号：US13090294

申请日：2011-04-20

申请人： Paul H. Vitt ,  David A. Kemp ,  Ching-Pang Lee ,  John J. Marra

发明人： Paul H. Vitt ,  David A. Kemp ,  Ching-Pang Lee ,  John J. Marra

IPC分类号： F01D5/18

CPC分类号： F01D5/186 ,  F01D5/188 ,  F05D2250/30 ,  F05D2260/221 ,  F05D2260/941

摘要： An airfoil in a gas turbine engine includes an outer wall and an inner wall. The outer wall includes a leading edge, a trailing edge opposed from the leading edge in a chordal direction, a pressure side, and a suction side. The inner wall is coupled to the outer wall at a single chordal location and includes portions spaced from the pressure and suction sides of the outer wall so as to form first and second gaps between the inner wall and the respective pressure and suction sides. The inner wall defines a chamber therein and includes openings that provide fluid communication between the respective gaps and the chamber. The gaps receive cooling fluid that provides cooling to the outer wall as it flows through the gaps. The cooling fluid, after traversing at least substantial portions of the gaps, passes into the chamber through the openings in the inner wall.

摘要翻译： 燃气涡轮发动机中的翼型件包括外壁和内壁。 外壁包括前缘，从前缘朝向方向相对的后缘，压力侧和吸力侧。 内壁在单个弦位置处联接到外壁，并且包括与外壁的压力和吸力侧隔开的部分，以便在内壁和相应的压力和吸力侧之间形成第一和第二间隙。 内壁在其中限定一个室，并且包括在相应间隙和室之间提供流体连通的开口。 间隙接收冷却流体，当其流过间隙时，向外壁提供冷却。 冷却流体在穿过至少大部分间隙之后通过内壁中的开口进入腔室。

公开(公告)号：US20110194939A1

公开(公告)日：2011-08-11

申请号：US12701041

申请日：2010-02-05

申请人： John J. Marra

发明人： John J. Marra

IPC分类号： F01D5/22 ,  B23P11/00

CPC分类号： F01D5/187 ,  F01D5/22 ,  F01D5/26 ,  F05D2260/221 ,  F05D2260/96

摘要： A snubber associated with a rotatable turbine blade in a turbine engine, the turbine blade including a pressure sidewall and a suction sidewall opposed from the pressure wall. The snubber assembly includes a first snubber structure associated with the pressure sidewall of the turbine blade, a second snubber structure associated with the suction sidewall of the turbine blade, and a support structure. The support structure extends through the blade and is rigidly coupled at a first end portion thereof to the first snubber structure and at a second end portion thereof to the second snubber structure. Centrifugal loads exerted by the first and second snubber structures caused by rotation thereof during operation of the engine are at least partially transferred to the support structure, such that centrifugal loads exerted on the pressure and suctions sidewalls of the turbine blade by the first and second snubber structures are reduced.

摘要翻译： 与涡轮发动机中的可旋转涡轮叶片相关联的缓冲器，涡轮机叶片包括压力侧壁和与压力壁相对的吸力侧壁。 缓冲组件包括与涡轮叶片的压力侧壁相关联的第一缓冲结构，与涡轮叶片的抽吸侧壁相关联的第二缓冲结构和支撑结构。 支撑结构延伸穿过叶片并且在其第一端部处刚性耦合到第一缓冲结构，并且在其第二端部处紧固到第二缓冲结构。 由第一和第二缓冲结构施加的由第一和第二缓冲结构施加的离心载荷至少部分地传递到支撑结构，从而使得施加在压力上的离心载荷由第一和第二缓冲器吸附在涡轮叶片的侧壁 结构减少。

公开(公告)号：US09822662B2

公开(公告)日：2017-11-21

申请号：US14075140

申请日：2013-11-08

申请人： Jan H. Marsh ,  John J. Marra

发明人： Jan H. Marsh ,  John J. Marra

IPC分类号： F01D25/12 ,  F02C6/08 ,  F02C7/12 ,  F02C7/18

CPC分类号： F01D25/12 ,  F02C6/08 ,  F02C7/12 ,  F02C7/185 ,  F05D2220/3215 ,  F05D2260/601

摘要： A cooling system for a turbine engine for directing cooling fluids from a compressor to a turbine blade cooling fluid supply and from an ambient air source to the turbine blade cooling fluid supply to supply cooling fluids to one or more airfoils of a rotor assembly is disclosed. The cooling system may include a compressor bleed conduit extending from a compressor to the turbine blade cooling fluid supply that provides cooling fluid to at least one turbine blade. The compressor bleed conduit may include an upstream section and a downstream section whereby the upstream section exhausts compressed bleed air through an outlet into the downstream section through which ambient air passes. The outlet of the upstream section may be generally aligned with a flow of ambient air flowing in the downstream section. As such, the compressed air increases the flow of ambient air to the turbine blade cooling fluid supply.

公开(公告)号：US09726028B2

公开(公告)日：2017-08-08

申请号：US13171699

申请日：2011-06-29

申请人： John J. Marra ,  Brian J. Wessell ,  Allister W. James ,  Jan H. Marsh ,  Paul J. Gear

发明人： John J. Marra ,  Brian J. Wessell ,  Allister W. James ,  Jan H. Marsh ,  Paul J. Gear

IPC分类号： F01D9/04 ,  F01D11/00 ,  B22D19/00 ,  B22D19/04

CPC分类号： F01D9/042 ,  B22D19/0072 ,  B22D19/04 ,  F01D11/006 ,  F05D2300/10 ,  F05D2300/506 ,  F05D2300/518 ,  Y10T29/49323

摘要： A vane assembly (10) having: an airfoil (12) and a shroud (14) held together without metallurgical bonding there between; a channel (22) disposed circumferentially about the airfoil (12), between the airfoil (12) and the shroud (14); and a seal (20) disposed in the channel (22), wherein during operation of a turbine engine having the vane assembly (10) the seal (20) has a sufficient ductility such that a force generated on the seal (20) resulting from relative movement of the airfoil (12) and the shroud (14) is sufficient to plastically deform the seal (20).

公开(公告)号：US09359902B2

公开(公告)日：2016-06-07

申请号：US13930479

申请日：2013-06-28

申请人： Christian X. Campbell, Jr. ,  John J. Marra ,  Jan H. Marsh

发明人： Christian X. Campbell, Jr. ,  John J. Marra ,  Jan H. Marsh

IPC分类号： F01D5/18

CPC分类号： F01D5/187 ,  F01D5/186 ,  F05D2260/22141

摘要： A turbine airfoil usable in a turbine engine and having at least one ambient air cooling system is disclosed. At least a portion of the cooling system may include one or more cooling channels configured to receive ambient air at about atmospheric pressure. The ambient air cooling system may have a tip static pressure to ambient pressure ratio of at least 0.5, and in at least one embodiment, may include a tip static pressure to ambient pressure ratio of between about 0.5 and about 3.0. The cooling system may also be configured such that an under root slot chamber in the root is large to minimize supply air velocity. One or more cooling channels of the ambient air cooling system may terminate at an outlet at the tip such that the outlet is aligned with inner surfaces forming the at least one cooling channel in the airfoil to facilitate high mass flow.

摘要翻译： 公开了一种可用于涡轮发动机并具有至少一个环境空气冷却系统的涡轮机翼型。 冷却系统的至少一部分可以包括一个或多个冷却通道，其构造成在约大气压下接收环境空气。 环境空气冷却系统可以具有至少0.5的环境压力比的尖端静态压力，并且在至少一个实施例中，可以包括约0.5至约3.0的尖端静压力至环境压力比。 冷却系统还可以被配置成使得根部的根下槽室较大以最小化供应空气速度。 环境空气冷却系统的一个或多个冷却通道可以终止在尖端处的出口处，使得出口与形成翼型中的至少一个冷却通道的内表面对准以便于高质量流动。