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1. 发明申请

US20120034097A1 COMPONENT WITH INSPECTION-FACILITATING FEATURES 有权
标题翻译：具有检查功能的组件
公开(公告)号：US20120034097A1
公开(公告)日：2012-02-09
申请号：US12850147
申请日：2010-08-04
申请人： John J. Marra , Paul J. Zombo
发明人： John J. Marra , Paul J. Zombo
IPC分类号： F01D5/14 , G01M15/14
CPC分类号： F01D5/141 , B22C9/04 , B22C9/10 , F01D5/147 , F01D21/003 , F05D2250/182
摘要： A turbine airfoil can be formed with features to facilitate measurement of its wall thickness. An outer wall of the airfoil can include an outer surface and an inner surface. The outer surface of the airfoil can have an outer inspection target surface, and the inner surface of the airfoil can have an inner inspection target surface. The inner and outer target surfaces can define substantially flat regions in surfaces that are otherwise highly contoured. The inner and outer inspection target surfaces can be substantially aligned with each other. The inner and outer target surfaces can be substantially parallel to each other. As a result of these arrangements, a highly accurate measurement of wall thickness can be obtained. In one embodiment, the outer inspection target surface can be defined by an innermost surface of a groove formed in the outer surface of the outer wall of the airfoil.
摘要翻译：涡轮机翼型可以形成有特征以便于测量其壁厚。翼型件的外壁可以包括外表面和内表面。翼型件的外表面可以具有外部检查目标表面，并且翼型件的内表面可以具有内部检查目标表面。内外目标表面可以在表面上限定基本上平坦的区域，否则高度轮廓。内部和外部检查目标表面可以基本上彼此对准。内外目标表面可以基本上彼此平行。作为这些布置的结果，可以获得高精度的壁厚测量。在一个实施例中，外部检查目标表面可以由形成在翼型件的外壁的外表面中的凹槽的最内表面限定。

2. 发明授权

US08646511B2 Component with inspection-facilitating features 有权
标题翻译：具有检查功能的组件
公开(公告)号：US08646511B2
公开(公告)日：2014-02-11
申请号：US12850147
申请日：2010-08-04
申请人： John J. Marra , Paul J. Zombo
发明人： John J. Marra , Paul J. Zombo
IPC分类号： B22D46/00 , F01D5/14
CPC分类号： F01D5/141 , B22C9/04 , B22C9/10 , F01D5/147 , F01D21/003 , F05D2250/182
摘要： A turbine airfoil can be formed with features to facilitate measurement of its wall thickness. An outer wall of the airfoil can include an outer surface and an inner surface. The outer surface of the airfoil can have an outer inspection target surface, and the inner surface of the airfoil can have an inner inspection target surface. The inner and outer target surfaces can define substantially flat regions in surfaces that are otherwise highly contoured. The inner and outer inspection target surfaces can be substantially aligned with each other. The inner and outer target surfaces can be substantially parallel to each other. As a result of these arrangements, a highly accurate measurement of wall thickness can be obtained. In one embodiment, the outer inspection target surface can be defined by an innermost surface of a groove formed in the outer surface of the outer wall of the airfoil.
摘要翻译：涡轮机翼型可以形成有特征以便于测量其壁厚。翼型件的外壁可以包括外表面和内表面。翼型件的外表面可以具有外部检查目标表面，并且翼型件的内表面可以具有内部检查目标表面。内外目标表面可以在表面上限定基本上平坦的区域，否则高度轮廓。内部和外部检查目标表面可以基本上彼此对准。内外目标表面可以基本上彼此平行。作为这些布置的结果，可以获得高精度的壁厚测量。在一个实施例中，外部检查目标表面可以由形成在翼型件的外壁的外表面中的凹槽的最内表面限定。

3. 发明授权

US08939727B2 Turbine blade and non-integral platform with pin attachment 有权
标题翻译：涡轮叶片和非固定平台，带有针脚附件
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。

4. 发明申请

US20150003973A1 AFT OUTER RIM SEAL ARRANGEMENT 有权
标题翻译： AFT外部RIM密封安排
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。

5. 发明授权

US08579593B2 Damping element for reducing the vibration of an airfoil 失效
标题翻译：用于减小翼型振动的阻尼元件
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。

6. 发明授权

US08485787B2 Turbine airfoil fabricated from tapered extrusions 失效
标题翻译：涡轮翼型由锥形挤压制成
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。

7. 发明申请

US20130156579A1 AMBIENT AIR COOLING ARRANGEMENT HAVING A PRE-SWIRLER FOR GAS TURBINE ENGINE BLADE COOLING 有权
标题翻译：具有用于气体涡轮发动机叶片冷却器的预吹扫器的环境空气冷却装置
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。

8. 发明申请

US20120269647A1 COOLED AIRFOIL IN A TURBINE ENGINE 有权
标题翻译：涡轮发动机冷却空气
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。

9. 发明申请

US20110194939A1 Snubber Assembly for Turbine Blades 失效
标题翻译：涡轮叶片缓冲组件
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。

10. 发明授权

US09822662B2 Cooling system with compressor bleed and ambient air for gas turbine engine 有权
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.

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