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公开(公告)号：EP2730501A3
公开(公告)日：2017-11-15
申请号：EP13192605.7
申请日：2013-11-12
申请人： The Boeing Company
发明人： Moore, Matthew D. , Boren, Kelly L.
CPC分类号： F02K5/00 , B64C11/001 , B64C11/18 , F01D1/24 , F01D5/03 , F01D5/225 , F02K1/44 , F02K1/827 , F02K3/062 , F02K3/072 , F04D29/326 , F05D2260/96 , Y02T50/672 , Y02T50/673 , Y10T137/0536
摘要： A propulsion system and methods are presented. A substantially tubular structure (102) comprises a central axis (104) through a longitudinal geometric center, and a first fan (108) rotates around the central axis, and comprises a first fan hub (110) and first fan blades (112). The fan hub (108) is rotationally coupled to the substantially tubular structure (102), and the first fan blades (112) are coupled to the first fan hub (110) and increase in chord length with increasing distance from the first fan hub (108). A second fan (118) is rotationally coupled to the substantially tubular structure (102) and rotates around the central axis and contra-rotates relative to the first fan (108). Second fan blades (118) are coupled to the second fan hub (120), and a nacelle (124) circumscribing the first fan (108) and the second fan (118) is coupled to and rotates with the first fan (108).
摘要翻译： 介绍了一种推进系统和方法。 大致管状结构（102）包括穿过纵向几何中心的中心轴线（104），并且第一风扇（108）围绕中心轴线旋转，并且包括第一风扇轮毂（110）和第一风扇叶片（112）。 风扇轮毂108旋转地联接到大致管状结构102，并且第一风扇叶片112联接到第一风扇轮毂110并且随着距离第一风扇轮毂110的距离增加而增加弦长。 108）。 第二风扇（118）可旋转地联接到大致管状结构（102）并围绕中心轴线旋转并且相对于第一风扇（108）反转。 第二风扇叶片118联接到第二风扇轮毂120，外接第一风扇108和第二风扇118的机舱124联接到第一风扇108并与第一风扇108一起旋转。
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2.发明公开COUNTER-ROTATING LOW PRESSURE TURBINE WITH GEAR SYSTEM MOUNTED TO TURBINE EXHAUST CASE 审中-公开连续低压管与涡轮排气装置安装的齿轮系统
公开(公告)号：EP2820266A4
公开(公告)日：2015-09-16
申请号：EP13793559
申请日：2013-02-15
发明人： MERRY BRIAN D , SUCIU GABRIEL L
IPC分类号： F02C3/067 , F01D1/24 , F01D15/12 , F01D25/12 , F01D25/16 , F01D25/24 , F01D25/30 , F02C3/107 , F02C7/32 , F02K3/072
CPC分类号： F01D15/12 , F01D1/24 , F01D25/162 , F01D25/30 , F02C3/107 , F02C7/32 , F02K3/072 , Y02T50/671
摘要： 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.
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公开(公告)号：EP1921253A3
公开(公告)日：2014-01-22
申请号：EP07119448.4
申请日：2007-10-29
CPC分类号： F01D1/24 , F01D1/26 , F02C3/067 , F02K3/072 , F05D2260/40311
摘要： A turbine engine assembly (10) is provided. A turbine engine assembly (10) includes a core gas turbine engine (12) includes a high-pressure compressor (18), a combustor (20), and a high-pressure turbine (22). A turbine engine assembly (10) further includes a booster compressor (30) coupled upstream from the core gas turbine engine. A turbine engine assembly (10) further includes an intermediate-pressure turbine (32) coupled to the booster compressor, the intermediate-pressure turbine disposed downstream from the core gas turbine engine. A turbine engine assembly (10) further includes a counter-rotating fan assembly (16) disposed upstream from the booster compressor, the counter-rotating fan assembly includes a first fan assembly (50) configured to rotate in a first direction and a second fan assembly (52) configured to rotate in an opposite second direction. A turbine engine assembly (10) further includes a low-pressure turbine (14) disposed downstream from the intermediate-pressure turbine, the low-pressure turbine configured to drive the counter-rotating fan assembly.
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公开(公告)号：EP2545252A1
公开(公告)日：2013-01-16
申请号：EP11723049.0
申请日：2011-05-31
发明人： MILNER, Glynn
CPC分类号： F01D25/04 , B23K26/32 , B23K26/342 , B23K35/0244 , B23K2101/001 , B23K2103/08 , F01D1/24 , F01D5/005 , F01D5/027 , F05B2260/966 , F05D2260/30 , F16F15/34 , Y10T29/4932
摘要： The invention relates to a system for balancing a movable turbine part (110) of a turbine or of a compressor. The system comprises a balancing weight element (100) with a first hole (101) and a second hole (102) and a fixing element (201). The first hole (101) and the second hole (102) are formed in such a manner that the fixing element (201) is detachably insertable in either the first hole (101) or the second hole (102). The first hole (101) is formed in such a manner that the inserted fixing element (201) in the first hole (101) detachably couples the balancing weight element (100) to the movable turbine part (110) in a spatially fixed position. The second hole (102) is formed in such a manner that the fixing element (201) is receivable in the second hole (102), when the balancing weight element (100) is non-detachably fixed to the movable turbine part (110) in the spatially fixed position.
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公开(公告)号：EP1626002B1
公开(公告)日：2008-06-04
申请号：EP05254610.8
申请日：2005-07-25
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公开(公告)号：EP1655475A1
公开(公告)日：2006-05-10
申请号：EP05255228.8
申请日：2005-08-25
IPC分类号： F02K3/072 , F02C3/067 , F01D1/24 , B64D35/06 , F01D25/16 , F16C17/12 , F16C17/18 , F16C13/00
CPC分类号： F16C17/024 , F01D1/24 , F01D25/16 , F02C3/067 , F02K3/072 , F05D2240/53 , F16C17/18 , F16C2360/23
摘要： A method for assembling a gas turbine engine (10) that includes providing a low-pressure turbine inner rotor (42) configured to rotate in a first direction, providing a low-pressure turbine outer rotor (38) configured to rotate in a second direction that is opposite the first rotational direction, and coupling at least one foil bearing (100) to at least one of the inner and outer rotors to facilitate improving clearance control between a first rotating component and at least one of a second rotating component and a non-rotating component.
摘要翻译： 一种用于组装燃气涡轮发动机（10）的方法，包括提供构造成沿第一方向旋转的低压涡轮机内转子（42），提供低压涡轮机外转子（38），其构造成沿第二方向旋转 其与第一旋转方向相反，并且将至少一个箔片轴承（100）联接到内转子和外转子中的至少一个，以便于改进第一旋转部件与第二旋转部件和非转动部件中的至少一个之间的间隙控制 旋转部件。
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公开(公告)号：EP0563404A4
公开(公告)日：1994-03-23
申请号：EP92921820
申请日：1992-10-21
申请人： NOZU, RIKUROU
发明人： NOZU, RIKUROU
CPC分类号： F01D19/00 , F01D1/24 , F01D1/30 , F01D5/18 , F03B13/142 , F05B2250/33 , F05D2250/33 , Y02E10/32 , Y02E10/38
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公开(公告)号：EP2677638B1
公开(公告)日：2018-04-25
申请号：EP12746744.7
申请日：2012-02-02
申请人： Hitachi Metals, Ltd.
发明人： MITA, Masahiro
摘要： Provided is a motor device capable of suppressing undesired vibrations occurring at the time of starting a motor, by canceling a torque in a motor device system so as to reduce a reaction torque acting on a motor base. The motor device is equipped with a dual axis motor 1 having first and second rotating shafts 10a and 10b projecting at either end, a rotational direction converter 2 having an input shaft 20a to which the torque of the dual axis motor 1 is inputted and an output shaft 20b that outputs the torque by rotating in a direction opposite to that of the input shaft 20a, and a flywheel 3 provided at an end portion of the first rotating shaft 10a, for balancing out the reaction torque acting on the input shaft 20a and the output shaft 20b of the rotational direction converter 2 when the dual axis motor 1 rotates.
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10.发明公开Method and apparatus for model based control for counter-rotating open-rotor gas turbine engine 审中-公开用于反转开式转子燃气涡轮发动机的基于模型的控制的方法和设备
公开(公告)号：EP2623712A3
公开(公告)日：2017-08-09
申请号：EP13154024.7
申请日：2013-02-05
发明人： Lu, Manxue , Carpenter, Sheldon
CPC分类号： F02C9/54 , B64C11/305 , B64D2027/005 , F01D1/24 , F01D7/00 , F02C9/58 , Y02T50/66
摘要： A counter-rotating open-rotor gas turbine engine includes: a forward un-ducted rotor (15) including a plurality of forward rotor blades and including a forward rotor angle actuator (14) for setting blade pitch angles of the plurality of forward rotor blades; an aft un-ducted rotor (13) including a plurality of aft rotor blades and including an aft rotor angle actuator (12) for setting blade pitch angles of the plurality of aft rotor blades; a gas turbine engine (10) driving forward and aft un-ducted rotors and including a fuel actuator (16) for setting the fuel flow to the gas turbine engine; and an open rotor control system (18/20) including, a forward rotor blade pitch angle command (BetaF) electrically connected to the forward rotor angle actuator, an aft rotor blade pitch angle command (BetaA) electrically connected to the aft rotor angle actuator, a fuel flow command (Wf) electrically connected to the fuel actuator, a forward rotor speed feedback signal (Nf), an aft rotor speed feedback signal (Na), and an engine core speed feedback signal or engine pressure ratio signal (EPR). The open rotor control system may include a multiple-input-multiple output (MIMO) control algorithm including a dynamic inverstion approach for at least the forward rotor blade pitch angle command (BetaF), the aft rotor blade pitch angle command (BetaA), the forward rotor speed feedback signal (Nf) and the aft rotor speed feedback signal (Na).
摘要翻译： 反转开式转子燃气涡轮发动机包括：包括多个前向转子叶片并包括前向转子角致动器（14）的前向不导管转子（15），所述前向转子角致动器（14）用于设定多个前向转子叶片 ; 包括多个后转子叶片并且包括用于设定所述多个后转子叶片的叶片倾斜角的后转子角致动器（12）的后部不导管转子（13） （10），所述燃气涡轮发动机（10）驱动前部和后部无管道转子并且包括用于设定到所述燃气涡轮发动机的燃料流量的燃料致动器（16） 和开式转子控制系统（18/20），其包括电连接到所述前转子角致动器的前转子叶片俯仰角命令（BetaF），电连接到所述后转子角致动器的后转子叶片俯仰角命令（BetaA） ，与燃料致动器电连接的燃料流量指令（Wf），前进转子速度反馈信号（Nf），后转子速度反馈信号（Na）以及发动机核心速度反馈信号或发动机压力比信号（EPR） 。 开放式转子控制系统可以包括多输入多输出（MIMO）控制算法，该算法包括用于至少前向转子叶片俯仰角命令（BetaF），后转子叶片俯仰角命令（BetaA）， 正转转速反馈信号（Nf）和后转速反馈信号（Na）。
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