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41. 发明申请

US20170058689A1 SEALING ELEMENT FOR A TURBO-MACHINE, TURBO-MACHINE COMPRISING A SEALING ELEMENT AND METHOD FOR MANUFACTURING A SEALING ELEMENT 审中-公开
标题翻译：涡轮机的密封元件，包含密封元件的涡轮机和用于制造密封元件的方法
公开(公告)号：US20170058689A1
公开(公告)日：2017-03-02
申请号：US15247247
申请日：2016-08-25
申请人： Rolls-Royce Deutschland Ltd & Co KG
发明人： Miklos GAEBLER , Stephan PANNIER , Mandy Eileen SCHNEIDER
IPC分类号： F01D11/12 , F04D29/32 , F01D11/10 , F01D5/12 , F04D29/52 , F01D25/24 , F04D29/16 , F01D5/02
CPC分类号： F01D11/127 , F01D11/10 , F01D11/122 , F04D29/164 , F04D29/526 , F05D2220/323 , F05D2250/11 , F05D2250/121 , F05D2250/131 , F05D2250/132 , F05D2250/141 , F05D2250/283 , F16J15/444
摘要： A sealing element for a turbomachine, in particular an aircraft engine, with a housing for the at least one rotating structural component is provided. The sealing element comprises a honeycomb structure for arrangement inside the housing, wherein the honeycomb structure extends in a first direction, wherein support structures are connected to the honeycomb structure in one piece and/or in a pattern-like manner and extend at least partially into the honeycomb structure, and the support structures extend at least partially or completely in a second direction that is different from the first direction. The support structures have planar portions, which are formed by at least one partially or completely closed cell together with the honeycomb structure.
摘要翻译：提供了一种用于涡轮机，特别是飞机发动机的密封元件，其具有用于至少一个旋转结构部件的壳体。所述密封元件包括用于布置在所述壳体内的蜂窝结构体，其中所述蜂窝结构体沿第一方向延伸，其中支撑结构以一体式和/或图案状方式连接到所述蜂窝结构，并且至少部分地延伸到蜂窝结构和支撑结构至少部分地或完全地在与第一方向不同的第二方向上延伸。支撑结构具有平面部分，其由与蜂窝结构一起的至少一个部分或完全闭合的单元形成。

42. 发明申请

US20170016457A1 Flow Control Structures For Turbomachines and Methods of Designing The Same 有权
标题翻译：涡轮机的流量控制结构及其设计方法
公开(公告)号：US20170016457A1
公开(公告)日：2017-01-19
申请号：US15280362
申请日：2016-09-29
申请人： Concepts NREC, LLC
发明人： David Japikse
IPC分类号： F04D29/44 , F04D29/28
CPC分类号： F04D29/444 , F01D5/048 , F01D5/12 , F01D9/02 , F01D9/06 , F01D25/24 , F04D29/162 , F04D29/167 , F04D29/284 , F04D29/4206 , F04D29/426 , F04D29/441 , F04D29/448 , F04D29/526 , F04D29/664 , F04D29/685 , F04D31/00 , F05D2240/121 , F05D2240/126 , F05D2250/52 , G06F17/10 , G06F17/5086
摘要： Flow control devices and structures designed and configured to improve the performance of a turbomachine. Exemplary flow control devices may include various flow guiding channels, ribs, diffuser passage-width reductions, and other treatments and may be located on one or both of a shroud and hub side of a machine to redirect, guide, or otherwise influence portions of a turbomachine flow field to thereby improve the performance of the machine.
摘要翻译：流量控制装置和结构设计和配置以改善涡轮机的性能。示例性流量控制装置可以包括各种流动引导通道，肋，扩散器通道宽度减小和其它处理，并且可以位于机器的护罩和轮毂侧的一个或两个上，以重定向，引导或以其他方式影响涡轮机流场，从而提高机器的性能。

43. 发明申请

US20170016454A1 METHOD FOR COATING COMPRESSOR BLADE TIPS 审中-公开
标题翻译：涂覆压缩机叶片的方法
公开(公告)号：US20170016454A1
公开(公告)日：2017-01-19
申请号：US14630965
申请日：2015-02-25
申请人： United Technologies Corporation
发明人： Christopher W. Strock , Changsheng Guo
IPC分类号： F04D29/32 , F04D29/52 , C23C26/00 , F04D29/02
CPC分类号： F04D29/324 , B23K9/044 , B23K9/23 , B23K2101/001 , B23K2103/26 , C23C26/00 , F01D5/288 , F04D29/023 , F04D29/526 , F05D2230/30 , F05D2230/90 , F05D2300/226
摘要： A method for forming a component having an abrasive portion includes forming the component and selectively forming a coating on the component using electric spark deposition to form the abrasive portion. A method for coating a blade tip with an abrasive material includes forming a blade having a tip and depositing a coating on the blade tip using electric spark deposition. A method includes providing a casing having an inner diameter surface, locating an abradable coating on a portion of the inner diameter surface, providing a blade configured to rotate within the casing and having a blade tip where the blade tip and the inner diameter surface of the casing form a seal, and depositing an abrasive coating on the blade tip using electric spark deposition so that the abrasive coating and abradable coating interact during rotation of the blade within the casing.
摘要翻译：用于形成具有研磨部分的部件的方法包括形成部件并且使用电火花沉积选择性地在部件上形成涂层以形成磨料部分。用研磨材料涂覆刀片尖端的方法包括形成具有尖端的刀片，并使用电火花沉积在刀片尖端上沉积涂层。一种方法包括提供具有内径表面的壳体，将可磨损涂层定位在内径表面的一部分上，提供构造成在壳体内旋转并具有叶片尖端的刀片，其中刀尖和内径表面套管形成密封件，并且使用电火花沉积将磨料涂层沉积在刀片尖端上，使得研磨涂层和可磨损涂层在壳体内的刀片旋转期间相互作用。

44. 发明申请

US20160369703A1 EFFICIENT, LOW PRESSURE RATIO PROPULSOR FOR GAS TURBINE ENGINES 审中-公开
标题翻译：高效的，用于气体涡轮发动机的低压比推进器
公开(公告)号：US20160369703A1
公开(公告)日：2016-12-22
申请号：US15233142
申请日：2016-08-10
申请人： United Technologies Corporation
发明人： Edward J. Gallagher , Byron R. Monzon , Shari L. Bugaj
IPC分类号： F02C7/36 , F04D29/02 , F04D29/053 , F02K3/06 , F04D29/38 , F04D29/56 , F04D29/52 , F01D15/12 , F04D29/32
CPC分类号： F02C7/36 , F01D5/147 , F01D5/282 , F01D15/12 , F02K1/06 , F02K3/06 , F04D29/023 , F04D29/053 , F04D29/325 , F04D29/388 , F04D29/526 , F04D29/563 , F05D2220/32 , F05D2220/327 , F05D2220/36 , F05D2260/4031 , F05D2300/603 , Y02T50/672
摘要： A gas turbine engine includes a gear assembly and a bypass flow passage that includes an inlet and an outlet that define a design pressure ratio between 1.3 and 1.55. A fan is arranged at the inlet. A first turbine is coupled with a first shaft such that rotation of the first turbine will drive the fan, through the first shaft and the gear assembly, at a lower speed than the first shaft. The fan includes a row of fan blades. The row includes 12-16 (N) fan blades, a solidity value (R) that is from 1.0 to 1.3, and a ratio of N/R that is from 10.0 to 16.
摘要翻译：燃气涡轮发动机包括齿轮组件和旁通流动通道，其包括限定1.3至1.55之间的设计压力比的入口和出口。入口处设有风扇。第一涡轮与第一轴联接，使得第一涡轮的旋转将以比第一轴更低的速度通过第一轴和齿轮组件驱动风扇。风扇包括一排风扇叶片。该行包括12-16（N）个风扇叶片，固体值（R）为1.0至1.3，N / R的比例为10.0至16。

45. 发明申请

US20160363135A1 FAN CASING ASSEMBLY 审中-公开
标题翻译：风扇组装
公开(公告)号：US20160363135A1
公开(公告)日：2016-12-15
申请号：US15151136
申请日：2016-05-10
申请人： ROLLS-ROYCE plc
发明人： Ian C D CARE , Dale E EVANS
IPC分类号： F04D29/66 , F04D29/38 , F04D29/02 , F04D29/32 , F04D29/52 , F04D29/70
CPC分类号： F04D29/662 , F01D21/045 , F01D25/24 , F04D29/023 , F04D29/325 , F04D29/38 , F04D29/526 , F04D29/703 , F05D2220/32 , F05D2220/36 , F05D2250/41 , Y02T50/672
摘要： A fan casing assembly comprising an annular casing member for circumferentially surrounding a fan, and an annular fan track liner comprising a plurality of circumferentially adjacent liner panels. The annular fan track liner is positioned radially inward of the annular casing member. A tilting arrangement is provided and configured to selectively circumferentially tilt one or more of the liner panels, such that, in the event of a fan blade being released from a fan, the tilting arrangement can initiate tilting of one or more liner panels so that the liner panels can trim one or more of the remaining fan blades.
摘要翻译：一种风扇壳体组件，包括用于周向地围绕风扇的环形壳体构件和包括多个周向相邻的衬板的环形风扇轨道衬套。环形风扇履带衬板位于环形壳体构件的径向内侧。提供倾斜装置并且构造成选择性地周向地倾斜一个或多个衬板，使得在风扇叶片从风扇释放的情况下，倾斜装置可以启动一个或多个衬板的倾斜，使得衬板可以修剪一个或多个剩余的风扇叶片。

46. 发明授权

US09513021B2 Blower and heat pump apparatus using the same 有权
标题翻译：鼓风机和热泵设备使用相同
公开(公告)号：US09513021B2
公开(公告)日：2016-12-06
申请号：US13123174
申请日：2009-10-29
申请人： Yasuaki Kato , Takahide Tadokoro , Masanobu Baba , Hiroyuki Takada
发明人： Yasuaki Kato , Takahide Tadokoro , Masanobu Baba , Hiroyuki Takada
IPC分类号： F01D25/24 , F24F1/38 , F04D29/16 , F04D29/52 , F04D29/66 , F24F1/40
CPC分类号： F24F1/38 , F04D29/162 , F04D29/164 , F04D29/526 , F04D29/663 , F24F1/40
摘要： The rear side outer peripheral edge of a propeller fan rotated and driven by a motor, of a propeller fan drive unit, is surrounded by a bell mouth. An upper plate, a lower plate, a side plate, and a machine room plate constitute an air duct at the suction side, outside the radial direction of the propeller fan. The cross-section of the bell mouth, at a first position in the vicinity where a blade of the propeller fan is closest, and where the distance between the propeller fan and the plate constituting the air duct outside the radial direction is relatively narrow, is made to be such that an expansion angle θ1 of the bell mouth suction side is made small. The overlapped height Hb of the propeller fan and the bell mouth is made large against a cross-section at a second position where the distance between the propeller fan and a plate is relatively large. The shape of the cross-section of the bell mouth is made to change gradually between the first position and the second position.
摘要翻译：由螺旋桨式风扇驱动单元的电动机旋转驱动的螺旋桨式风扇的后侧外周边缘被喇叭口包围。上板，下板，侧板和机室板构成在螺旋桨式风扇的径向外侧的吸入侧的风路。喇叭口的横截面在螺旋桨叶片的叶片最靠近的第一位置处，螺旋桨式风扇和构成空气管道的板之间的距离在径向外的距离相对较窄，使得喇叭口吸入侧的扩张角θ1变小。螺旋桨式风扇和喇叭口的重叠高度Hb相对于螺旋桨式风扇和板之间的距离相对较大的第二位置处的横截面大得多。喇叭口的横截面的形状在第一位置和第二位置之间逐渐变化。

47. 发明申请

US20160327059A1 Max Phase Reinforced Polymer Matrix Composite Abradables with Enhanced Thermal Conductivity 审中-公开
标题翻译：具有增强导热性的最大相增强聚合物基复合材料
公开(公告)号：US20160327059A1
公开(公告)日：2016-11-10
申请号：US14709721
申请日：2015-05-12
申请人： UNITED TECHNOLOGIES CORPORATION
发明人： Shahram Amini , Christopher W. Strock , Changsheng Guo
IPC分类号： F04D29/52 , F04D29/02 , F04D29/16 , F02K3/06 , F04D19/00
CPC分类号： F04D29/526 , F01D5/28 , F01D11/12 , F01D11/122 , F01D21/045 , F02K3/06 , F04D19/002 , F04D29/023 , F04D29/164 , F05B2220/302 , F05B2230/90 , F05B2280/107 , F05B2280/40 , F05B2280/5011 , Y02T50/672 , Y02T50/673
摘要： A turbine engine system comprising a turbine engine component, such as a fan includes a fan casing and a fan blade rotatable within the fan casing. An abradable seal coupled to the fan casing proximate the fan blade. The abradable seal comprising an abradable composite layer including a MAX phase solid and a polymer based abradable composition.
摘要翻译：包括诸如风扇的涡轮发动机部件的涡轮发动机系统包括风扇壳体和在风扇壳体内可旋转的风扇叶片。与风扇壳体相邻的可磨损密封件，靠近风扇叶片。可磨损密封件包括包含MAX相固体和基于聚合物的可磨损组合物的可磨损复合层。

48. 发明申请

US20160319689A1 KEYSTONED BLADE TRACK 审中-公开
标题翻译：梯形叶片跟踪
公开(公告)号：US20160319689A1
公开(公告)日：2016-11-03
申请号：US15090134
申请日：2016-04-04
申请人： Rolls-Royce North American Technologies, Inc. , Rolls-Royce Corporation , Rolls-Royce plc
发明人： Daniel K. Vetters , Aaron D. Sippel , David J. Thomas , Andrew J. Eifert , Paul A. Davis , Simon L. Jones , Peter Broadhead , Bruce E. Varney , Jeffrey A. Walston , Steven Hillier
IPC分类号： F01D11/12 , F01D25/12
CPC分类号： F01D11/122 , C04B35/803 , C04B35/806 , C04B35/83 , C04B2235/5252 , C04B2235/94 , F01D11/12 , F01D25/005 , F01D25/12 , F04D29/164 , F04D29/526 , F05D2220/32 , F05D2230/60 , F05D2240/11 , F05D2240/55 , F05D2260/22141 , F05D2260/52 , F05D2300/6033 , Y02T50/672
摘要： A blade track for a gas turbine engine includes a plurality of blade track segments. The blade track segments are arranged circumferentially around a central axis to form the blade track.
摘要翻译：用于燃气涡轮发动机的叶片轨道包括多个叶片轨道段。刀片轨道段围绕中心轴线周向布置以形成刀片轨道。

49. 发明申请

US20160281739A1 BLOWER AND OUTDOOR UNIT OF AIR CONDITIONER COMPRISING SAME 审中-公开
标题翻译：包含该空气调节器的风扇和室外单元
公开(公告)号：US20160281739A1
公开(公告)日：2016-09-29
申请号：US15172027
申请日：2016-06-02
申请人： SAMSUNG ELECTRONICS CO., LTD.
发明人： Masaru NAKAGAWA , Seiji SATO
IPC分类号： F04D29/52 , F04D29/32 , F04D29/66 , F04D25/16 , F04D29/58
CPC分类号： F04D29/663 , F04D19/002 , F04D25/166 , F04D29/325 , F04D29/522 , F04D29/526 , F04D29/542 , F04D29/544 , F04D29/547 , F04D29/5833 , F04D29/666 , F04D29/667 , F24F1/38 , F24F1/40 , F25B39/00 , F25B39/028 , F25D17/067
摘要： Provided are a blower, capable of suppressing noise occurring in a stator while significantly improving blowing efficiency, and an outdoor unit using the same. The present invention comprises: a bell mouth part spaced apart at a predetermined distance in the radial direction with respect to an outer circumferential end of a propeller fan; and a diffuser part installed on the downstream side of the bell mouth part, and having a flow path area which is enlarged from the upstream side toward the downstream side with a larger magnification rate than the magnification rate of the flow path area in the downstream end of the bell mouth part; and a stator part having a plurality of stators, wherein the stator part is arranged within the diffuser part.
摘要翻译：提供一种鼓风机，能够抑制定子中产生的噪音，同时显着提高吹风效率，以及使用该鼓风机的室外机。本发明包括：相对于螺旋桨式风扇的外圆周端在径向方向上隔开预定距离的喇叭口部分; 以及扩散部，其安装在喇叭口部的下游侧，具有从上游侧向下游侧扩大的流路面积，放大率比下游端的流路面积的放大率大的喇叭口部分; 以及具有多个定子的定子部件，其中定子部件布置在扩散器部分内。

50. 发明授权

US09429038B2 Method for mounting shielding on a turbine casing, and mounting assembly for implementing same 有权
标题翻译：在涡轮壳体上安装屏蔽的方法，以及用于实现其的安装组件
公开(公告)号：US09429038B2
公开(公告)日：2016-08-30
申请号：US13817057
申请日：2011-08-23
申请人： Jean-Luc Pierre Sahores , Carole Jaureguiberry , Jean-Maurice Casaux-Bic , Olivier Pierre Descubes
发明人： Jean-Luc Pierre Sahores , Carole Jaureguiberry , Jean-Maurice Casaux-Bic , Olivier Pierre Descubes
IPC分类号： F01D25/24 , F01D21/04 , F02C7/05 , F02K1/82 , F04D27/00 , F04D29/52 , B21K1/26 , F04D27/02
CPC分类号： F01D25/24 , B21K1/26 , F01D21/045 , F02C7/05 , F02K1/82 , F04D27/008 , F04D27/0261 , F04D29/522 , F04D29/526 , F05D2240/14 , Y10T29/49323
摘要： A method and structure negating thermal inertia of a solid portion, such as shielding, which influences mechanical behavior of parts of an engine structure, by reducing forces transmitted to the engine structure during an event in which a turbine blade ruptures, while preserving mechanical strength and vibratory positioning. The structure includes a flexible fastener for a shield, enabling producing a fusible section. An assembly for mounting a shielding onto a casing of the engine structure of a turbine includes connection lugs and points for attachment to the casing and shielding. The attachment points are sufficiently spaced apart in accordance with curvature of the shielding and casing so connection between the lugs and the shielding or casing, and connection of the attachment points, are substantially tangential. The lugs are sized so the connection has sufficient flexibility to control vibratory positioning thereof and ensure sufficient mechanical strength under thermo-mechanical loads.
摘要翻译：一种方法和结构通过在涡轮叶片破裂的事件期间减少传递到发动机结构的力同时保持机械强度而抵消固体部分（例如屏蔽）的热惯性，其影响发动机结构部件的机械性能，振动定位。该结构包括用于护罩的柔性紧固件，能够产生可熔部分。用于将屏蔽件安装在涡轮机的发动机结构的壳体上的组件包括用于附接到壳体和屏蔽的连接凸耳和点。附接点根据屏蔽和壳体的曲率充分间隔开，因此凸耳与屏蔽或壳体之间的连接以及连接点的连接基本上是切线的。凸耳的尺寸使得连接具有足够的灵活性来控制其振动定位并且确保在热机械载荷下的足够的机械强度。

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