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公开(公告)号：WO2015017041A1
公开(公告)日：2015-02-05
申请号：PCT/US2014/043175
申请日：2014-06-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： MERRY, Brian D. , SUCIU, Gabriel L. , DAVIS, Todd A. , REINHARDT, Gregory E. , DIBENEDETTO, Enzo
IPC: F02K3/04
CPC classification number: F02K3/06 , F01D25/162 , F02C7/06 , F05D2250/232 , F05D2260/40311 , Y02T50/671
Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A first shaft supports a low pressure compressor section that is arranged axially between the inlet case flow path and the intermediate case flow path. A first bearing supports the first shaft relative to the inlet case. A second bearing supports a second shaft relative to the intermediate case. A low pressure compressor hub is mounted to the first shaft. The low pressure compressor hub extends to the low pressure compressor section between the first bearing and the second bearing.
Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 第一轴支撑轴向设置在入口壳体流动路径和中间壳体流动路径之间的低压压缩机部分。 第一轴承相对于入口壳体支撑第一轴。 第二轴承相对于中间壳体支撑第二轴。 低压压缩机毂安装在第一轴上。 低压压缩机毂在第一轴承和第二轴承之间延伸到低压压缩机部分。
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12.发明申请COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO TURBINE EXHAUST CASE 审中-公开带齿轮系统的逆转低压涡轮机安装在涡轮机排气箱
公开(公告)号：WO2013176709A2
公开(公告)日：2013-11-28
申请号：PCT/US2013/026287
申请日：2013-02-15
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： MERRY, Brian D. , SUCIU, Gabriel L.
CPC classification number: F01D15/12 , F01D1/24 , F01D25/162 , F01D25/30 , F02C3/107 , F02C7/32 , F02K3/072 , Y02T50/671
Abstract: A gas turbine engine includes a shaft defining an axis of rotation. An outer rotor directly drives the shaft and includes an outer set of blades. An inner rotor has an inner set of blades interspersed with the outer set of blades. The inner rotor is configured to rotate in an opposite direction about the axis of rotation from the outer rotor. A gear system couples the inner rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.
Abstract translation: 燃气涡轮发动机包括限定旋转轴线的轴。 外转子直接驱动轴并且包括一组外部叶片。 内转子具有与外组叶片交替散布的内组叶片。 内转子构造成围绕与外转子的旋转轴线相反的方向旋转。 齿轮系统将内转子连接到轴，并且构造成以比外部组叶片更快的速度旋转内组叶片。
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公开(公告)号：WO2013147968A1
公开(公告)日：2013-10-03
申请号：PCT/US2013/020462
申请日：2013-01-07
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： MERRY, Brian D. , SUCIU, Gabriel L.
CPC classification number: F01D25/16 , F01D25/162 , F02C7/06 , F02C7/36 , F02K3/04 , F05D2250/19 , F05D2260/40311
Abstract: A gas turbine engine includes a core housing providing a core flowpath. A shaft supports a compressor section arranged within the core flowpath. First and second bearings support the shaft relative to the core housing and are arranged radially inward of and axially overlapping with the compressor section.
Abstract translation: 燃气涡轮发动机包括提供核心流路的芯壳体。 轴支撑设置在核心流路内的压缩机部分。 第一和第二轴承相对于芯壳体支撑轴，并且设置在压缩机部分的径向内侧并与轴向重叠。
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公开(公告)号：WO2013138104A1
公开(公告)日：2013-09-19
申请号：PCT/US2013/029006
申请日：2013-03-05
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SUCIU, Gabriel L. , ALVANOS, Ioannis , MERRY, Brian D.
CPC classification number: F02C7/20 , B64D27/10 , B64D27/26 , B64D2027/262 , B64D2027/266 , F05D2220/323 , F05D2230/60 , F05D2240/90 , Y02T50/44 , Y10T29/49947
Abstract: A method for mounting a gas turbine engine having a compressor section, a combustor section, a turbine section, a pylon and a rear mount bracket, includes positioning the mounting bracket between the gas turbine engine and the pylon. The mounting bracket is connected to the turbine case reacting a least a vertical load, a side load, a thrust load, and a torque load from the gas turbine engine through the mounting bracket. The mounting bracket is attached to the pylon reacting the same loads from the gas turbine engine.
Abstract translation: 一种用于安装具有压缩机部分，燃烧器部分，涡轮部分，塔架和后部安装支架的燃气涡轮发动机的方法，包括将安装支架定位在燃气涡轮发动机和塔架之间。 安装支架连接到涡轮机壳体，使至少垂直载荷，侧向载荷，推力载荷和来自燃气涡轮发动机的转矩载荷通过安装支架反应。 安装支架连接到塔架，使来自燃气涡轮发动机的相同负载反应。
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公开(公告)号：WO2013130296A1
公开(公告)日：2013-09-06
申请号：PCT/US2013/026576
申请日：2013-02-18
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： LORD, Wesley K. , SUCIU, Gabriel L. , EPSTEIN, Alan H. , MCCUNE, Michael E. , MERRY, Brian D.
CPC classification number: F02C7/36 , F01D15/12 , F02C3/06 , F02C3/107 , F05D2220/32 , F05D2220/36 , F05D2240/24 , F05D2240/35 , F05D2240/40 , F05D2240/60 , F05D2260/4031 , F05D2260/40311
Abstract: A gas turbine engine includes a core engine with a compressor section, a combustor and a turbine. The turbine drives an output shaft, and the output shaft drives at least four gears. Each of the at least four gears extends through a drive shaft to drive an associated fan rotor.
Abstract translation: 燃气涡轮发动机包括具有压缩机部分的核心发动机，燃烧器和涡轮机。 涡轮驱动输出轴，输出轴驱动至少四个齿轮。 所述至少四个齿轮中的每一个延伸穿过驱动轴以驱动相关联的风扇转子。
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Patent Agency Ranking
公开(公告)号：WO2015119687A3
公开(公告)日：2015-08-13
申请号：PCT/US2014/064956
申请日：2014-11-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： HILL, James D. , SUCIU, Gabriel L. , MERRY, Brian D. , ALVANOS, Ioannis
Abstract: One exemplary embodiment of this disclosure relates to a gas turbine engine. The engine includes a first rotor disk, a second rotor disk, and a circumferentially segmented seal. The segmented seal engages the first rotor disk and the second rotor disk. The segmented seal further includes a fore surface contacting the first disk, an aft surface contacting the second disk, and a radially outer surface. Further, (1) the aft surface and (2) one of the fore surface and the radially outer surface include perforations to allow fluid to flow through the interior of the segmented seal.
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公开(公告)号：WO2015050619A3
公开(公告)日：2015-04-09
申请号：PCT/US2014/046781
申请日：2014-07-16
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SCHWARZ, Frederick M. , HASEL, Karl L. , MERRY, Brian D.
Abstract: A ratio of an outer diameter of a fan hub at a leading edge of the blades to an outer tip diameter of the blades at the leading edge is greater than or equal to about 0.24 and less than or equal to about 0.38. The fan tip diameter is greater than or equal to about 84 inches (213.36 centimeters) and a fan tip speed is less than or equal to about 1050 ft / second (320.04 meters / second). A bypass ratio, a gear ratio and an AN2 value are also claimed. The fan drive turbine has between three and six stages.
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公开(公告)号：WO2015047489A1
公开(公告)日：2015-04-02
申请号：PCT/US2014/043195
申请日：2014-06-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： MERRY, Brian D. , SUCIU, Gabriel L. , HASEL, Karl L.
CPC classification number: F02C7/36 , F01D25/162 , F02C3/107 , F02C7/06 , F05D2260/40311
Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flow path. A geared architecture is arranged within the inlet case. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged axially between the inlet case flow path and the intermediate case flow path. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.
Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流动路径的入口壳体和中间壳体。 入口箱内设有齿轮架构。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分轴向布置在入口壳体流动路径和中间壳体流动路径之间。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。
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19.发明申请
公开(公告)号：WO2015017042A1
公开(公告)日：2015-02-05
申请号：PCT/US2014/043184
申请日：2014-06-19
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： MERRY, Brian D. , SUCIU, Gabriel L. , BRILLIANT, Lisa I. , ROSE, Becky E. , DONG, Yuan , BALAMUCKI, Stanley J.
IPC: F02C3/13
CPC classification number: F02C9/18 , F01D5/143 , F02K3/075 , F04D19/028 , F04D29/547 , F05D2250/314 , F05D2260/98 , Y02T50/673
Abstract: A gas turbine engine includes a core housing that includes an inlet case and an intermediate case that respectively provide an inlet case flow path and an intermediate case flowpath. A shaft provides a rotational axis. A hub is operatively supported by the shaft. A rotor is connected to the hub and supports a compressor section. The compressor section is arranged in a core flow path axially between the inlet case flow path and the intermediate case flow path. The core flowpath has an inner diameter and an outer diameter. At least a portion of inner diameter has an increasing slope angle relative to the rotational axis. A bearing is mounted to the hub and supports the shaft relative to one of the intermediate case and the inlet case.
Abstract translation: 燃气涡轮发动机包括芯壳体，其包括分别设置入口壳体流动路径和中间壳体流路的入口壳体和中间壳体。 轴提供旋转轴。 轮毂由轴可操作地支撑。 转子连接到轮毂并支撑压缩机部分。 压缩机部分布置在轴向上在入口壳体流动路径和中间壳体流动路径之间的芯流动路径中。 核心流路具有内径和外径。 内径的至少一部分相对于旋转轴具有增加的倾斜角。 轴承安装到轮毂上并相对于中间壳体和入口壳体之一支撑轴。
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公开(公告)号：WO2014164586A1
公开(公告)日：2014-10-09
申请号：PCT/US2014/022936
申请日：2014-03-11
Applicant: UNITED TECHNOLOGIES CORPORATION
Inventor： SUCIU, Gabriel L. , MERRY, Brian D.
CPC classification number: F01D25/162 , B64D27/18 , B64D2027/264 , F01D25/28 , F02C7/20 , Y02T50/44 , Y02T50/671
Abstract: A mounting system for a gas turbine engine includes a low pressure turbine section, a first bearing, a mid-turbine frame, and a rear mount. The first bearing supports at least a portion of the low pressure turbine section. The mid-turbine frame supports the first bearing. The rear mount is connected to the mid-turbine frame and is configured to react loads from the gas turbine engine.
Abstract translation: 用于燃气涡轮发动机的安装系统包括低压涡轮部分，第一轴承，中涡轮机框架和后部安装件。 第一轴承支撑低压涡轮机部分的至少一部分。 中涡轮机架支撑第一轴承。 后部安装件连接到中间涡轮机框架并且被配置为对来自燃气涡轮发动机的负载起反应。
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