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41. 发明申请

US20160201476A1 AIRFOIL FOR A TURBINE ENGINE 审中-公开
标题翻译：涡轮发动机
公开(公告)号：US20160201476A1
公开(公告)日：2016-07-14
申请号：US14882551
申请日：2015-10-14
申请人： General Electric Company
发明人： Ronald Scott BUNKER , Robert Frederick BERGHOLZ , Robert David BRIGGS , Kevin Robert FELDMANN
IPC分类号： F01D5/18 , F01D25/12 , F01D9/04
CPC分类号： F01D5/187 , F01D5/18 , F01D5/186 , F01D9/041 , F01D25/12 , F05D2220/32 , F05D2240/128 , F05D2250/22 , F05D2250/294 , F05D2250/60 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/676
摘要： An airfoil for a turbine engine includes a cooling cavity and a cooling fluid supply cavity which supplies cooling fluid to the cooling cavity through a passage. The cooling cavity can be provided with a swirl feature for imparting a swirling motion to the cooling fluid.
摘要翻译：用于涡轮发动机的翼型件包括冷却腔和冷却流体供应腔，其通过通道将冷却流体供应到冷却腔。冷却腔可以设置有用于向冷却流体施加旋转运动的旋流特征。

42. 发明申请

US20160097286A1 INTERNAL COOLING OF ENGINE COMPONENTS 有权
标题翻译：发动机部件的内部冷却
公开(公告)号：US20160097286A1
公开(公告)日：2016-04-07
申请号：US14846284
申请日：2015-09-04
申请人： ROLLS-ROYCE PLC
发明人： Ian TIBBOTT , Peter Thomas IRELAND , Anthony John RAWLINSON , Irene CRESCI
IPC分类号： F01D5/18 , F01D9/06
CPC分类号： F01D5/188 , F01D5/189 , F01D9/041 , F01D9/065 , F05D2240/126 , F05D2240/127 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/673 , Y02T50/676
摘要： A gas turbine engine component, especially an aerofoil-sectioned nozzle guide vane (NGV), having at least one internal cooling chamber for passage of cooling air, the chamber including leading edge portion and one inlet portion via which cooling air may enter the chamber from feed source, wherein the component includes a partitioning element, e.g. curved or scoop-shaped partitioning plate or wall, provided in the chamber inlet portion and defining within the inlet portion a sub-chamber adjacent the leading edge portion, and wherein partitioning element is configured so the cooling air velocity in the sub-chamber is less than the cooling air velocity in the remainder of inlet portion. The reduced velocity of the cooling air in the sub-chamber adjacent the leading edge serves to increase pressure therein, thereby maintaining desired backflow pressure margin between the feed pressure of the cooling air delivered to the showerhead holes and the gas-path from the combustor.
摘要翻译：一种燃气涡轮发动机部件，特别是翼型截面喷嘴引导叶片（NGV），其具有用于冷却空气通过的至少一个内部冷却室，所述内部冷却室包括前缘部分和一个入口部分，冷却空气可通过该入口部分从冷却空气进入室进料源，其中所述组件包括分隔元件，例如弯曲或铲形的分隔板或壁，设置在室入口部分中，并且在入口部分内限定与前缘部分相邻的子室，并且其中分隔元件被构造成使得子室中的冷却空气速度较小比进口部分的剩余部分中的冷却风速快。靠近前缘的副室中的冷却空气的减小的速度用于增加其中的压力，从而在输送到喷头孔的冷却空气的进料压力和来自燃烧器的气体路径之间保持期望的回流压力裕度。

43. 发明授权

US09279331B2 Gas turbine engine airfoil with dirt purge feature and core for making same 有权
标题翻译：带有污垢清除功能的燃气涡轮发动机翼型和制造相同的核心
公开(公告)号：US09279331B2
公开(公告)日：2016-03-08
申请号：US13453137
申请日：2012-04-23
申请人： Jeffrey R. Levine , Jeffrey S. Beattie
发明人： Jeffrey R. Levine , Jeffrey S. Beattie
IPC分类号： F01D5/18
CPC分类号： F01D5/188 , B22C9/103 , B22C9/108 , F01D5/187 , F05D2200/33 , F05D2230/211 , F05D2260/22141 , F05D2260/607 , F05D2300/13 , Y02E10/721
摘要： An airfoil includes a body. The body includes leading and trailing edges adjoining pressure and suction sides to provide an exterior airfoil surface. First and second cooling passages extend in a radial direction from a root to a tip. The first cooling passage includes a tip flag passage that is radially inboard from the tip and extends in a chord-wise direction to a first end that penetrates the trailing edge. The second cooling passage includes a second end terminates adjacent the tip flag passage and a dirt purge passage interconnects the second end to the tip flag passage. A core for making the airfoil is also disclosed.
摘要翻译：机翼包括一个机身。主体包括邻近压力和吸力侧的前缘和后缘，以提供外部翼型表面。第一和第二冷却通道在径向方向上从根部延伸到尖端。第一冷却通道包括从顶端径向插入的尖端标记通道，并且沿着弦向延伸到穿过后缘的第一端。第二冷却通道包括邻近末端标记通道终止的第二端，并且污物清除通道将第二端与尖端标记通道相互连接。还公开了制造翼型的核心。

44. 发明授权

US09273632B2 Heat exchanger for aircraft engine 有权
标题翻译：飞机发动机换热器
公开(公告)号：US09273632B2
公开(公告)日：2016-03-01
申请号：US14243769
申请日：2014-04-02
申请人： SUMITOMO PRECISION PRODUCTS CO., LTD.
发明人： Tatsuya Ueda
IPC分类号： B60H3/00 , F02K3/115 , F02C7/14 , F28F3/02 , F28D1/03 , F28F3/12 , F28F27/02 , F28D21/00
CPC分类号： F02K3/115 , F02C7/14 , F05D2230/237 , F05D2250/232 , F05D2250/61 , F05D2250/71 , F05D2260/213 , F05D2260/22141 , F05D2260/606 , F05D2260/98 , F28D1/035 , F28D2021/0021 , F28D2021/0049 , F28F3/02 , F28F3/025 , F28F3/12 , F28F27/02 , F28F2250/06 , Y02T50/671 , Y02T50/675
摘要： A heat exchanger for an aircraft engine includes: a body including a plate-like first member and a plate-like second member that are stacked in a thickness direction of the first and second members and joined together, and a channel which is defined in the body and in which the cooling target fluid flows; and a corrugated fin plate disposed in the channel in the body. The body is bent along a curved surface to which the heat exchanger is attached. A plurality of heat dissipation fins stand on an outer surface of at least one of the first member or the second member.
摘要翻译：一种用于飞行器发动机的热交换器包括：主体，包括板状第一构件和板状第二构件，该第一构件和第二构件沿第一和第二构件的厚度方向堆叠并接合在一起，并且限定在身体，其中冷却目标流体流动; 以及设置在身体的通道中的波纹状翅板。主体沿着热交换器连接的曲面弯曲。多个散热翅片位于第一构件或第二构件中的至少一个的外表面上。

45. 发明申请

US20160047271A1 DUCTING PLATFORM COVER PLATE 有权
标题翻译：导电平板盖板
公开(公告)号：US20160047271A1
公开(公告)日：2016-02-18
申请号：US14924369
申请日：2015-10-27
申请人： United Technologies Corporation
发明人： Pedro L. Castaneda , Edward F. Pietraszkiewicz , Rafael A. Perez , Nestor A. Alvarez , Seth J. Thomen
IPC分类号： F01D25/12 , F01D9/04
CPC分类号： F01D25/12 , F01D9/041 , F01D9/065 , F05D2220/30 , F05D2240/81 , F05D2260/20 , F05D2260/202 , F05D2260/205 , F05D2260/22141 , Y02T50/676
摘要： The present disclosure relates to cooling systems for turbine stators. A stator may include a vane platform. A ducting plate may be coupled to the vane platform. The ducting plate and the vane platform may form a cooling chamber between the ducting plate and the vane platform. The ducting plate may include an inlet adjacent to a leading edge of the vane platform. The vane platform may include an outlet adjacent to a trailing edge of the vane platform. The ducting plate may be configured to channel cooling air through the cooling chamber from the leading edge to the trailing edge.
摘要翻译：本公开涉及涡轮定子的冷却系统。定子可以包括叶片平台。管道板可以联接到叶片平台。导管板和叶片平台可以在管道板和叶片平台之间形成冷却室。导管板可以包括与叶片平台的前缘相邻的入口。叶片平台可以包括与叶片平台的后缘相邻的出口。导管板可以被配置成将冷却空气从前缘引导到后缘。

46. 发明申请

US20160024936A1 LOW PRESSURE LOSS COOLED BLADE 有权
标题翻译：低压冷却叶片
公开(公告)号：US20160024936A1
公开(公告)日：2016-01-28
申请号：US14774566
申请日：2014-03-11
申请人： United Technologies Corporation
发明人： Christopher Corcoran , Jamie G. Ghigliotty , Rafael A. Perez , Edward F. Pietraszkiewicz
IPC分类号： F01D5/18
CPC分类号： F01D5/186 , F01D5/187 , F05D2220/32 , F05D2240/30 , F05D2260/202 , F05D2260/22141 , Y02T50/676
摘要： A rotor blade comprises a root section, an airfoil section, a leading edge cooling cavity, an intermediate cooling cavity, and a trailing edge cooling cavity. The leading edge, intermediate, and trailing edge cooling cavities each extend spanwise through the airfoil section from a coolant inlet passage in the root section, and each terminate proximate the airfoil tip.
摘要翻译：转子叶片包括根部，翼型部分，前缘冷却腔，中间冷却腔和后缘冷却腔。前缘，中间和后缘冷却空腔各自从根部中的冷却剂入口通道翼展方向穿过翼型部分，并且各自终止于翼型末端附近。

47. 发明申请

US20160017806A1 GAS TURBINE ENGINE COMPONENT HAVING SHAPED PEDESTALS 审中-公开
标题翻译：具有形状垫片的气体涡轮发动机部件
公开(公告)号：US20160017806A1
公开(公告)日：2016-01-21
申请号：US14772398
申请日：2014-03-12
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Dominic J. MONGILLO , Brandon W. SPANGLER
IPC分类号： F02C7/18 , F01D9/04 , F01D25/12 , F01D11/08 , F01D25/30 , F02C7/25 , F01D5/18
CPC分类号： F02C7/18 , F01D5/186 , F01D5/187 , F01D9/041 , F01D9/065 , F01D11/08 , F01D25/12 , F01D25/30 , F02C7/25 , F02K1/822 , F05D2220/32 , F05D2240/11 , F05D2240/12 , F05D2240/127 , F05D2240/30 , F05D2240/35 , F05D2250/141 , F05D2250/185 , F05D2250/711 , F05D2250/712 , F05D2250/75 , F05D2260/201 , F05D2260/202 , F05D2260/204 , F05D2260/2212 , F05D2260/22141 , F23R3/16 , F23R2900/03045 , Y02T50/675
摘要： A component according to an exemplary aspect of the present disclosure includes, among other things, a first wall, a second wall and at least one row of shaped pedestals extending between the first wall and the second wall. The at least one row of shaped pedestals includes a first set of C-shaped pedestals and a second set of C-shaped pedestals adjacent to the first set of C-shaped pedestals.
摘要翻译：根据本公开的示例性方面的部件包括在第一壁和第二壁之间延伸的第一壁，第二壁和至少一排成形基座。至少一排成形基座包括第一组C形基座和与第一组C形基座相邻的第二组C形基座。

48. 发明申请

US20150354821A1 Cumbustor Liners with U-Shaped Cooling Channels 有权
标题翻译：具有U形冷却通道的铜制衬管
公开(公告)号：US20150354821A1
公开(公告)日：2015-12-10
申请号：US14647035
申请日：2013-11-06
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Frank J. Cunha
IPC分类号： F23R3/04 , F23R3/00
CPC分类号： F23R3/04 , F02C7/18 , F02C7/185 , F05D2240/35 , F05D2260/201 , F05D2260/202 , F05D2260/2212 , F05D2260/2214 , F05D2260/22141 , F23R3/002 , F23R3/005 , F23R3/02 , F23R3/06 , F23R3/08 , F23R3/42 , F23R3/425 , F23R3/44 , F23R3/46 , F23R3/50 , F23R3/52 , F23R3/54 , F23R3/56 , F23R3/58 , F23R2900/03041 , F23R2900/03042 , F23R2900/03043 , F23R2900/03044 , F23R2900/03045 , Y02T50/675
摘要： A combustor having U-shaped cooling channels is disclosed. The combustor may include a shell having an impingement hole, a liner spaced from the shell and having an effusion hole; a first partition spanning between the shell and the liner, a second partition spaced from the first partition and spanning between the shell and the liner; and a U-shaped channel defined between the shell and the liner and defined in part by the wall, the channel having upstream and downstream ends both adjacent the first partition and separated by the wall, wherein the impingement hole communicates with the upstream end and the effusion hole communicates with the downstream end.
摘要翻译：公开了一种具有U形冷却通道的燃烧器。燃烧器可以包括具有冲击孔的壳体，与壳体间隔开并具有渗出孔的衬套; 跨越所述壳体和所述衬套之间的第一分隔件，与所述第一分隔件间隔开并跨越所述壳体和所述衬套之间的第二分隔件; 以及U形通道，其限定在所述壳体和所述衬套之间并且部分地由所述壁限定，所述通道具有邻近所述第一隔板的上游和下游端部并被所述壁分隔，其中所述冲击孔与所述上游端和渗出孔与下游端连通。

49. 发明申请

US20150315929A1 GAS TURBINE ENGINE AIRFOIL COOLING PASSAGE CONFIGURATION 审中-公开
标题翻译：气体涡轮发动机空气冷却通风配置
公开(公告)号：US20150315929A1
公开(公告)日：2015-11-05
申请号：US14696627
申请日：2015-04-27
申请人： United Technologies Corporation
发明人： Tracy A. Propheter-Hinckley , San Quach
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F01D5/187 , F05D2220/32 , F05D2260/22141 , Y02T50/676
摘要： An airfoil for a gas turbine engine includes an airfoil body that extends in a radial direction from a support. The airfoil body has pressure and suction side walls joined at leading and trailing edges to provide an exterior airfoil surface. A chord-wise direction extends between the leading and trailing edges and a thickness direction transverse to chord-wise direction and extending between the pressure and suction side walls. Cooling passages extend from the support into the airfoil body. The cooling passages include adjacent passageways in the thickness direction and are separated by a chord-wise wall. One of the adjacent passageways is adjacent to another passageway in the chord-wise direction and is separated by a rib in the thickness direction. The rib is discontinued at a location along the radial direction to provide an opening that fluidly connects one of the adjacent passageways to the other passageway.
摘要翻译：用于燃气涡轮发动机的翼型件包括从支撑件沿径向方向延伸的翼型件本体。翼型体具有在前缘和后缘处连接的压力和吸力侧壁，以提供外部翼面表面。并列方向在前缘和后缘之间延伸，厚度方向横向于弦向并在压力侧和吸力侧壁之间延伸。冷却通道从支撑件延伸到翼型体中。冷却通道包括在厚度方向上相邻的通道，并且由一个和弦壁隔开。相邻通道中的一个沿着并列方向的另一个通道相邻，并且在厚度方向上被肋条隔开。肋沿着径向方向停止，以提供将相邻通道中的一个流体连接到另一个通道的开口。

50. 发明申请

US20150285086A1 GAS TURBINE ENGINE TURBINE VANE PLATFORM COOLING 审中-公开
标题翻译：燃气涡轮发动机涡轮风扇平台冷却
公开(公告)号：US20150285086A1
公开(公告)日：2015-10-08
申请号：US14675824
申请日：2015-04-01
申请人： United Technologies Corporation
发明人： James P. Bangerter
IPC分类号： F01D9/02 , F01D5/02 , F01D1/02 , F01D25/12
CPC分类号： F01D9/02 , F01D1/02 , F01D5/02 , F01D5/18 , F01D9/041 , F01D9/065 , F01D25/12 , F05D2220/32 , F05D2230/232 , F05D2240/12 , F05D2240/81 , F05D2260/201 , F05D2260/2212 , F05D2260/22141 , Y02T50/672 , Y02T50/676
摘要： A stator vane for a gas turbine engine includes an airfoil that extends radially from a first side of a platform. A pocket is provided in the platform on a second side opposite the airfoil. Forward and aft rails extend from the second side of the platform. One of the forward and aft rails includes a radial surface. An impingement plate is secured to the platform over the pocket. The impingement plate includes a radial wall that engages the radial surface.
摘要翻译：用于燃气涡轮发动机的定子叶片包括从平台的第一侧径向延伸的翼型件。在与翼型相对的第二侧的平台上设置有口袋。前后导轨从平台的第二侧延伸。前后轨道中的一个包括径向表面。冲击板在口袋上固定到平台上。冲击板包括接合径向表面的径向壁。

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