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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：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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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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4.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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5.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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Patent Agency Ranking6.发明申请
公开(公告)号：WO2013180789A3
公开(公告)日：2014-01-23
申请号：PCT/US2013030125
申请日：2013-03-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , GLAHN JORN A , MERRY BRIAN D , DYE CHRISTOPHER M
CPC classification number: F01D15/08 , F02C3/10 , F02C6/04 , F02C6/08 , F02C7/14 , F02C7/32 , F02C9/16 , Y02T50/671
Abstract: An engine includes a duct containing a flow of cool air and a pump system for providing air to an environmental control system. The pump system has an impeller having an inlet for receiving cool air from the duct and an outlet for discharging air to the environmental control system.
Abstract translation: 发动机包括含有冷空气流的管道和用于向环境控制系统提供空气的泵系统。 泵系统具有叶轮，其具有用于从管道接收冷空气的入口和用于将空气排放到环境控制系统的出口。
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公开(公告)号：WO2013180788A2
公开(公告)日：2013-12-05
申请号：PCT/US2013030123
申请日：2013-03-11
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , MERRY BRIAN D , GLAHN JORN A , DYE CHRISTOPHER M
Abstract: A gas turbine engine has an impeller pump for delivering air to an environmental control system and a speed control pump connected to the impeller pump for driving the impeller pump at a constant speed.
Abstract translation: 燃气涡轮发动机具有用于将空气输送到环境控制系统的叶轮泵和连接到叶轮泵的速度控制泵，用于以恒定速度驱动叶轮泵。
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公开(公告)号：RU2747543C1
公开(公告)日：2021-05-06
申请号：RU2019113285
申请日：2012-12-31
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , MERRY BRIAN D , DYE CHRISTOPHER M , JOHNSON STEVEN B , SCHWARZ FREDERICK M
Abstract: Газотурбинныйдвигательсогласноодномуиллюстративномуаспектунастоящегоизобретениясодержитредуктор, расположенныйвдольпродольнойосидвигателя, икаскад, которыйрасположенвдольуказаннойпродольнойосидвигателяи приводитв действиередуктор, приэтомуказанныйкаскадсодержиттурбинунизкогодавленияс небольшимчисломступеней. Вследующемнеограничительномпримереодногоизвышеуказанныхвариантовосуществлениягазотурбинногодвигателянебольшоечислоступенейможетсоставлятьоттрехдошести (3-6) ступеней. Дополнительноилиальтернативно, небольшоечислоступенейможетсоставлятьтри (3) ступени. Дополнительноилиальтернативно, небольшоечислоступенейможетсоставлятьпять (5) илишесть (6) ступеней. Достигаетсяполучениелегкойи эффективнофункционирующейконструкциидвигателяи обеспечениевысокогополетногоКПД. 14 з.п. ф-лы, 15 ил.
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公开(公告)号：BR102012028940A2
公开(公告)日：2015-10-06
申请号：BR102012028940
申请日：2012-11-12
Applicant: UNITED TECHNOLOGIES CORP
Inventor： MERRY BRIAN D , DYE CHRISTOPHER M , SCHWARZ FREDERICK M , SUCIU GABRIEL L , JOHNSON STEVEN B
Abstract: motor de turbina a gás. é descrito um motor de turbina a gás que inclui um eixo do conjunto compressor-turbina ao longo de um eixo geométrico da linha central do motor que aciona um trem de engrenagem, o dito eixo do conjunto compressor-turbina inclui um compressor de baixa pressão com quatro a oito (4-8) estágios
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公开(公告)号：CA2800001C
公开(公告)日：2015-10-13
申请号：CA2800001
申请日：2012-12-21
Applicant: UNITED TECHNOLOGIES CORP
Inventor： SUCIU GABRIEL L , MERRY BRIAN D , DYE CHRISTOPHER M , JOHNSON STEVEN B , SCHWARZ FREDERICK M
Abstract: A gas turbine engine includes a spool along an engine centerline axis which drives a gear train, said spool includes a low pressure compressor with four to eight (4-8) stages.
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