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1. 发明公开

EP3526457A2 TURBINE ENGINE AND METHOD OF COOLING THEREOF 审中-公开
公开(公告)号：EP3526457A2
公开(公告)日：2019-08-21
申请号：EP17889699.9
申请日：2017-11-03
申请人： General Electric Company
发明人： MONIZ, Thomas Ory , GLOVER, Jerrey , ROSE, Joseph George , CLEMENTS, Jeffrey Donald
IPC分类号： F02C7/18 , F02C7/141 , F02C9/16 , F02K3/06 , F01D15/10

2. 发明公开

EP3187700A3 METHOD AND SYSTEM FOR CENTRIFUGAL PUMP 审中-公开
标题翻译：离心泵的方法和系统
公开(公告)号：EP3187700A3
公开(公告)日：2017-08-16
申请号：EP16203873.1
申请日：2016-12-13
申请人： General Electric Company
发明人： MONIZ, Thomas Ory , BECKER JR., Thomas Lee
IPC分类号： F01D25/18 , F01D25/20
CPC分类号： F01D25/20 , F01D5/06 , F01D25/162 , F01D25/18 , F01D25/183 , F04D1/12 , F04D29/321 , F05D2220/32 , F05D2240/60 , F05D2260/98 , Y02T50/671
摘要： The pump (300) includes a first rotatable member (302) including a radially inward facing groove (310) having an edge (308). The first rotatable member (302) configured to receive a plurality of flows of fluid over the edge (308). The first rotatable member (302) configured to rotate at a first angular velocity (316). The pump (300) also includes a second rotatable member (304) including a collector (304) configured to rotate at a second angular velocity (318). The second rotatable member (304) also includes a plurality of scoop tubes (314) extending radially outwardly from the collector (304). Each scoop tube of the plurality of scoop tubes (314) includes a first end coupled in flow communication to the collector (304) and a second end including an inlet opening extending into the groove (310). The second end curved such that the inlet opening is open in a direction of rotation of the second rotatable member (304). The inlet opening configured to scoop a fluid collected in the groove (310).
摘要翻译：泵（300）包括第一可旋转构件（302），该第一可旋转构件包括具有边缘（308）的径向面向内的凹槽（310）。第一可旋转构件（302）构造成在边缘（308）上接收多个流体流。第一可旋转构件（302）构造成以第一角速度（316）旋转。泵（300）还包括第二可旋转构件（304），其包括构造成以第二角速度（318）旋转的收集器（304）。第二可旋转构件（304）还包括从收集器（304）径向向外延伸的多个汲取管（314）。多个杓管（314）中的每个舀管包括与收集器（304）流动连通的第一端和包括延伸到凹槽（310）中的入口开口的第二端。第二端部弯曲成使得入口开口在第二可旋转构件（304）的旋转方向上打开。入口开口构造成铲取收集在凹槽（310）中的流体。

3. 发明公开

EP3192998A1 METHOD AND SYSTEM FOR CONTROLLING CORE COWL VENT AREA 审中-公开
标题翻译：用于控制核心通风区域的方法和系统
公开(公告)号：EP3192998A1
公开(公告)日：2017-07-19
申请号：EP17150244.6
申请日：2017-01-04
申请人： General Electric Company
发明人： CHILLAPALLI, Durga Srinivas , KUMAR, Hemanth , MONDAL, Bhaskar Nanda , PAL, Kishanjit , SHEVAKARI, Sushilkumar , MONIZ, Thomas Ory
IPC分类号： F02K1/06 , F02K1/38 , F02C7/18
CPC分类号： F02K1/06 , F02C7/18 , F02K1/38 , F02K3/06 , F05D2220/36 , F05D2260/205 , F05D2260/608 , Y02T50/675
摘要： A variable core cowl vent nozzle system is described herein, the system including a core casing 118 at least partially surrounding a core engine 114 of a gas turbine engine 100, and a core cowl 120 extending aftward from the core casing 118. The core cowl 120 defines a core cowl vent area (V) between the core cowl 120 and a primary nozzle 131. At least one of the core cowl 120 and the primary nozzle 131 is movable to vary the core cowl vent area (V). A method for varying the core cowl vent area (V) by moving one or more of the core cowl 120 and the primary nozzle 131 is also described herein.
摘要翻译：本文描述了一种可变核心罩通风口喷嘴系统，该系统包括至少部分地围绕燃气涡轮发动机100的核心发动机114的核心壳体118以及从核心壳体118向后延伸的核心整流罩120.核心整流罩120 限定了核心整流罩120和主喷嘴131之间的核心整流罩通风区域（V）。核心整流罩120和主喷嘴131中的至少一个可移动以改变核心整流罩通风面积（V）。本文还描述了通过移动一个或多个核心整流罩120和主喷嘴131来改变核心整流罩通风面积（V）的方法。

4. 发明公开

EP3187700A2 METHOD AND SYSTEM FOR CENTRIFUGAL PUMP 审中-公开
公开(公告)号：EP3187700A2
公开(公告)日：2017-07-05
申请号：EP16203873.1
申请日：2016-12-13
申请人： General Electric Company
发明人： MONIZ, Thomas Ory , BECKER JR., Thomas Lee
IPC分类号： F01D25/18 , F01D25/20 , F02C7/14
CPC分类号： F01D25/20 , F01D5/06 , F01D25/162 , F01D25/18 , F01D25/183 , F04D1/12 , F04D29/321 , F05D2220/32 , F05D2240/60 , F05D2260/98 , Y02T50/671
摘要： The pump (300) includes a first rotatable member (302) including a radially inward facing groove (310) having an edge (308). The first rotatable member (302) configured to receive a plurality of flows of fluid over the edge (308). The first rotatable member (302) configured to rotate at a first angular velocity (316). The pump (300) also includes a second rotatable member (304) including a collector (304) configured to rotate at a second angular velocity (318). The second rotatable member (304) also includes a plurality of scoop tubes (314) extending radially outwardly from the collector (304). Each scoop tube of the plurality of scoop tubes (314) includes a first end coupled in flow communication to the collector (304) and a second end including an inlet opening extending into the groove (310). The second end curved such that the inlet opening is open in a direction of rotation of the second rotatable member (304). The inlet opening configured to scoop a fluid collected in the groove (310).

5. 发明公开

EP3187691A1 TURBOFAN ENGINE ASSEMBLY AND METHOD OF ASSEMBLING THE SAME 审中-公开
标题翻译：涡轮增压发动机组件及其组装方法
公开(公告)号：EP3187691A1
公开(公告)日：2017-07-05
申请号：EP16203391.4
申请日：2016-12-12
申请人： General Electric Company
发明人： MONIZ, Thomas Ory , ROSE, Joseph George , KEMPER, Paul Daniel
IPC分类号： F01D9/04 , F01D25/16 , F01D25/24
CPC分类号： F04D29/542 , F01D9/041 , F01D25/162 , F01D25/243 , F01D25/246 , F02C3/04 , F02K3/06 , F04D29/522 , F04D29/644 , F05D2220/323 , F05D2230/60 , F05D2230/70 , F05D2240/12 , F05D2240/129 , F05D2240/35 , F05D2240/80 , F05D2250/36 , Y02T50/671 , Y02T50/673
摘要： A turbofan engine assembly 110 includes a core gas turbine engine 116 with a booster compressor 122 having a radially outer diameter, a fan case assembly 114, and an outlet guide vane assembly 152. The outlet guide vane assembly includes a plurality of outlet guide vane segments 149 spaced circumferentially about the core gas turbine engine. Each outlet guide vane segment of the plurality of outlet guide vane segments includes a radially inner fan hub frame flange 153 configured to couple to the core gas turbine engine, a radially outer fan case flange 155 configured to couple to the fan case assembly, and a plurality of outlet guide vanes 151 extending therebetween. The radially inner diameter of the outlet guide vane assembly is smaller than the radially outer diameter of the booster compressor.
摘要翻译：涡轮风扇发动机组件110包括具有径向外径的增压压缩机122的核心燃气涡轮发动机116，风扇箱组件114和出口导向叶片组件152.出口导向叶片组件包括多个出口导向叶片段围绕核心燃气涡轮发动机周向间隔开。多个出口导向叶片节段中的每个出口导向叶片节段包括构造成联接至核心燃气涡轮发动机的径向内部风扇轮毂框架凸缘153，构造成联接至风扇壳体组件的径向外部风扇壳体凸缘155，在其间延伸的多个出口导向叶片151。出口导向叶片组件的径向内径小于增压压缩机的径向外径。

6. 发明公开

EP3181830A1 ACTIVE HIGH PRESSURE COMPRESSOR CLEARANCE CONTROL 审中-公开
标题翻译：主动式高压压缩机间隙控制
公开(公告)号：EP3181830A1
公开(公告)日：2017-06-21
申请号：EP16203216.3
申请日：2016-12-09
申请人： General Electric Company
发明人： MONIZ, Thomas Ory , ROSE, Joseph George
IPC分类号： F01D11/24 , F02C6/08 , F01D25/12 , F02C7/12
CPC分类号： F04D27/006 , F01D11/24 , F01D25/12 , F02C6/08 , F02C7/12 , F04D29/321 , F04D29/522 , F04D29/542 , F04D29/582 , F05D2220/32 , F05D2230/60 , F05D2240/12 , F05D2240/24 , F05D2260/20 , Y02T50/675
摘要： In one embodiment, a compressor clearance control system (100) is provided. The compressor clearance control system includes a cooling air source (126), a compressor casing (112), and a cooling air flowpath (128) defined through the compressor casing. The flowpath includes an inlet (132) configured to receive cooling air from the cooling air source and an outlet (140) configured to exhaust the cooling air to the cooling air source such that the flowpath defines a closed loop within the compressor.
摘要翻译：在一个实施例中，提供了一种压缩机间隙控制系统（100）。压缩机间隙控制系统包括穿过压缩机壳体限定的冷却空气源（126），压缩机壳体（112）和冷却空气流动路径（128）。流动路径包括构造成接收来自冷却空气源的冷却空气的入口（132）和构造成将冷却空气排放到冷却空气源的出口（140），使得流动路径限定压缩机内的闭合回路。

7. 发明授权

EP1895124B1 Oil cooling apparatus in fan cowling 有权
标题翻译：在风扇壳体油冷却装置
公开(公告)号：EP1895124B1
公开(公告)日：2014-07-02
申请号：EP07114906.6
申请日：2007-08-24
申请人： GENERAL ELECTRIC COMPANY
发明人： VENKATARAMANI, Kattalaicheri Srinivasan , MONIZ, Thomas Ory , STEPHENSON, Justin P. , BAILEY, William Andrew
IPC分类号： F02C7/14 , F01D25/18 , F01D25/12
CPC分类号： F02C7/14 , F01D25/12 , F01D25/18 , F05D2260/207 , F05D2260/208 , Y02T50/675

8. 发明公开

EP1895124A3 Oil cooling apparatus in fan cowling and method therefor 有权
标题翻译：在风扇罩和方法油冷却装置
公开(公告)号：EP1895124A3
公开(公告)日：2012-11-21
申请号：EP07114906.6
申请日：2007-08-24
申请人： GENERAL ELECTRIC COMPANY
发明人： VENKATARAMANI, Kattalaicheri Srinivasan , MONIZ, Thomas Ory , STEPHENSON, Justin P. , BAILEY, William Andrew
IPC分类号： F02C7/14 , F01D25/18 , F01D25/12
CPC分类号： F02C7/14 , F01D25/12 , F01D25/18 , F05D2260/207 , F05D2260/208 , Y02T50/675
摘要： A cooling apparatus 18 is provided for a turbine engine of the type including an cowling 14 with an outer surface 17 defined by a skin 15 exposed to an external air flow. The cooling apparatus 18 includes at least one heat pipe 20 disposed in the cowling 14. The heat pipe 20 has a first end 29 thermally coupled with the outer surface 17 of the casing and a second end 44 thermally coupled to a heat source, such that heat from the heat source can be transferred through the heat pipe 20 to the external air flow.

9. 发明公开

EP3464823A1 SYSTEM FOR A LOW SWIRL LOW PRESSURE TURBINE 审中-公开
公开(公告)号：EP3464823A1
公开(公告)日：2019-04-10
申请号：EP17733151.9
申请日：2017-04-19
申请人： General Electric Company
发明人： MILLER, Brandon, Wayne , MONIZ, Thomas Ory , CLEMENTS, Jeffrey Donald , ROSE, Joseph George
IPC分类号： F01D5/14 , F01D9/04 , F01D25/24 , F02C7/36 , F02K3/02 , F02K3/06

10. 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.

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