公开(公告)号：EP2048325A2

公开(公告)日：2009-04-15

申请号：EP08253007.2

申请日：2008-09-11

申请人： Rolls-Royce plc

发明人： Evans, Dale Edward

IPC分类号： F01D5/14

CPC分类号： F01D5/147 ,  F01D9/042 ,  F01D9/065 ,  F05D2220/3216 ,  F05D2230/60 ,  F05D2240/121 ,  F05D2260/36

摘要： A fan outlet guide vane for a gas turbine engine comprises a generally radially-extending internal structural member and at least one surface member securable in use to the internal structural member so as to define an aerofoil. The gas turbine engine includes an annular first structure and an annular second structure, the second structure being radially outward of the first structure so as to define a duct between them, and in use the internal structural member of the vane is secured between the first structure and the second structure. In a preferred embodiment, the surface member or surface members are secured only to the internal structural member, and not to the first or second structures.

摘要翻译： 一种用于燃气涡轮发动机的风扇出口导向叶片（25）包括大致径向延伸的内部结构构件（32）和至少一个可与内部结构构件（32）一起使用的表面构件（36,38），以便 定义机翼 燃气涡轮发动机包括环形第一结构（21）和环形第二结构（23），第二结构（23）在第一结构的径向外侧，以便在它们之间形成管道，并且在使用中，内部结构构件 叶片（25）的叶片（32）固定在第一结构（21）和第二结构（23）之间。 在优选实施例中，表面构件或表面构件（36,38）仅固定到内部结构构件（32），而不固定到第一或第二结构。

公开(公告)号：EP3056669B1

公开(公告)日：2018-12-26

申请号：EP16155708.7

申请日：2016-02-15

申请人： United Technologies Corporation

发明人： KUPRATIS, Daniel B. ,  SHERIDAN, William G.

IPC分类号： F02C3/107 ,  F02C3/045 ,  F02C7/36 ,  F02K3/06

CPC分类号： F02C6/12 ,  F01D5/02 ,  F01D5/146 ,  F01D5/147 ,  F01D5/225 ,  F01D13/006 ,  F02C3/045 ,  F02C3/06 ,  F02C3/073 ,  F02C3/107 ,  F02C7/36 ,  F02K1/60 ,  F02K1/68 ,  F02K3/00 ,  F02K3/06 ,  F04D29/321 ,  F05D2220/3216 ,  F05D2220/36 ,  F05D2240/24 ,  F05D2240/35 ,  F05D2250/36 ,  F05D2260/4031

摘要： A turbine engine is provided that includes a turbo-compressor and a combustor section. The turbo-compressor includes a compressor section and a turbine section. The combustor section is fluidly coupled between the compressor section and the turbine section. The compressor section includes a first number of stages. The turbine section includes a second number of stages that is different than the first number.

公开(公告)号：EP3269940A1

公开(公告)日：2018-01-17

申请号：EP17180351.3

申请日：2017-07-07

申请人： General Electric Company

发明人： CASAVANT, Matthew Stephen ,  BLACK, Kenneth Damon ,  HANSEN, Christian Michael ,  FLOYD, Donald Earl ,  ADAICKALASAMY, James ,  KLINGLER, Brett Darrick ,  CAO, Khoa Dang ,  BENSON, Kyle Eric ,  PERKINS, Devin Patrick ,  MCCLELLAND, Damian Anthony

IPC分类号： F01D11/18 ,  F01D25/00 ,  F01D25/24 ,  F04D29/52

CPC分类号： F04D29/642 ,  F01D11/18 ,  F01D25/005 ,  F01D25/24 ,  F02C3/04 ,  F04D29/023 ,  F04D29/324 ,  F04D29/522 ,  F04D29/526 ,  F04D29/542 ,  F05D2220/32 ,  F05D2220/3216 ,  F05D2240/12 ,  F05D2260/97 ,  F05D2300/173 ,  F05D2300/174 ,  F05D2300/177 ,  F05D2300/50212

摘要： A gas turbine engine (10) is disclosed having a turbine (16), one or more hydrocarbon gas combustors (34), and a compressor (12). The compressor (12) has a rotor assembly with one or more rotor blade rows (18) extending radially outward from an inner wheel disk (54). The compressor (12) also has a stator assembly with one or more stator vane rows (24) extending radially inward from an inner casing (46) and positioned between adjacent rotor blade rows (18). The inner casing (46) extends circumferentially around the rotor assembly and is constructed from at least one low-alpha metal alloy.

摘要翻译： 公开了一种燃气涡轮发动机（10），其具有涡轮机（16），一个或多个烃气体燃烧器（34）和压缩机（12）。 压缩机（12）具有转子组件，其具有从内轮盘（54）径向向外延伸的一个或多个转子叶片排（18）。 压缩机12还具有定子组件，定子组件具有从内壳体46径向向内延伸并定位在相邻转子叶片排18之间的一个或多个定子叶片排24。 内壳体（46）围绕转子组件圆周地延伸并且由至少一个低α金属合金构成。

公开(公告)号：EP3181884A1

公开(公告)日：2017-06-21

申请号：EP16203771.7

申请日：2016-12-13

申请人： United Technologies Corporation

发明人： TOPOL, David A. ,  MORIN, Bruce L.

IPC分类号： F02K3/06 ,  F02C7/045 ,  F04D29/66

CPC分类号： F02C7/045 ,  F02K3/06 ,  F04D29/666 ,  F04D29/667 ,  F05D2220/3216 ,  F05D2260/40311 ,  F05D2260/96

摘要： A gas turbine engine (20) includes a fan (42), a turbine section (28) having a fan drive turbine rotor (46), and a compressor rotor (44). A gear reduction (48) effects a reduction in a speed of the fan (42) relative to an input speed from the fan drive turbine rotor (46). The compressor rotor (44) has a number of compressor blades in at least half of a plurality of blade rows of the compressor rotor (44). The blades are configured to operate at least some of the time at a rotational speed. The number of compressor blades in the at least half of the blade rows and the rotational speed is such that the following formula holds true for each row of the at least half of the blade rows of the compressor rotor (44): (the number of blades × the rotational speed) / 60s ≥ about 5500 Hz.

摘要翻译： 燃气涡轮发动机（20）包括风扇（42），具有风扇驱动涡轮转子（46）的涡轮部分（28）以及压缩机转子（44）。 齿轮减速器（48）实现风扇（42）的速度相对于来自风扇驱动涡轮转子（46）的输入速度的降低。 压缩机转子（44）在压缩机转子（44）的多个叶片排的至少一半中具有多个压缩机叶片。 叶片构造成以旋转速度中的至少一些时间进行操作。 至少一半叶片排中的压缩机叶片的数量和旋转速度使得对于压缩机转子（44）的叶片排的至少一半的每排适用下列公式：（ 叶片×转速）/ 60s≥约5500 Hz。

公开(公告)号：EP2971598A4

公开(公告)日：2017-04-19

申请号：EP14801625

申请日：2014-02-21

申请人： UNITED TECHNOLOGIES CORP

发明人： DO LOGAN H ,  SYKES RICHARD L

IPC分类号： F01D17/16 ,  F01D9/04 ,  F02C7/04 ,  F02C9/22

CPC分类号： F01D17/12 ,  F01D9/02 ,  F01D17/02 ,  F01D17/162 ,  F02C9/20 ,  F04D27/0246 ,  F05D2220/3216 ,  F05D2240/12 ,  F05D2270/44

摘要： A method of controlling a variable vane assembly includes the steps of sensing a first angular deflection of a first array of variable vanes about a first vane axis, and a second angular deflection of a second array of variable vanes about a second vane axis, the first array of variable vanes axially spaced from the second array of variable vanes, and adjusting the angular deflection of one of the first and second arrays of variable vanes, based on the sensed angular deflections from the other of the first and second arrays of variable vanes. A compressor including the variable vane assembly and a method of operating the variable vane assembly for a compressor are also disclosed.

公开(公告)号：EP3084141A1

公开(公告)日：2016-10-26

申请号：EP14827799.9

申请日：2014-12-04

申请人： Snecma Société Anonyme

发明人： SEBRECHT, Pierre-Alain, Francis, Claude ,  COCHON, Sébastien ,  LANGLOIS, Arnaud

IPC分类号： F01D17/16 ,  F04D29/56

CPC分类号： F01D17/162 ,  F04D29/563 ,  F05D2220/3216 ,  F05D2220/323 ,  F05D2240/12

摘要： The invention relates to a turbine engine compressor, in particular of an aeroplane turboprop or turbofan, including a stator comprising an annular casing and at least one annular row of variable-pitch vanes, each vane comprising a radially external end including a pivot mounted in an opening of the casing and connected by a linking member to a control ring (38) capable of pivoting axially relative to the casing, the linking member comprising a first end attached to the pivot of the vane and a second end comprising a pin inserted in a hole (52, 58) of the control ring (38), characterised in that at least one (58) of the holes (52, 58) of the control ring (38), which is used for inserting the pins of the linking members, has an oblong shape and extends in the circumferential direction such as to enable the pin to move into said oblong hole (58), during the rotation of the control ring (38).

公开(公告)号：EP2971598A2

公开(公告)日：2016-01-20

申请号：EP14801625.6

申请日：2014-02-21

申请人： United Technologies Corporation

发明人： DO, Logan, H. ,  SYKES, Richard, L.

IPC分类号： F01D17/16 ,  F01D9/04 ,  F02C9/22 ,  F02C7/04

CPC分类号： F01D17/12 ,  F01D9/02 ,  F01D17/02 ,  F01D17/162 ,  F02C9/20 ,  F04D27/002 ,  F04D27/0246 ,  F05D2220/3216 ,  F05D2240/12 ,  F05D2250/90 ,  F05D2270/44

摘要： A method of controlling a variable vane assembly includes the steps of sensing a first angular deflection of a first array of variable vanes about a first vane axis, and a second angular deflection of a second array of variable vanes about a second vane axis, the first array of variable vanes axially spaced from the second array of variable vanes, and adjusting the angular deflection of one of the first and second arrays of variable vanes, based on the sensed angular deflections from the other of the first and second arrays of variable vanes. A compressor including the variable vane assembly and a method of operating the variable vane assembly for a compressor are also disclosed.

摘要翻译： 控制可变叶片组件的方法包括以下步骤：感测围绕第一叶片轴线的可变叶片的第一阵列的第一角度偏转和绕第二叶片轴线的可变叶片的第二阵列的第二角度偏转，第一 可变叶片的阵列与第二可变叶片阵列轴向间隔开，并且基于来自第一和第二可变叶片阵列中的另一个的感测的角度偏转来调节可变叶片的第一和第二阵列之一的角度偏转。 还公开了一种包括可变叶片组件的压缩机以及操作用于压缩机的可变叶片组件的方法。

公开(公告)号：EP2880282A1

公开(公告)日：2015-06-10

申请号：EP13827417.0

申请日：2013-07-23

申请人： United Technologies Corporation

发明人： LOCKHART, Eugene ,  WEINSTEIN, Jess A. ,  DUBE, David P.

IPC分类号： F02C7/00 ,  F02C7/20 ,  F02C7/32

CPC分类号： F04D29/542 ,  F01D9/042 ,  F04D29/644 ,  F05D2220/3216 ,  F05D2230/642 ,  F05D2260/36 ,  Y10T29/49245

摘要： A compressor assembly of a gas turbine engine includes a case including at least one opening and a stator assembly supported within the case. A lug assembly is secured to the case and sets a position of the stator assembly relative to the case. The lug assembly includes a lug engaging the stator assembly and a boss extending from the lug through the opening in the case. The boss including a threaded hole receiving a threaded member holding the lug assembly to the case and defines a seat for the threaded member that is spaced apart from an outer surface of the case.

摘要翻译： 燃气涡轮发动机的压缩机组件包括壳体，壳体包括至少一个开口和支撑在壳体内的定子组件。 凸耳组件固定到壳体并且设定定子组件相对于壳体的位置。 凸耳组件包括接合定子组件的凸耳和从凸耳延伸穿过壳体中的开口的凸台。 所述凸台包括螺纹孔，所述螺纹孔容纳将所述凸耳组件保持到所述壳体的螺纹构件并且限定所述螺纹构件的与所述壳体的外表面间隔开的座。

公开(公告)号：EP2859239A2

公开(公告)日：2015-04-15

申请号：EP13742668.0

申请日：2013-04-15

申请人： Snecma

发明人： OBRECHT, Thierry, Jean-Jacques ,  GHILARDI, Céline ,  PERROT, Vincent

IPC分类号： F04D27/02 ,  F04D29/16 ,  F04D29/52 ,  F04D29/54 ,  F04D29/68

CPC分类号： F04D29/526 ,  F04D19/00 ,  F04D29/164 ,  F04D29/541 ,  F04D29/542 ,  F04D29/685 ,  F05D2220/3216

摘要： The invention relates to a compressor for a turbine engine, comprising: a casing, at least one compressor stage formed by an impeller having stationary blades and an impeller having moving blades (1) positioned downstream of the stationary blade impeller, and cavities (5) in the thickness of the casing that are disposed along a circumference of said casing (4) opposite the moving blades (1). The cavities, which are elongate and extend along a main direction of orientation, are closed upstream and downstream by upstream and downstream faces respectively, and an upstream border (7) and a downstream border (6) are formed at the intersections between same and the casing. The cavities are offset in relation to the moving blades (1) such as to overlap the moving blade impeller in the upstream portion, thereby covering the upstream end thereof. The casing is characterised in that the downstream border (6) of the cavities (5) is oriented parallel to the chord at the head of the moving blade (1).

公开(公告)号：EP2679783A2

公开(公告)日：2014-01-01

申请号：EP13172442.9

申请日：2013-06-18

申请人： Rolls-Royce plc

发明人： Bradbrook, Stephen John ,  Davis, Brian

IPC分类号： F02C3/08

CPC分类号： F04D19/02 ,  F02C3/08 ,  F04D17/06 ,  F04D19/028 ,  F05D2220/3216 ,  F05D2220/3219 ,  F05D2240/30

摘要： A spool (14) for turbo machinery comprises a fluid flow path (16) defined by an axial compressor stage (18) adjacent to a mixed flow compressor stage (20) to thereby provide a compression system which has a relatively high ratio of efficiency to compressor diameter.

摘要翻译： 用于涡轮机械的阀芯（14）包括由与混合流动压缩机级（20）相邻的轴向压缩机级（18）限定的流体流动路径（16），从而提供一种压缩系统，其具有相对较高的效率比 压缩机直径。