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1. 发明公开

EP3351725A1 ROTOR THRUST BALANCED TURBINE ENGINE 审中-公开
公开(公告)号：EP3351725A1
公开(公告)日：2018-07-25
申请号：EP18151720.2
申请日：2018-01-15
申请人： General Electric Company
发明人： MONIZ, Thomas Ory , CLEMENTS, Jeffrey Donald
IPC分类号： F01D3/00 , F01D25/16 , F01D11/00
CPC分类号： F01D5/027 , F01D3/00 , F01D11/00 , F01D11/08 , F01D25/16 , F01D25/24 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2220/32 , F05D2270/051
摘要： The present disclosure is directed to a rotor thrust balanced turbine engine (10) that may increase engine performance and efficiency while managing thrust mismatch or imbalance in a low pressure (LP) spool between a fan assembly and a turbine rotor assembly (20). The gas turbine engine (10) defines a radial direction, a longitudinal direction, and a circumferential direction, an upstream end (99) and a downstream end (98) along the longitudinal direction, and an axial centerline (15) extended along the longitudinal direction. The gas turbine engine (10) includes a turbine rotor assembly (20) and a turbine frame (30). The turbine rotor assembly (20) defines a first flowpath radius (11) and a second flowpath radius (12) each extended from the axial centerline (15). The first flowpath radius (11) is disposed at the upstream end (99) of the turbine rotor assembly (20), and wherein the second flowpath radius (12) is disposed at the downstream end (98) of the turbine rotor assembly (20). The turbine frame (30) and the turbine rotor assembly (20) together define a seal interface radius (25) inward of the turbine rotor assembly (20) along the radial direction and concentric to the axial centerline (15), and wherein the turbine rotor assembly (20) defines a ratio of the first flowpath radius (11) to the seal interface radius (25) less than or equal to approximately 1.79.

2. 发明公开

EP3295033A1 SUBMERGED HYDRODYNAMIC MAGNETIC VARIABLE SPEED DRIVE UNIT 有权转让
公开(公告)号：EP3295033A1
公开(公告)日：2018-03-21
申请号：EP16777794
申请日：2016-05-11
申请人： FUGLESANGS SUBSEA AS
发明人： FUGLESANG ALEXANDER , WESTBERG TOMMY
IPC分类号： F04D13/02 , F04D13/06 , F04D13/08 , F04D25/02 , F04D25/06
CPC分类号： E21B43/128 , F04D13/022 , F04D13/023 , F04D13/024 , F04D13/025 , F04D13/027 , F04D13/04 , F04D13/0653 , F04D13/086 , F04D25/022 , F04D25/026 , F04D25/045 , F04D25/0686 , F04D29/5806
摘要： A unique low cost and efficient submersible, hermetically sealed, variable speed system intended to drive submersible boosting units. The system includes a unique combination of a liquid filled electrical motor connected to a hydraulic coupling and a magnetic coupling driver section, in a hermetically sealed container, with a magnetic coupling follower driving a booster unit. The system further includes integrated cooling, lubrication and control functionality. The drive unit has an actuating system connected to internal guide vanes which controls the liquid flow between the pump impeller and turbine wheel of the hydrodynamic coupling and hence the torque and speed. The combined system is a sealed seal-less and topside-less submersible drive unit that can operate in harsh subsea environments. The drive unit opens up for use of thin walled pressure casings and low pressure electrical penetrators.

3. 发明公开

EP3293398A1 COMPRESSOR WHEEL AND SHAFT ASSEMBLY 有权转让
标题翻译：压缩机轮和轴组件
公开(公告)号：EP3293398A1
公开(公告)日：2018-03-14
申请号：EP17187379.7
申请日：2017-08-22
申请人： Honeywell International Inc.
发明人： CASTAN, Joel , ARMAND, Dominique , DIEUDONNE, Gerard , HETTINGER, Raphael , CLAUDON, Alain , REMY, Bernard
IPC分类号： F04D29/054 , F01D5/02 , F04D29/26 , F04D29/28
CPC分类号： F04D29/624 , F01D5/025 , F04D25/024 , F04D25/045 , F04D25/06 , F04D29/054 , F04D29/266 , F04D29/284 , F04D29/4206 , F05D2220/40 , F05D2260/31
摘要： An assembly can include a shaft that includes threads and a free end that includes a shaft drive feature; a compressor wheel that includes a compressor wheel drive feature and a through bore that receives the shaft; and a nut that includes threads that mate the threads of the shaft.
摘要翻译：组件可以包括具有螺纹的轴和包括轴驱动特征的自由端; 压缩机叶轮，其包括压缩机叶轮驱动部件和容纳所述轴的通孔; 以及包括与轴的螺纹配合的螺纹的螺母。

4. 发明公开

EP3249234A1 TURBOCHARGER WITH TWO-STAGE SERIES COMPRESSOR DRIVEN BY EXHAUST GAS-DRIVEN TURBINE AND ELECTRIC MOTOR 有权转让
标题翻译：涡轮增压器采用排气驱动涡轮和电动机驱动的两级系列压缩机
公开(公告)号：EP3249234A1
公开(公告)日：2017-11-29
申请号：EP17167437.7
申请日：2017-04-20
申请人： Honeywell International Inc.
发明人： DONKIN, Gavin
IPC分类号： F04D17/12 , F02B37/10 , F04D25/04 , F04D25/06 , F02C6/12 , F04D25/02 , F02B39/10 , F02B37/013
CPC分类号： F02B37/10 , F02B33/40 , F02B37/013 , F02B37/22 , F02B39/005 , F02B39/10 , F02C6/12 , F04D17/12 , F04D25/024 , F04D25/04 , F04D25/045 , F04D25/06 , F04D25/0606 , F05D2220/40 , F05D2240/40 , Y02T10/144
摘要： A turbocharger includes a two-stage serial compressor having a first impeller and a second impeller affixed to a shaft and arranged in series for a two-stage compression of air, an exhaust gas-driven turbine having a turbine wheel affixed to the shaft, and an electric motor mounted on the shaft for assisting the turbine in rotatably driving the compressor.
摘要翻译：涡轮增压器包括两级串联压缩机，其具有第一叶轮和第二叶轮，该第一叶轮和第二叶轮被固定到轴并串联布置以用于空气的两级压缩，具有固定到该轴的涡轮机叶轮的排气驱动涡轮机，以及安装在轴上的电动机，用于辅助涡轮机旋转驱动压缩机。

5. 发明公开

EP3249195A1 AN ENERGY FLOW OF AN ADVANCED ENVIRONMENTAL CONTROL SYSTEM 有权转让
标题翻译：先进的环境控制系统的能量流动
公开(公告)号：EP3249195A1
公开(公告)日：2017-11-29
申请号：EP17172757.1
申请日：2017-05-24
申请人： Hamilton Sundstrand Corporation
发明人： Hall, David E. , Bruno, Louis J.
IPC分类号： F02C1/02 , F02C6/08 , B64D13/06
CPC分类号： B64D13/02 , B64D13/06 , B64D13/08 , B64D2013/0618 , B64D2013/0644 , B64D2013/0648 , F01D1/023 , F01D5/06 , F02C1/02 , F02C6/08 , F04D25/045 , F04D25/06 , F04D29/053 , F05D2220/323 , F05D2220/62 , F05D2260/606
摘要： An airplane is provided. The airplane includes a compressing device (109). The compressing device includes a turbine (113) with a first inlet and a second inlet. The turbine provides energy by expanding mediums. The first inlet is configured to receive a first medium of the mediums. The second inlet is configured to receive a second medium of the mediums. The compressing device (109) includes a compressor (112) and a motor (117). The compressor receives a first energy derived from the first and second mediums being expanded across the turbine during a first mode of the compressing device, receives a second energy derived from the first medium being expanded across the turbine during a second mode of the compressing device, and compresses the second medium in accordance with the first mode or the second mode. The motor (117) provides a supplementary energy to the compressor.
摘要翻译：提供飞机。飞机包括压缩装置（109）。压缩装置包括具有第一入口和第二入口的涡轮机（113）。涡轮机通过扩大介质提供能量。第一入口构造成接收介质的第一介质。第二入口构造成接收介质的第二介质。压缩装置（109）包括压缩机（112）和电动机（117）。在压缩装置的第一模式期间，压缩机接收从在涡轮机上扩张的第一和第二介质获得的第一能量，在压缩装置的第二模式期间接收从在涡轮机上膨胀的第一介质获得的第二能量，并按照第一模式或第二模式压缩第二媒体。电动机（117）向压缩机提供辅助能量。

6. 发明公开

EP3176379A1 CASING FOR USE IN A TURBOFAN ENGINE AND METHOD OF SCAVENGING FLUID THEREFROM 审中-公开
标题翻译：住宅用在涡轮风扇发动机和方法进行处置流体THEREOF
公开(公告)号：EP3176379A1
公开(公告)日：2017-06-07
申请号：EP16200477.4
申请日：2016-11-24
申请人： General Electric Company
发明人： MILLER, Brandon Wayne , TOMPKINS, Andrew Michael , NIERGARTH, Daniel Alan
IPC分类号： F01D9/06 , F01D25/18
CPC分类号： F04D29/063 , F01D9/065 , F01D25/18 , F01M2001/126 , F02C7/06 , F02K3/06 , F04D25/045 , F04D29/526 , F05B2260/602 , F05D2260/40311 , F05D2260/602 , F16N31/00 , Y02T50/671
摘要： A casing 132 for use in a turbofan engine 100 is provided. The casing 132 includes an inner hub 134 including a first fluid opening 140 defined at bottom dead center of the casing 132. The casing 132 also includes an intermediate casing 136 positioned radially outward from the inner hub 134, an outer casing 138 positioned radially outward from the intermediate casing 136, and struts spaced circumferentially about the inner hub 134 and extending between the inner hub 134 and the outer casing 138. The struts include a first strut 144 and a second strut 146 positioned on opposing sides of bottom dead center of the casing 132 such that a first fluid sump 148 is defined between the inner hub 134, the intermediate casing 136, and the first and second struts 144,146. At least one of said first and second struts 144,146 includes a flow channel 150,152 extending therethrough such that a fluid flow path is defined from the first fluid opening 140, through the first fluid sump 148, and through the flow channel 150,152.
摘要翻译：一种用于在涡轮风扇发动机100使用壳体132设置。壳体132包括在内毂134包括第一流体开口140在外壳132的壳体132因此包括在从内轮毂134到外壳138沿径向向外定位的中间套136的下死点定义从向外径向定位中间壳体136和支柱沿周向间隔绕内毂134和内轮毂134和外部壳体之间延伸138.支杆包括第一支杆144和位于相对的所述壳体的下死点侧上的第二支柱146 132搜索做了第一流体储槽148内轮毂134，中间壳体136，以及第一和第二支柱144,146之间。所述至少一个第一和第二支柱144,146包括流动通道150.152通过搜索扩展有眼的流体流动路径从所述第一流体开口140所定义的通过所述第一流体储槽148，并通过流动通道150,152。

7. 发明公开

EP3047126A4 DUAL DIRECTION WINDMILL PUMP FOR GEARED TURBOFAN ENGINE 有权转让
标题翻译： ZWEIWEGE-WINDMÜHLENPUMPEFÜRDEN MOTOR EINESGETRIEBETURBOLÜFTERS
公开(公告)号：EP3047126A4
公开(公告)日：2017-04-26
申请号：EP14856564
申请日：2014-07-23
申请人： UNITED TECHNOLOGIES CORP
发明人： SHERIDAN WILLIAM G , JAMES READE W , MASTRO JACOB PETER
IPC分类号： F02C7/06 , F01D25/20 , F16H57/04
CPC分类号： F04D29/063 , F01D21/00 , F01D25/20 , F02C7/32 , F04D19/005 , F04D25/028 , F04D25/045 , F04D29/053 , F04D29/325 , F05D2260/4031 , F16H57/04
摘要： A lubrication system includes a shaft rotatable about an axis, a lubrication pump configured to supply a lubricant flow to a gear system, and a gear train coupled to the shaft and configured to drive the lubrication pump in a first direction responsive to rotation of the shaft in both the first direction and a second direction. A gas turbine engine and method are also disclosed.
摘要翻译：润滑系统包括可围绕轴线旋转的轴，构造成将润滑剂流供应到齿轮系统的润滑泵，以及联接到轴并构造成响应于轴的旋转在第一方向上驱动润滑泵的齿轮系在第一方向和第二方向上。燃气涡轮发动机和方法也被公开。

8. 发明公开

EP3105432A1 CORROSION RESISTANT PNEUMATIC ACTUATOR 审中-公开
标题翻译：耐腐蚀气动执行器
公开(公告)号：EP3105432A1
公开(公告)日：2016-12-21
申请号：EP15749295.0
申请日：2015-02-05
申请人： Borgwarner Inc.
发明人： LONGACRE, Christian , HOWELL, Ryan
IPC分类号： F02B39/16 , F02B37/18 , F02B37/22
CPC分类号： F02B37/186 , F01D5/04 , F01D17/105 , F01D17/145 , F01D25/24 , F02B39/16 , F04D25/045 , F04D29/284 , F05D2220/40 , F15B15/02 , F15B15/10 , F15B21/041 , Y02T10/144
摘要： A turbocharger (1) includes a wastegate valve (30) supported on the turbine housing (8), and a pneumatic actuator (100) configured to actuate the wastegate valve (30). The pneumatic actuator (100) includes a housing (101) separated into compartments (104, 108) by a separating member (110, 112), The actuator (100) includes a piston (112) disposed in the housing (101) that defines at least a portion of the separating member (110, 112), a piston-biasing spring (120) disposed in the housing (101), a first inlet (126) that is in fluid communication with the first compartment (104), the first inlet configured to be connected to a non-zero-pressure fluid source (8), and a second inlet (116) that is in fluid communication with the second compartment (108), the second inlet (116) configured to be connected to a non-zero-pressure fluid source (104).

9. 发明公开

EP3052812A1 COMPRESSOR AREA SPLITS FOR GEARED TURBOFAN 无效转让
标题翻译：压缩过程庭的齿轮涡轮风扇
公开(公告)号：EP3052812A1
公开(公告)日：2016-08-10
申请号：EP14848344.9
申请日：2014-04-02
申请人： United Technologies Corporation
发明人： SCHWARZ, Frederick M. , SPIESMAN, Paul H.
IPC分类号： F04D29/00 , F04D29/18 , F01D25/00 , F02C7/00
CPC分类号： F02K3/06 , B64D11/06 , F01D5/06 , F01D5/147 , F01D25/24 , F01D25/30 , F02C3/10 , F04D19/02 , F04D19/026 , F04D19/028 , F04D25/045 , F04D29/321 , F04D29/325 , F04D29/542 , F04D29/563 , F05D2220/327 , F05D2220/36 , F05D2240/30 , F05D2260/40311
摘要： A gas turbine engine has an upstream compressor having an upstream entrance area leading into a first vane upstream of the upstream compressor. A downstream compressor has an exit area at a leading edge of an exit vane for the downstream compressor. The entrance area divided by the exit area is greater than or equal to 13.8 and less than or equal to 15.3.

10. 发明公开

EP3045673A1 EXHAUST TURBINE ASSEMBLY 有权转让
标题翻译： ABGASTURBINENANORDNUNG
公开(公告)号：EP3045673A1
公开(公告)日：2016-07-20
申请号：EP15197657.8
申请日：2015-12-02
申请人： Honeywell International Inc.
发明人： GERARD, Arnaud , SOLANKI, Shankar Pandurangasa , EUMONT, Vincent , MORAND, Nicolas , ABEL, Francis , BARTHELET, Pierre
IPC分类号： F01D11/00 , F01D17/16
CPC分类号： F04D17/10 , F01D11/003 , F01D17/165 , F04D25/045 , F04D29/083 , F05D2220/40
摘要： An assembly can include a turbine wheel; a turbine housing that includes a lower turbine housing surface that extends from an exhaust volute to a cylindrical surface that defines an upper portion of a turbine wheel space;a shroud component that includes a contoured surface disposed between an inner end of an upper shroud component surface and an inner end of a lower shroud component surface where the contoured surface defines a lower portion of a turbine wheel space; anda seal mechanism where the turbine housing and the shroud component form an axial gap between a lower axial position of the cylindrical surface and an upper axial position of the contoured surface where the axial gap is axially positioned between an axial position of an inducer portion of the turbine wheel and an axial position of an exducer portion of the turbine wheel.
摘要翻译：组件可以包括涡轮机轮; 涡轮壳体，其包括从排气蜗壳延伸到限定涡轮机叶片空间的上部的圆柱形表面的下涡轮机壳体表面;护罩部件，其包括设置在上护罩部件表面的内端之间的轮廓表面以及下护罩部件表面的内端，其中轮廓表面限定涡轮机叶轮空间的下部; 以及密封机构，其中涡轮机壳体和护罩部件在圆柱形表面的下轴向位置和轮廓表面的上轴向位置之间形成轴向间隙，其中轴向间隙轴向定位在引导部分的轴向位置之间涡轮机叶轮和涡轮机叶轮的驱动部分的轴向位置。

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