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1.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：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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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：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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Patent Agency Ranking
公开(公告)号：JP2013181542A
公开(公告)日：2013-09-12
申请号：JP2013038267
申请日：2013-02-28
Inventor： SUCIU GABRIEL L , MERRY BRIAN D , MCCUNE MICHAEL E , MAGGE SHANKAR S
CPC classification number: F02C3/107 , F01D1/26 , F02C3/067 , F02C7/36 , F02K3/072 , F05D2250/44 , 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 low 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 the 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 fixed to an outside rotor 126; a front end of the outside rotor 126 is supported on a central turbine frame 134 by a bearing 150; and a rear end of the outside rotor 126 is supported on the low shaft 40 by the bearing 152. In addition, the gear device 116 comprises a sun gear 140, a splitter gear 142 which is meshed with the sun gear 140, and a ring gear 148 which is meshed with the splitter gear 142.
Abstract translation: 要解决的问题：在增加发动机的输出密度的同时缩短发动机的低轴。解决方案：燃气涡轮发动机20包括低轴40，反向旋转低压压缩机60和反向旋转 低压涡轮机62.反向旋转的低压涡轮机62包括通过齿轮装置116连接到低轴40的内部叶片组120和插入在内部叶片组120之间的外部叶片组122。 外侧刀片组122固定在外侧转子126上; 外转子126的前端由轴承150支撑在中心涡轮机框架134上; 并且外转子126的后端由轴承152支撑在低轴40上。此外，齿轮装置116包括太阳齿轮140，与太阳齿轮140啮合的分动齿轮142和环 与分动齿轮142啮合的齿轮148。
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公开(公告)号：JP2013139798A
公开(公告)日：2013-07-18
申请号：JP2012280501
申请日：2012-12-25
Inventor： SUCIU GABRIEL L , MERRY BRIAN D , DYE CHRISTOPHER M , JOHNSON STEVEN B , SCHWARZ FREDERICK M
CPC classification number: F02C3/107 , B64D27/26 , B64D33/04 , F02K1/09 , F02K1/72 , F02K1/763 , F02K3/075 , F05D2240/50
Abstract: PROBLEM TO BE SOLVED: To provide a gas turbine engine which has a low stage count low-pressure turbine.SOLUTION: A gas turbine engine includes a spool which drives a gear train along an engine center axis, wherein the spool includes the low-pressure turbine with 3 to 6 stages.
Abstract translation: 要解决的问题：提供一种具有低阶数低压涡轮机的燃气涡轮发动机。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阀芯，其中阀芯包括低压 涡轮机3〜6级。
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8.发明专利Turbine exhaust case of gas turbine engine, and method of assembling gas turbine engine 审中-公开气体涡轮发动机涡轮机排气装置及组装气体涡轮发动机的方法
公开(公告)号：JP2012246921A
公开(公告)日：2012-12-13
申请号：JP2012116114
申请日：2012-05-22
Inventor： SUCIU GABRIEL L , ALVANOS IOANNIS , MERRY BRIAN D
IPC: F02C7/00
CPC classification number: F02C7/20 , F01D9/041 , F01D25/30 , F02K1/04 , F05D2300/6033 , Y02T50/672 , Y02T50/673 , Y10T29/4932
Abstract: PROBLEM TO BE SOLVED: To reduce weight and cost of a gas turbine engine.SOLUTION: A turbine exhaust case (70) of the gas turbine engine includes a plurality of CMC (ceramic matrix composite) turbine exhaust case struts (72) between a CMC core nacelle aft portion (76) and a CMC tail cone (74).
Abstract translation: 要解决的问题：减少燃气轮机的重量和成本。 燃气涡轮发动机的涡轮机排气箱（70）包括CMC核心机舱后部（76）和CMC尾锥（CMC）之间的多个CMC（陶瓷基体复合）涡轮机排气外壳支柱（72） 74）。 版权所有（C）2013，JPO＆INPIT
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9.发明专利Ceramic matrix composite airfoil segment for gas turbine engine, ceramic matrix composite structure, and method for assembling the ceramic matrix composite structure 审中-公开用于气体涡轮发动机的陶瓷基体复合材料分段，陶瓷基体复合结构以及组装陶瓷基体复合结构的方法
公开(公告)号：JP2012246917A
公开(公告)日：2012-12-13
申请号：JP2012099336
申请日：2012-04-25
Inventor： BERCZIK DOUGLAS M , SUCIU GABRIEL L , MERRY BRIAN D , ALVANOS IOANNIS , DYE CHRISTOPHER M
CPC classification number: F01D5/282 , C04B37/00 , C04B2235/5244 , C04B2237/365 , C04B2237/38 , C04B2237/76 , F01D5/147 , F01D5/284 , F01D9/041 , F01D25/246 , F05D2240/12 , F05D2300/6033 , Y10T29/49321
Abstract: PROBLEM TO BE SOLVED: To provide a geometry that provides continuity to fibers of a ceramic matrix composite material, and to maximize the strength per weight.SOLUTION: In each structure of the air foil segments 82, the box-shape ceramic-matrix-composite-fiber geometry 98 is used. Each of the ceramic matrix composite airfoil segments 82 defines a rectilinear pressure side bond line 100P and a rectilinear suction side bond line 100S on a circumferential segment of the ceramic matrix composite airfoil segments 82 to maintain aerodynamic performance and provide a strong bonding part. The rectilinear pressure side bond line 100P and the rectilinear suction side bond line 100S approximately align with a front edge 84L, a rear edge 84T, and respective platforms 90, 92.
Abstract translation: 要解决的问题：提供为陶瓷基质复合材料的纤维提供连续性并使每重量的强度最大化的几何形状。 解决方案：在翼片段82的每个结构中，使用箱形陶瓷基复合纤维几何形状98。 陶瓷基复合翼型段82中的每一个在陶瓷基体复合翼型段82的周向段上限定直线压力侧接合线100P和直线吸力侧接合线100S，以保持空气动力学性能并提供强结合部分。 直线侧压接侧线接合线100P和直线吸引侧接合线100S大致与前缘84L，后缘84T以及各平台90,92对准。（C）2013，JPO＆INPIT
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10.发明专利Disk, ceramic matrix composite disk and rotor module for gas turbine engine 有权磁盘，陶瓷基体复合材料盘和转子发动机转子模块
公开(公告)号：JP2012246916A
公开(公告)日：2012-12-13
申请号：JP2012099335
申请日：2012-04-25
Inventor： ALVANOS IOANNIS , SUCIU GABRIEL L , MERRY BRIAN D , DYE CHRISTOPHER M
Abstract: PROBLEM TO BE SOLVED: To provide a disk that has self-retention capability in order to maintain the balance of circumferential stress.SOLUTION: Airfoils 66A, 66C define rails 80A, 80C. Respective contours of the rails 80A, 80C define an innermost bore radius B of a rail inner bore 82. That is, the rails 80A, 80C are relatively axially wide at rail platforms 84 of the contours adjacent the airfoils 66A, 66C and inclined toward the rail inner bore 82. The rail inner bore 82 defines an axial thickness of 1y while the rail platforms 84 define axial thicknesses of 1y to 6y.
Abstract translation: 要解决的问题：为了提供具有自保持能力的盘，以便保持圆周应力的平衡。 解决方案：翼片66A，66C限定轨道80A，80C。 轨道80A，80C的相应轮廓限定轨道内孔82的最内孔半径B.即，轨道80A，80C在与翼型件66A，66C相邻的轮廓的轨道平台84处相对轴向宽，并朝向 轨道内孔82.轨道内孔82限定1y的轴向厚度，而轨道平台84限定1y至6y的轴向厚度。 版权所有（C）2013，JPO＆INPIT
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