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公开(公告)号：JP2013181541A
公开(公告)日：2013-09-12
申请号：JP2013038266
申请日：2013-02-28
Inventor： SUCIU GABRIEL L , MERRY BRIAN D
CPC classification number: F02K3/072 , F02C3/113 , F02C7/36 , F05D2250/36 , F05D2260/40311 , Y02T50/671
Abstract: PROBLEM TO BE SOLVED: To shorten the low shaft of an engine while increasing the output density of the engine.SOLUTION: A gas turbine engine 20 includes a shaft 40, a counter-rotating low-pressure compressor 60, and a counter-rotating low-pressure turbine 62. The counter-rotating low-pressure compressor 60 comprises a counter-rotating compressor hub 70 having blade stages 72, 74 and 76, and blade stages 78 and 80 of a low-speed spool 30 are inserted among the blade stages 72, 74 and 76. A transmission 82 counter-rotates the counter-rotating compressor hub 70 with respect to the low-speed spool 30. The counter-rotating low-pressure turbine 62 comprises inside blade sets 120 which are connected to a low shaft 40 via a gear device 116, and an outside blade set 122 which is inserted between the inside blade sets 120. The outside blade set 122 is rotated on a rotation axis in a direction opposite to the inside blade set 120 at a speed lower than the inside blade set 120.
Abstract translation: 要解决的问题：缩短发动机的低轴，同时增加发动机的输出密度。解决方案：燃气涡轮发动机20包括轴40，反向旋转低压压缩机60和反向旋转低 反转式低压压缩机60包括具有叶片级72,74和76的反向旋转的压缩机毂70，并且低速线轴30的叶片级78和80插入在叶片级之间 传动装置82相对于低速卷轴30使反向旋转的压缩机毂70相对旋转。反向旋转的低压涡轮机62包括内叶片组120，其连接到低轴 通过齿轮装置116和外部刀片组122插入在内侧刀片组120之间。外侧刀片组122以与内侧刀片组120相反的方向在旋转轴线上以低于内侧刀片组120的速度旋转。 内刀片组120。
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公开(公告)号：JP2012246915A
公开(公告)日：2012-12-13
申请号：JP2012099334
申请日：2012-04-25
Inventor： SUCIU GABRIEL L , ALVANOS IOANNIS , MERRY BRIAN D , DYE CHRISTOPHER M
CPC classification number: F01D5/284 , F01D5/147 , F01D5/282 , F01D9/041 , F01D11/001 , F01D25/246 , F05D2240/12 , F05D2300/6033
Abstract: PROBLEM TO BE SOLVED: To provide a full hoop ring structure that prevents leakage of fluid from between each segment of a vane structure.SOLUTION: A vane structure 64B includes: a ceramic matrix composite ring 66 on the outer peripheral side; a ceramic matrix composite ring 68 on the inner peripheral side; and a multiple of ceramic matrix composite airfoils 70 incorporated between the ceramic matrix composite ring 66 on the outer peripheral side and the ceramic matrix composite ring 68 on the inner peripheral side. The ceramic matrix composite ring 66 on the outer peripheral side and the ceramic matrix composite ring 68 on the inner peripheral side are basically wound around the multiple of incorporated airfoils 70 so as to form a full hoop. The design of the full hoop rings allows to maximize the utilization of the fiber strength of the ceramic matrix composite material in the full hoop configuration.
Abstract translation: 要解决的问题：提供一种防止来自叶片结构的每个部分之间的流体泄漏的完整环形环结构。 解决方案：叶片结构64B包括：外周侧的陶瓷基复合环66; 内周侧的陶瓷基复合环68; 以及并列在外周侧的陶瓷基复合环66和内周侧的陶瓷基复合环68之间的多个陶瓷基复合翼型件70。 外周侧的陶瓷基复合环66和内周侧的陶瓷基复合环68基本上缠绕在多个配置的翼型件70上，以形成完整的箍。 全环环的设计允许最大限度地利用全环形结构中的陶瓷基复合材料的纤维强度。 版权所有（C）2013，JPO＆INPIT
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3.发明专利Rotor module, turbine assembly and assembling method thereof for gas turbine engine 有权涡轮发动机转子组件，涡轮组件及其组装方法
公开(公告)号：JP2012246918A
公开(公告)日：2012-12-13
申请号：JP2012101927
申请日：2012-04-27
Inventor： SUCIU GABRIEL L , ALVANOS IOANNIS , MERRY BRIAN D
IPC: F01D5/06 , F01D5/12 , F01D5/28 , F01D11/02 , F01D25/00 , F02C7/00 , F02C7/28 , F04D29/02 , F04D29/12 , F04D29/32 , F04D29/34 , F04D29/38
CPC classification number: F01D5/34 , C04B37/001 , C04B2237/38 , C04B2237/76 , C04B2237/84 , F01D5/282 , F01D5/284 , F01D11/001 , F05D2300/6033 , Y10T29/4932
Abstract: PROBLEM TO BE SOLVED: To provide an integrated rotor module that decreases hardware complexity and weight.SOLUTION: A rotor module 62 disposed in a low-pressure turbine 46 includes CMC airfoils 64A, 64B, and 64C, a CMC drum 66, vanes 68A, 68B, and a split case 60 respectively made of a ceramic composite material. The CMC airfoils 64A, 64B, and 64C form a multiple of rows and extend from the common CMC drum. The CMC airfoils 64A, 64B, and 64C are alternately arranged with the CMC vanes 68A, 68B. The rotor module 62 has a mount 70. The mount 70 extends radially inwardly from the central-axis position extending in the axial direction of the common drum 66 adjacent to the airfoil row 68B and integrally mounts the rotor module 62 to an inner shaft 40. The rotor module 62 further includes an independent feature such as a knife edge seal 72.
Abstract translation: 要解决的问题：提供降低硬件复杂性和重量的集成转子模块。 解决方案：设置在低压涡轮机46中的转子模块62包括分别由陶瓷复合材料制成的CMC翼型件64A，64B和64C，CMC滚筒66，叶片68A，68B和分体式壳体60。 CMC翼型件64A，64B和64C形成多个行并从公共的CMC滚筒延伸。 CMC翼片64A，64B和64C与CMC叶片68A，68B交替布置。 转子模块62具有安装件70.安装件70从与翼型件排68B相邻的公共鼓66的轴向延伸的中心轴位置径向向内延伸，并将转子模块62整体地安装在内轴40上。 转子模块62还包括诸如刀刃密封件72的独立特征。版权所有：（C）2013，JPO＆INPIT
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公开(公告)号：JP2006348931A
公开(公告)日：2006-12-28
申请号：JP2005338031
申请日：2005-11-24
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , NORRIS JAMES W
Abstract: PROBLEM TO BE SOLVED: To increase efficiency by compensating for a reduction in the cross section of the flow passage of a compressor. SOLUTION: A turbine engine comprises a rotor stack 32 having vane stages 38A to I and blade disks 34A to I. The disks support the blade stages 36A to I. Spacers 62A to H connect the adjacent disks 34A to I in pairs to each other to transmit a compressive force. Recessed parts of the spacers 62B to H compensate for a reduction in the cross section of the flow passage. The spacers 62 exclude loss heat transfer during air recirculation by cavities between the outer disks. Joints 66C to H on the radial inner side of the spacers 62C to H comprise a first annular structural part extending from the forward disks to the rear and a second annular structural part extending from the backward disks to the front, and transmit torque. An anti-vortex tube 100 between the disks 34G and 34H is fitted to a joint 66G, leads air stream on the radial inner side to a spacer 67G, maintains a specified disk temperature characteristic, and controls a thermo/mechanical stress. COPYRIGHT: (C)2007,JPO&INPIT
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公开(公告)号：JP2013181540A
公开(公告)日：2013-09-12
申请号：JP2013038265
申请日：2013-02-28
Inventor： SUCIU GABRIEL L , MERRY BRIAN D
CPC classification number: F02C3/107 , F01D1/26 , F01D25/162 , F02C3/067 , F02C7/06 , F02C7/36 , F02K3/072 , F05D2250/36 , F05D2250/44 , F05D2260/4031 , F05D2260/40311 , Y02T50/671
Abstract: PROBLEM TO BE SOLVED: To shorten a low shaft of an engine while increasing output density of the engine.SOLUTION: A gas turbine engine 20 includes a shaft 40, a counter-rotating low-pressure compressor 60, and a counter-rotating low-pressure turbine 62. The counter-rotating low-pressure turbine 62 includes inside blade sets 120 which are connected to a low shaft 40 via a gear device 116, and an outside blade set 122 which is inserted between the inside blade sets 120. The outside blade set 122 is rotated on a rotation axis in a direction opposite to the inside blade set 120 at a speed lower than the speed of the inside blade set 120. This configuration shortens the overall length of the engine 20, and makes the engine 20 have a desirable high-pressure core ratio, while maximizing the output density of the engine.
Abstract translation: 要解决的问题：缩短发动机的低轴，同时增加发动机的输出密度。解决方案：燃气涡轮发动机20包括轴40，反向旋转低压压缩机60和反向旋转低压压缩机60， 反向旋转的低压涡轮62包括通过齿轮装置116连接到低轴40的内部叶片组120和插入在内侧叶片组120之间的外部叶片组122。 刀片组122以比内侧刀片组120的速度低的速度在旋转轴线上以与内侧刀片组120相反的方向旋转。该构造缩短了发动机20的总长度，并且使发动机20具有 期望的高压芯比，同时使发动机的输出密度最大化。
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Patent Agency Ranking
公开(公告)号：JP2013139782A
公开(公告)日：2013-07-18
申请号：JP2012278774
申请日：2012-12-21
Inventor： SUCIU GABRIEL L , MERRY BRIAN D , DYE CHRISTOPHER M , JOHNSON STEVEN B , SCHWARZ FREDERICK M
Abstract: PROBLEM TO BE SOLVED: To provide a gas turbine engine arrangement in an engine mounting structure for mounting a turbo fan gas turbine engine to an aircraft pylon.SOLUTION: The gas turbine engine includes a spool which drives a gear train along an engine center axis, wherein the spool includes a low pressure compressor with 4 to 8 stages.
Abstract translation: 要解决的问题：提供一种用于将涡轮风扇燃气涡轮发动机安装到飞机塔架的发动机安装结构中的燃气涡轮发动机装置。解决方案：燃气涡轮发动机包括沿发动机中心轴驱动齿轮系的线轴， 其中所述线轴包括具有4至8级的低压压缩机。
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公开(公告)号：JP2003148104A
公开(公告)日：2003-05-21
申请号：JP2002326472
申请日：2002-11-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , BABU MICHAEL , MURDOCK JAMES R
Abstract: PROBLEM TO BE SOLVED: To reduce engine weight of a turbine engine. SOLUTION: The blade 203 for the turbine engine having a center line includes a root part extended at a certain angle with respect to the center line and an air foil part 215 extended from the root part. The root part is directly adjacent to the air foil part 215. Namely, the blade 203 has no neck part. The blade 203 is part of the rotor assembly, and preferably, it is a fan blade.
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公开(公告)号：JP2014234822A
公开(公告)日：2014-12-15
申请号：JP2014042229
申请日：2014-03-05
Applicant: ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation , United Technologies Corp
, ユナイテッド テクノロジーズ コーポレイションUnited Technologies Corporation Inventor： MCCUNE MICHAEL E , JASON HUSBAND , FREDERICK M SCHWARZ , DANIEL BERNARD KUPRATIS , SUCIU GABRIEL L , WILLIAM K ACKERMANN
CPC classification number: F01D25/16 , F02C7/36 , F02K3/06 , F05D2260/40311 , Y02T50/671
Abstract: 【課題】歯車の噛合部における整列のずれを防止しつつ、エンジンの効率を向上させる。【解決手段】ガスタービンエンジン20が、ファン42を駆動するファンシャフト76と、このファンシャフト76を支持するフレーム82と、ファンシャフト76を駆動する複数の歯車とを備えている。可撓性支持部78が、複数の歯車を少なくとも部分的に支持する。第1のタービンセクション46は、第1の出口点401において第1の出口面積を有するとともに、第1の速度で回転する。第2のタービンセクション54は、第2の出口点400において第2の出口面積を有するとともに、第1の速度よりも高速の第2の速度で回転する。第1の性能量が、第1の速度の二乗と第1の出口面積との積として定義される。第2の性能量が、第2の速度の二乗と第2の出口面積との積として定義される。第2の性能量に対する第1の性能量の比は、約0.5〜約1.5である。【選択図】図1D
Abstract translation: 要解决的问题：为了防止齿轮啮合网格的错位，提高发动机效率。解决方案：燃气轮机发动机20具有驱动风扇42的风扇轴76，支撑风扇轴76的框架82和多个齿轮 驱动风扇轴76.柔性支撑件78至少部分支撑多个齿轮。 第一涡轮机部分46在第一出口点401处具有第一出口区域并以第一速度旋转。 第二涡轮部分54在第二出口点处具有第二出口区域，并以比第一速度快的第二速度旋转。 第一性能数量被定义为第一速度平方和第一出口区域的乘积。 第二性能量被定义为第二速度平方和第二出口区的乘积。 第一性能量与第二性能量的比率在约0.5至约1.5之间。
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公开(公告)号：JP2012246925A
公开(公告)日：2012-12-13
申请号：JP2012119126
申请日：2012-05-25
Inventor： ALVANOS IOANNIS , SUCIU GABRIEL L
IPC: F01D5/28 , F01D5/02 , F01D5/12 , F01D5/20 , F01D9/02 , F01D9/04 , F01D11/02 , F01D11/08 , F01D25/00 , F02C7/00 , F02C7/28
CPC classification number: F01D5/282 , F01D5/066 , F01D5/284 , F01D5/34 , F01D11/001 , F05D2300/6033
Abstract: PROBLEM TO BE SOLVED: To provide an additional disk for a gas turbine engine.SOLUTION: CMC disks 64A, 64B and 64C for a gas turbine engine 20 include CMC hubs 68A, 68B and 68C defined about an axis, and a plurality of CMC airfoils 66A, 66B and 66C integrated with the respective CMC hubs. The CMC disks 64A, 64B and 64C for the gas turbine engine 20 include the plurality of CMC airfoils 66A, 66B and 66C integrated with the respective CMC hubs 68A, 68B and 68C, and rails 80A, 80C integrated with the respective CMC hubs on sides opposite to the plurality of airfoils. The rails define rail platforms adjacent to the plurality of airfoils and tapered to a rail inner bore.
Abstract translation: 要解决的问题：提供用于燃气涡轮发动机的附加盘。 解决方案：用于燃气涡轮发动机20的CMC盘64A，64B和64C包括围绕轴限定的CMC轮毂68A，68B和68C以及与各个CMC轮毂一体化的多个CMC翼型66A，66B和66C。 用于燃气涡轮发动机20的CMC盘64A，64B和64C包括与相应的CMC集线器68A，68B和68C一体化的多个CMC翼型66A，66B和66C，以及与侧面上的相应CMC轮毂一体化的轨道80A，80C 与多个翼型件相对。 导轨限定与多个翼型件相邻的轨道平台并且逐渐变细到轨道内孔。 版权所有（C）2013，JPO＆INPIT
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10.发明专利Inlet guide vane flap, fan section, and control method for variable-shape inlet guide vane flap system 有权入口指南VANE FLAP，风扇部分和可变形导向导叶片系统的控制方法
公开(公告)号：JP2011132963A
公开(公告)日：2011-07-07
申请号：JP2011083273
申请日：2011-04-05
Inventor： LORD WESLEY K , SHARMA OM P , DYE CHRISTOPHER , SUCIU GABRIEL L
IPC: F04D29/56
CPC classification number: F01D5/146 , F01D5/148 , F01D17/162 , F04D29/563 , F05B2240/311 , F05D2240/12 , Y02T50/673
Abstract: PROBLEM TO BE SOLVED: To provide an inlet guide vane flap with increased partial-speed operability and flutter margin, thus avoiding fan rotor mistuning at particular operational conditions. SOLUTION: A variable-shape inlet guide vane (IGV) system 46 includes the variable-shape inlet guide vane flap 48 provided with a flexible part 64 that enables the desired spanwise distribution of axial velocities Cx, α, and β at an inlet of the fan rotor 30. The flexible part 64 is formed of a flexible material such as silicone rubber combined with internal reinforcing fibers or filaments. The form of the flap 48 is not symmetric, but twisted during actuation from the maximum opening position to the maximum closed position. COPYRIGHT: (C)2011,JPO&INPIT
Abstract translation: 要解决的问题：提供具有增加的部分速度可操作性和颤振余量的入口导向叶片翼片，从而避免在特定操作条件下风扇转子失谐。 解决方案：可变形入口引导叶片（IGV）系统46包括设置有柔性部分64的可变形入口导向叶片翼片48，其能够在轴向速度Cx，α和β处产生期望的翼展方向分布 风扇转子30的入口。柔性部分64由诸如与内部增强纤维或细丝组合的硅橡胶的柔性材料形成。 翼片48的形状不是对称的，而是在从最大打开位置到最大关闭位置的致动期间扭转。 版权所有（C）2011，JPO＆INPIT
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