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111.发明授权Controllable speed windmill operation of a gas turbine engine through low spool power extraction 有权通过低阀芯功率提取，可控风力发电机运行的燃气轮机公开(公告)号：US08966876B2
公开(公告)日：2015-03-03
申请号：US13278317
申请日：2011-10-21
CPC分类号： F02C9/16 , F02C3/107 , F02C7/32 , F05D2270/091 , Y02T50/671 , Y10T477/40 , Y10T477/45
摘要： A gas turbine engine according to an exemplary aspect of the present disclosure includes, among other things, a fan section including a fan, a geared architecture, a spool which drives the fan through the geared architecture, and at least one component geared to the spool and being operable to control a speed of the spool during a “windmilling” condition. A method of gas turbine engine operations during a “windmilling” condition is also disclosed.
摘要翻译： 根据本公开的示例性方面的燃气涡轮发动机尤其包括风扇部分，其包括风扇，齿轮架构，通过齿轮架构驱动风扇的阀芯，以及至少一个齿轮组件 并且可操作以在“风车”状态期间控制阀芯的速度。 还公开了在“风车”状态期间的燃气轮机发动机操作的方法。
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公开(公告)号：US08807477B2
公开(公告)日：2014-08-19
申请号：US13340969
申请日：2011-12-30
申请人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
发明人： Gabriel L. Suciu , Brian D. Merry , Christopher M. Dye , Steven B. Johnson , Frederick M. Schwarz
IPC分类号： B64D29/00
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266
摘要： A gas turbine engine includes a fan section and a low spool that includes a low pressure compressor section. The low pressure compressor section includes eight (8) or less stages. A high spool includes a high pressure compressor section that has between eight to fifteen (8-15) stages. An overall compressor pressure ratio is provided by the combination of the low pressure compressor section and the high pressure compressor. A gear train is defined along an engine centerline axis. The low spool is operable to drive the fan section through the gear train.
摘要翻译： 燃气涡轮发动机包括风扇部分和包括低压压缩机部分的低阀芯。 低压压缩机部分包括八（8）个或更少的阶段。 高阀芯包括高压压缩机部分，其具有8至15（8-15）级。 整体压缩机压力比由低压压缩机部分和高压压缩机的组合提供。 齿轮系沿发动机中心线定义。 低阀芯可操作以通过齿轮系驱动风扇部分。
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公开(公告)号：US08784062B2
公开(公告)日：2014-07-22
申请号：US13283710
申请日：2011-10-28
CPC分类号： F01D5/02 , F01D5/022 , F01D5/025 , F01D5/027 , F01D5/066 , F01D5/14 , F01D5/147 , F01D11/006 , F05D2240/20 , F05D2260/15 , Y10T29/49316 , Y10T29/4932
摘要： A spacer for a gas turbine engine includes a rotor ring defined along an axis of rotation, the rotor ring defines a forward circumferential flange which defines a first thickness and an aft circumferential flange which defines a second thickness, the first thickness different than the second thickness. A plurality of core gas path seals which extend from the rotor ring opposite the ramped interface.
摘要翻译： 用于燃气涡轮发动机的间隔件包括沿着旋转轴线限定的转子环，转子环限定限定第一厚度的前周向凸缘和限定第二厚度的后周向凸缘，第一厚度不同于第二厚度 。 多个核心气体路径密封件，其从转子环延伸，与斜坡界面相对。
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公开(公告)号：US08684303B2
公开(公告)日：2014-04-01
申请号：US13340940
申请日：2011-12-30
IPC分类号： B64D29/00
CPC分类号： B64D27/26 , B64D2027/264 , B64D2027/266
摘要： 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 (4) stages.
摘要翻译： 燃气涡轮发动机包括沿着发动机中心轴线驱动齿轮系的线轴，所述线轴包括具有四（4）级的低压压缩机。
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115.发明授权Systems and methods involving multiple torque paths for gas turbine engines 有权涉及用于燃气涡轮发动机的多个扭矩路径的系统和方法公开(公告)号：US08621871B2
公开(公告)日：2014-01-07
申请号：US13466745
申请日：2012-05-08
摘要： Systems and methods involving multiple torque paths of gas turbine engines are provided. In this regard, a representative method for reducing overspeed potential of a turbine of a gas turbine engine includes: providing a first load to the turbine via a first torque path; providing a second load to the turbine via a second torque path; and operating the turbine such that: mechanical failure of a component defining at least a portion of the first torque path does not inhibit the second load from being applied to the turbine via the second torque path; and mechanical failure of a component defining the second torque path does not inhibit the first load from being applied to the turbine via the first torque path.
摘要翻译： 提供了涉及燃气涡轮发动机的多个扭矩路径的系统和方法。 在这方面，用于降低燃气涡轮发动机的涡轮机的超速电位的代表性方法包括：经由第一扭矩路径向涡轮机提供第一负载; 经由第二扭矩路径向所述涡轮机提供第二负载; 并且操作所述涡轮机，使得限定所述第一扭矩路径的至少一部分的部件的机械故障不阻止所述第二负载经由所述第二扭矩路径施加到所述涡轮机; 并且限定第二扭矩路径的部件的机械故障不阻止第一负载经由第一扭矩路径施加到涡轮机。
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公开(公告)号：US20130259672A1
公开(公告)日：2013-10-03
申请号：US13435134
申请日：2012-03-30
摘要： A gas turbine engine case structure includes inner and outer annular case portions radially spaced from one another to provide a flow path and circumferentially arranged airfoils extend radially and interconnect the inner and outer annular case portions. The airfoils include multiple vanes and multiple strut-vanes. Each vane has a vane leading edge. Each strut-vane includes a strut-vane leading edge. The vane leading edges and strut-vane leading edges are aligned in a common plane. The vanes include a first axial length and the strut-vanes include a second axial length that is at least double the first axial length.
摘要翻译： 燃气涡轮发动机壳体结构包括彼此径向间隔开的内部和外部环形壳体部分，以提供流动路径，并且周向布置的翼型件径向延伸并且互连内部和外部环形壳体部分。 翼型件包括多个叶片和多个支柱叶片。 每个叶片都有一个叶片前缘。 每个支柱叶片包括支柱叶片前缘。 叶片前缘和支柱叶片前缘在公共平面对齐。 叶片包括第一轴向长度，支柱叶片包括至少是第一轴向长度的两倍的第二轴向长度。
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公开(公告)号：US20130239588A1
公开(公告)日：2013-09-19
申请号：US13419649
申请日：2012-03-14
CPC分类号： F02C7/14 , F01D25/12 , F02C7/224 , F02K3/06 , F04D29/5826 , F05D2250/36
摘要： An engine includes a duct containing a flow of cool air and a pump system having an impeller with an inlet for receiving air from the duct and an outlet for discharging air into a discharge manifold. The discharge manifold containing at least one heat exchanger which forms part of a thermal management system.
摘要翻译： 发动机包括含有冷空气流的管道和具有叶轮的泵系统，叶轮具有用于从管道接收空气的入口和用于将空气排放到排放歧管中的出口。 排放歧管包含形成热管理系统的一部分的至少一个热交换器。
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公开(公告)号：US20130239582A1
公开(公告)日：2013-09-19
申请号：US13419660
申请日：2012-03-14
IPC分类号： F02C6/08
摘要： 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.
摘要翻译： 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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119.发明申请COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO TURBINE EXHAUST CASE 有权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：US20130223992A1
公开(公告)日：2013-08-29
申请号：US13408281
申请日：2012-02-29
申请人： Gabriel L. Suciu , Brian D. Merry
发明人： Gabriel L. Suciu , Brian D. Merry
IPC分类号： F01D15/12
CPC分类号： F02C7/36 , F01D1/26 , F01D1/28 , F01D15/12 , F02C3/067 , F02C3/107 , F02C7/06 , F02K3/068 , F02K3/072 , F05D2260/40311 , F05D2260/53 , Y02T50/671
摘要： A gas turbine engine includes a shaft defining an axis of rotation. An inner rotor directly drives the shaft and includes an inner set of blades. An outer rotor has an outer set of blades interspersed with the inner set of blades. The outer rotor is configured to rotate in an opposite direction about the axis of rotation from the inner rotor. A gear system couples the outer rotor to the shaft and is configured to rotate the inner set of blades at a lower speed than the outer set of blades.
摘要翻译： 燃气涡轮发动机包括限定旋转轴线的轴。 内转子直接驱动轴并且包括内部一组叶片。 外转子具有与内组叶片分开的外组叶片。 外转子构造成围绕与内转子的旋转轴线相反的方向旋转。 齿轮系统将外转子连接到轴，并且构造成以比外部组叶片更低的速度旋转内组叶片。
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公开(公告)号：US20130223983A1
公开(公告)日：2013-08-29
申请号：US13408229
申请日：2012-02-29
CPC分类号： F02C3/107 , F01D1/26 , F02C3/067 , F02C7/36 , F02K3/072 , F05D2250/44 , F05D2260/40311 , Y02T50/671
摘要： A gas turbine engine includes a shaft defining an axis of rotation. An outer turbine rotor directly drives the shaft and includes an outer set of blades. An inner turbine rotor has an inner set of blades interspersed with the outer set of blades. The inner turbine rotor is configured to rotate in an opposite direction about the axis of rotation from the outer turbine rotor. A splitter gear system couples the inner turbine rotor to the shaft and is configured to rotate the inner set of blades at a faster speed than the outer set of blades.
摘要翻译： 燃气涡轮发动机包括限定旋转轴线的轴。 外涡轮转子直接驱动轴并且包括外部一组叶片。 内部涡轮转子具有与外部组叶片交替散布的内部一组叶片。 内涡轮转子被构造成围绕与外涡轮转子的旋转轴线相反的方向旋转。 分动齿轮系统将内涡轮转子与轴连接，并且构造成以比外套叶片更快的速度旋转内组叶片。
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