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31. 发明申请

US20170152866A1 STATOR VANE SYSTEM USABLE WITHIN A GAS TURBINE ENGINE 审中-公开
公开(公告)号：US20170152866A1
公开(公告)日：2017-06-01
申请号：US15323895
申请日：2014-07-24
申请人： Siemens Aktiengesellschaft
发明人： Elliot Griffin
IPC分类号： F04D29/64 , F04D29/08 , F04D29/54
CPC分类号： F04D29/644 , F01D9/042 , F01D11/001 , F01D11/127 , F01D25/246 , F04D29/083 , F04D29/542 , F05D2230/64 , F05D2260/30 , F05D2300/505
摘要： A stator assembly (10) usable in a gas turbine engine (12) and configured to restrain inner and outer endwalls (14, 16) to limit deflection and prevent clearance loss relative to adjacent blade rotor disks (18) is disclosed. The stator assembly (10) may be formed from a plurality of stator vanes (20) with inner and outer endwalls (14, 16) that are coupled together with a first radially outer tie bar (22). In at least one embodiment, first and second radially outer tie bars (22, 24) may form first and second stator vane segments (26, 28) that together form the circumferentially extending stator assembly (10). The inner and outer endwalls (14, 16) may be coupled together with one or more circumferentially extending alignment pins (30) that limit deflection. The stator assembly (10) may include one more deformable seals (52) extending radially inward from the inner endwall (14).

32. 发明申请

US20170130597A1 SYSTEM AND METHOD FOR REMOVING STATOR VANES FROM A CASING OF A ROTARY MACHINE 有权
公开(公告)号：US20170130597A1
公开(公告)日：2017-05-11
申请号：US15413787
申请日：2017-01-24
申请人： General Electric Company
发明人： Joshua Michael Oden , James Bradford Holmes
IPC分类号： F01D9/04 , B23P19/04
CPC分类号： F01D9/042 , B23P19/00 , B23P19/04 , B25B27/00 , F01D9/02 , F01D25/285 , F05D2230/70
摘要： A stator vane removal system includes a reaction platform configured to couple between opposing sides of a slot defined in an inner surface of a casing of a rotary machine. At least one stator vane is retained in the slot. The reaction platform includes at least one wedge surface. The system also includes an actuator configured to couple to the reaction platform. The at least one wedge surface facilitates inducing a coupling force exerted by the reaction platform to the opposing sides of the slot when the actuator applies a pushing force to the at least one stator vane in the slot.

33. 发明授权

US09611748B2 Stationary airfoils configured to form improved slip joints in bi-cast turbine engine components and the turbine engine components including the same 有权
公开(公告)号：US09611748B2
公开(公告)日：2017-04-04
申请号：US14099218
申请日：2013-12-06
申请人： HONEYWELL INTERNATIONAL INC.
发明人： Harry Lester Kington , Shezan Kanjiyani , Natalie Wali , John Gintert , Bradley R. Tucker
IPC分类号： F01D25/26 , F01D9/04 , B22C9/04 , B22C9/22
CPC分类号： F01D9/042 , B22C9/04 , B22C9/22 , F01D9/041 , F01D25/26 , F05D2230/21 , F05D2300/50212
摘要： Stationary airfoils configured to form an improved slip joint in bi-cast turbine engine components and the turbine engine components including the same are provided. The stationary airfoil for a bi-cast turbine engine component comprises a leading edge and a trailing edge interconnected by a pressure sidewall and a suction sidewall. An end portion is shaped with a pair of opposing flanges to form a slip joint with a shroud ring in the bi-cast turbine engine component and to define an interlocking feature. The slip joint permits radial movement of the stationary airfoil relative to the shroud ring due to thermal differential expansion and contraction.

34. 发明授权

US09567863B2 Assembly fixture for a stator vane assembly 有权
标题翻译：定子叶片组件的装配夹具
公开(公告)号：US09567863B2
公开(公告)日：2017-02-14
申请号：US14568257
申请日：2014-12-12
申请人： United Technologies Corporation
发明人： Michael E. McMahon , Steven J. Feigleson , Dennis R. Tremblay
IPC分类号： F01D9/04 , F01D25/28
CPC分类号： F01D9/042 , F01D25/285 , F05D2230/60 , F05D2240/10 , F05D2240/55 , Y10T29/49234 , Y10T29/49321 , Y10T29/53961 , Y10T29/53991
摘要： A fixture for assembling a stator vane assembly for a gas turbine engine includes, an outer locating ring including a plurality of outer locating pins defining a position for each of a plurality of vanes relative to an outer fairing. An inner locating ring includes a plurality of inner locating rings defining a position of each of the plurality of vanes relative to an inner fairing. A clamp section includes a clamp portion and a clamp pin defining an angular orientation of each of the plurality of vanes relative to each of the inner and outer fairings. An inner locating section supports a plurality of radial locating pins defining a radial position of each of the plurality of vanes relative to the inner and outer fairings.
摘要翻译：用于组装用于燃气涡轮发动机的定子叶片组件的固定装置包括：外定位环，其包括多个外定位销，所述外定位销限定相对于外整流罩的多个叶片中的每一个的位置。内定位环包括多个内定位环，其限定多个叶片中的每一个相对于内部整流罩的位置。夹紧部分包括夹紧部分和夹紧销，所述夹紧销限定所述多个叶片中的每一个相对于所述内部和外部整流罩中的每一个的角度定向。内部定位部分支撑多个径向定位销，其限定多个叶片中的每一个相对于内部和外部整流罩的径向位置。

35. 发明申请

US20170030209A1 STEAM TURBINE NOZZLE SEGMENT HAVING TRANSITIONAL INTERFACE, AND NOZZLE ASSEMBLY AND STEAM TURBINE INCLUDING SUCH NOZZLE SEGMENT 审中-公开
标题翻译：具有过渡接口的蒸汽涡轮喷嘴部分，以及包括这种喷嘴部分的喷嘴组件和蒸汽涡轮机
公开(公告)号：US20170030209A1
公开(公告)日：2017-02-02
申请号：US15290478
申请日：2016-10-11
申请人： General Electric Company
发明人： Steven Sebastian Burdgick
IPC分类号： F01D9/04
CPC分类号： F01D9/041 , F01D9/042 , F05D2220/31 , F05D2240/128 , F05D2250/711 , F05D2250/712 , F05D2250/73
摘要： Various embodiments include steam turbine static nozzles having transitional interfaces. In one embodiment a steam turbine static nozzle blade includes: an airfoil; an inner sidewall integral with a first side of the airfoil; and an outer sidewall integral with a second side of the airfoil; the inner sidewall and the outer sidewall each including: a first side having one of: an arcuate concave surface extending substantially an entire length of the sidewall, or an arcuate convex surface extending substantially the entire length of the sidewall; and a second side opposing the first side and having an angled interface extending substantially the entire length of the sidewall.
摘要翻译：各种实施例包括具有过渡界面的汽轮机静态喷嘴。在一个实施例中，蒸汽轮机静态喷嘴刀片包括：翼型件; 与所述翼型件的第一侧成一体的内侧壁; 以及与所述翼型件的第二侧成一体的外侧壁; 内侧壁和外侧壁各自包括：第一侧，其具有基本上延伸的侧壁的整个长度的弓形凹面或基本上在侧壁的整个长度上延伸的弓形凸面; 以及与所述第一侧相对的第二侧，并具有基本上延伸所述侧壁整个长度的成角度的界面。

36. 发明申请

US20170022842A1 GAS TURBINE ENGINES INCLUDING CHANNEL-COOLED HOOKS FOR RETAINING A PART RELATIVE TO AN ENGINE CASING STRUCTURE 有权
标题翻译：气体涡轮发动机，包括用于保持与发动机结构相关的部件的通道冷却钩
公开(公告)号：US20170022842A1
公开(公告)日：2017-01-26
申请号：US14807703
申请日：2015-07-23
申请人： United Technologies Corporation
发明人： BRANDON W. SPANGLER
IPC分类号： F01D25/12 , F01D25/14
CPC分类号： F01D25/12 , F01D9/042 , F01D25/14 , F01D25/246 , F05D2260/22141
摘要： A gas turbine engine is provided. The gas turbine engine includes an engine casing structure and a part retained relative to the engine casing structure by a channel-cooled hook. The channel-cooled hook includes at least a portion of a hook cooling channel. A vane assembly for the gas turbine engine is also provided.
摘要翻译：提供燃气涡轮发动机。燃气涡轮发动机包括发动机壳体结构和通过通道冷却的钩相对于发动机壳体结构保持的部分。通道冷却的钩包括钩冷却通道的至少一部分。还提供了一种用于燃气涡轮发动机的叶片组件。

37. 发明申请

US20170016341A1 SHROUD ASSEMBLY FOR GAS TURBINE ENGINE 审中-公开
标题翻译：气动涡轮发动机SHROUD装配
公开(公告)号：US20170016341A1
公开(公告)日：2017-01-19
申请号：US14797240
申请日：2015-07-13
申请人： General Electric Company
发明人： David Scott Stapleton , Bryce Loring Heitman , Laura Isabelle Armanios
IPC分类号： F01D11/08 , F01D25/00 , F02C3/04 , F01D9/04
CPC分类号： F01D11/08 , F01D9/04 , F01D9/042 , F01D11/18 , F01D25/005 , F01D25/246 , F02C3/04 , F05D2220/32 , F05D2240/11 , F05D2240/128 , F05D2240/35 , F05D2260/30 , F05D2260/31 , F05D2300/10 , F05D2300/6033 , Y02T50/672
摘要： Shroud assemblies for gas turbine engines are provided. A shroud assembly includes a hanger having a forward hanger arm, a rear hanger arm, and a hanger body extending between the forward hanger arm and the rear hanger arm. The shroud assembly further includes a shroud having a forward surface, a rear surface, and an inner surface and outer surface extending between the forward surface and the rear surface, the outer surface radially spaced from the inner surface, the shroud connected to the hanger. The shroud assembly further includes a support member positioned axially forward of the forward hanger arm, the support member having a radially outer portion connected to the forward hanger arm and a radially inner portion axially spaced from the shroud such that a gap is defined between the radially inner portion and an axially adjacent surface of the shroud.
摘要翻译：提供了用于燃气涡轮发动机的护罩组件。护罩组件包括具有前衣架臂，后衣架臂和在前衣架臂和后衣架臂之间延伸的衣架主体的衣架。护罩组件还包括具有前表面，后表面以及在前表面和后表面之间延伸的内表面和外表面的护罩，外表面与内表面径向间隔开，护罩连接到衣架。所述护罩组件还包括位于所述前悬挂臂的轴向前方的支撑构件，所述支撑构件具有连接到所述前悬挂臂的径向外部，以及与所述护罩轴向间隔开的径向内部，使得在径向内部部分和护罩的轴向相邻表面。

38. 发明授权

US09506361B2 Low profile vane retention 有权
标题翻译：薄型叶片保持力
公开(公告)号：US09506361B2
公开(公告)日：2016-11-29
申请号：US13789756
申请日：2013-03-08
申请人： PRATT & WHITNEY CANADA CORP.
发明人： Bruce Fielding , Nathan Tomes , Thomas Veitch
IPC分类号： F01D9/04 , F01D25/24
CPC分类号： F01D9/041 , F01D9/042 , F01D25/246 , F05D2260/12 , Y10T29/4995
摘要： A gas turbine having an annular casing with a series of circumferentially spaced openings defined therethrough; a plurality of vanes extending radially inwardly though respective casing openings, an outer end of the vanes projecting radially outwardly from the casing through the respective openings and located within the respective openings by grommets, and an inner end of the vanes being mounted to an inner portion of the casing; a flexible, segmented strap extending around the annular casing, surrounding the projecting outer ends of the vanes; and a spring radially loading the flexible strap configured to apply a tension force to the flexible strap.
摘要翻译：一种燃气轮机，其具有环形壳体，其具有通过其限定的一系列周向间隔开的开口; 多个叶片径向向内延伸穿过相应的壳体开口，叶片的外端通过相应的开口从壳体径向向外突出并且通过索环位于相应的开口内，并且叶片的内端安装到内部的套管围绕所述环形壳体延伸的柔性分段带，围绕所述叶片的突出的外端; 并且弹簧径向地加载被配置为向柔性带施加张力的柔性带。

39. 发明申请

US20160341068A1 FIXED-VARIABLE VANE WITH POTTING IN GAP 审中-公开
标题翻译：固定不变的风扇，带有凹槽
公开(公告)号：US20160341068A1
公开(公告)日：2016-11-24
申请号：US14880519
申请日：2015-10-12
申请人： United Technologies Corporation
发明人： Thomas J. Robertson, JR. , Enzo DiBenedetto , Nathan F. Champion , Niloofar Haghbin , Barry William Spaulding, III
IPC分类号： F01D17/14 , F01D9/04
CPC分类号： F01D17/14 , F01D9/041 , F01D9/042 , F01D17/162 , F04D29/563 , F04D29/644 , F05D2220/32 , F05D2230/30 , F05D2230/60 , F05D2230/644 , F05D2240/80 , F05D2260/30
摘要： A fixed-variable vane assembly includes a vane that has a fixed airfoil section and a variable airfoil section next to the fixed airfoil section. The variable airfoil section is pivotably mounted at an end thereof in a joint with a variable joint gap that controls a size of an airfoil gap between the fixed airfoil section and the variable airfoil section. A potting material is located in the variable joint gap. The potting material locks the variable joint gap and locks in the size of the airfoil gap.
摘要翻译：固定式叶片组件包括具有固定翼型部分和与固定翼型部分相邻的可变翼型部分的叶片。可变翼型部分在其端部可枢转地安装在具有可变接头间隙的接头中，该可变接缝间隙控制固定翼型部分和可变翼型部分之间的翼型间隙的尺寸。灌封材料位于可变接缝间隙中。灌封材料锁定可变接缝间隙并锁定翼型间隙的尺寸。

40. 发明申请

US20160333890A1 GAS TURBINE ENGINE INNER CASE WITH NON-INTEGRAL VANES 审中-公开
标题翻译：气体涡轮发动机内箱与非集成空气
公开(公告)号：US20160333890A1
公开(公告)日：2016-11-17
申请号：US15110856
申请日：2014-12-26
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Richard K. Hayford , Mark J. Rogers , Carl S. Richardson , Jonathan J. Earl
IPC分类号： F04D29/54 , F04D29/52 , F04D29/64
CPC分类号： F04D29/542 , F01D9/042 , F04D29/023 , F04D29/522 , F04D29/644 , F05B2220/302 , F05B2240/124 , F05B2280/10743 , F05B2280/50032 , F05D2220/3219 , F05D2230/642 , F05D2240/129 , F05D2300/177 , F05D2300/50212
摘要： A gas turbine engine includes a circumferential array of vanes slidably supported in an inner case shroud segment. Multiple segments are secured to one another to provide an annular engine static structure section. The inner case shroud segment and the vanes have different material properties than one another.
摘要翻译：燃气涡轮发动机包括可滑动地支撑在内壳体护罩段中的周向阵列的叶片。多个段彼此固定以提供环形发动机静态结构部分。内壳护罩段和叶片具有彼此不同的材料性质。

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