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1. 发明公开

EP3341570A1 DISPOSITIF DE FIXATION DES RAMPES DE REFROIDISSEMENT PAR JETS D'AIR DU CARTER D'UNE TURBINE DE TURBOMACHINE 有权
公开(公告)号：EP3341570A1
公开(公告)日：2018-07-04
申请号：EP16770056.6
申请日：2016-08-25
申请人： Safran Aircraft Engines
发明人： BUNEL, Jacques, Marcel, Arthur , D'HERBIGNY, Emeric , MADEC, Alain Paul , TINCELIN, Pierre , VILLENAVE, Benjamin
IPC分类号： F01D25/12
CPC分类号： F01D25/12 , F05D2220/3215 , F05D2240/90 , F05D2260/201
摘要： The invention relates to a device (3) for attaching manifolds (1) for cooling the casing (2) of a preferably low-pressure turbine of a turbine engine by air jets, comprising a mounting (4) of said manifolds, shaped such as to keep said manifolds spaced apart from one another and a plurality of elements (5) for supporting said manifold mounting (4), each supporting element being attached to the casing, and connected to said manifold mounting (4) by connection means (6, 6'). Said device is characterised in that it comprises N cooling manifolds (1) and N-1 supporting elements (5), each supporting element (5) being arranged between two adjacent cooling manifolds.

2. 发明授权

EP3207299B1 MULTI-POINT MOUNTING SYSTEM FOR ROTATING MACHINERY 有权转让
公开(公告)号：EP3207299B1
公开(公告)日：2018-06-20
申请号：EP15820249.9
申请日：2015-09-03
申请人： Nuovo Pignone S.r.l.
发明人： ZAFFINO, Domenico , CAPANNI, Francesco , CHECCACCI, Emanuele , ROSSIN, Stefano , MARCUCCI, Daniele
IPC分类号： F16M5/00 , B23Q1/01 , F02C1/00 , F16M7/00 , F01D15/12
CPC分类号： F01D25/28 , F05D2220/32 , F05D2230/60 , F05D2240/90 , F05D2240/91 , F05D2260/96 , F16M5/00 , F16M7/00
摘要： A mounting system for supporting rotating machinery is described. The system comprises a base frame having an upper side for mounting the rotating machinery, and a lower side. A set of main supporting members are arranged according to a triangular arrangement and forming a three-point mounting arrangement defining a mounting plane. Moreover, a set of auxiliary supporting members, having a variable stiffness in at least one direction, are provided and are configured and arranged such as to increase the stiffness thereof when the base frame is subject to an overload, thus reducing load on the main supporting members.

3. 发明公开

EP3299590A1 CARTER INTERMEDIAIRE DE TURBINE DE TURBOMACHINE 有权
标题翻译：涡轮机涡轮中间套管
公开(公告)号：EP3299590A1
公开(公告)日：2018-03-28
申请号：EP17189218.5
申请日：2017-09-04
申请人： SAFRAN AIRCRAFT ENGINES
发明人： BLANCHARD, Stéphane, Pierre, Guillaume , CONDAT, Hélène, Myriam
IPC分类号： F01D25/16 , F01D25/24
CPC分类号： F01D25/243 , F01D25/16 , F01D25/162 , F01D25/28 , F05D2220/323 , F05D2230/53 , F05D2240/14 , F05D2240/90 , Y02T50/671
摘要： L'invention concerne une turbine comprenant un carter (56) intermédiaire intercalée axialement entre un carter (36) de turbine haute pression amont et un carter (38) de turbine basse pression aval et comprenant une virole (60) annulaire externe depuis laquelle s'étend radialement une bride (54) annulaire, caractérisée en ce que l'extrémité (36a) aval du carter (36) de turbine haute pression et l'extrémité (38a) amont du carter (38) de turbine basse pression sont fixées sur la bride (54) annulaire radiale du carter (56) intermédiaire.
摘要翻译：本发明涉及一种通过高压的壳体（36）的上游和一个涡轮机壳体（38）和下游低压涡轮机，包括从外部环形套圈（60），其中，S'的轴向之间，其包括壳体（56）的涡轮机径向延伸的凸缘（54）的环形，其特征在于，所述端部（36A）的高压涡轮机的壳体（36）和所述端部（38A）低压涡轮机的壳体（38）的上游侧的下游侧安装在所述中间壳体（56）的径向环形凸缘（54）。

4. 发明公开

EP2781700A3 Supporting device for gas turbine 有权转让
标题翻译：燃气轮机配套装置
公开(公告)号：EP2781700A3
公开(公告)日：2017-10-11
申请号：EP14161105.3
申请日：2014-03-21
申请人： Doosan Heavy Industries & Construction Co., Ltd.
发明人： Roh, U Jin , Lee, Sang Eon , Kim, Kyung Kook
IPC分类号： F01D25/28 , F02C7/20 , F02C7/32
CPC分类号： F02C7/20 , F01D25/28 , F02C7/32 , F05D2240/14 , F05D2240/90 , Y10T29/49998
摘要： A supporting device for a gas turbine includes a base frame (200); a fixing member (10) installed on the base frame (200) so as to support one endof a gas turbine; and an absorbing member (20) installed on the base frame (200) so as to support the other end of the gas turbine. The absorbing member (20) having lower stiffness than the fixing member (10) so as to deform in first and second directions when the gas turbine thermally expands.
摘要翻译：一种燃气轮机支撑装置，包括底座（200）; 固定构件（10），其安装在基架（200）上以支撑燃气轮机的一端; 和安装在底座（200）上的吸收构件（20），以支撑燃气轮机的另一端。吸收构件（20）具有比固定构件（10）低的刚性，以便当燃气涡轮机热膨胀时在第一方向和第二方向上变形。

5. 发明授权

EP2831383B1 EXHAUST DIFFUSER FOR A GAS TURBINE 有权转让
标题翻译：汽轮机排气扩散器
公开(公告)号：EP2831383B1
公开(公告)日：2017-09-20
申请号：EP13712242.0
申请日：2013-03-25
申请人： Ansaldo Energia IP UK Limited
发明人： HOFMANN, Willy Heinz , SCHAEFER, Philipp
IPC分类号： F01D25/28 , F02C7/20 , F01D25/30
CPC分类号： F01D25/30 , F01D9/02 , F01D25/28 , F02C7/20 , F02K1/04 , F05B2250/711 , F05B2250/712 , F05B2250/713 , F05D2240/90
摘要： An exhaust diffuser for a gas turbine comprises an annular duct (1). A row of struts (6) is arranged in the duct. In a region downstream of the trailing edges (TE) of the struts (6), the cross-sectional area of the duct decreases to a local minimum (M) and then increases again towards the outlet end (3) of the duct. Thereby the gas flow is locally accelerated downstream of the struts. This stabilizes the boundary layer of the flow in this region and leads to a marked increase in pressure recovery for a wide range of operating conditions.
摘要翻译：用于燃气轮机的排气扩压器包括环形管（1）。一排支柱（6）布置在管道中。在支柱（6）的后缘（TE）下游的区域中，管道的横截面积减小到局部最小值（M），然后再次朝着管道的出口端（3）增加。由此气流在支柱下游局部加速。这稳定了该区域内的流动边界层，并且在广泛的操作条件下导致压力恢复的显着增加。

6. 发明公开

EP3216699A1 METHOD AND SYSTEM FOR MOUNTING AN AIRCRAFT ENGINE 审中-公开
标题翻译：用于安装飞机发动机的方法和系统
公开(公告)号：EP3216699A1
公开(公告)日：2017-09-13
申请号：EP17159591.1
申请日：2017-03-07
申请人： General Electric Company
发明人： STUART, Alan Roy
IPC分类号： B64D27/18 , B64D27/26 , F01D25/28 , F02C7/20
CPC分类号： B64D27/26 , B64D27/18 , B64D2027/268 , F02C7/20 , F05D2220/323 , F05D2230/60 , F05D2240/90 , Y02T50/44 , Y02T50/671
摘要： A system 100 for mounting an engine 10 to an aircraft 1 includes a rigid structure 102 coupled to a wing 3 and including a forward mount interface 104 and an aft mount interface 106. The system includes a frame 115 including a first support connection 108 and a second support connection 110 spaced apart from the first support connection. A linkage structure 114 couples the frame to the rigid structure and includes a first linkage pair 116 extending between the forward mount interface and the first support connection at a first angle α with respect to a rotational axis 40, and a second linkage pair 118 extending between the aft mount interface and the second support connection at a second angle β with respect to the rotational axis. A projection of the load vector 120,122 of the first linkage pair and the second linkage pair intersect proximate the rotational axis of the engine between a forward end of a fan assembly 16 and a high pressure compressor 22.
摘要翻译：用于将发动机10安装到飞机1的系统100包括刚性结构102，该刚性结构102联接到机翼3并且包括前部安装接口104和后部安装接口106.该系统包括框架115，框架115包括第一支撑连接件108和第二支撑连接件110与第一支撑连接件间隔开。连杆结构114将框架连接到刚性结构并且包括第一连杆对116和第二连杆对118，第一连杆对116在前部安装接口和第一支撑连接部之间相对于旋转轴线40以第一角度α延伸，后安装界面和第二支撑连接件相对于旋转轴线成第二角度β。第一连杆对和第二连杆对的载荷矢量120,122的投影在风扇组件16的前端和高压压缩机22之间的发动机的旋转轴线附近相交。

7. 发明公开

EP3137742A1 ENSEMBLE MODULAIRE POUR UNE TURBOMACHINE 有权
标题翻译： MODULARE ANORDNUNGFÜREINEN TURBINENMOTOR
公开(公告)号：EP3137742A1
公开(公告)日：2017-03-08
申请号：EP15725820.3
申请日：2015-04-28
申请人： Safran Aircraft Engines
发明人： CURLIER, Augustin , LEMARCHAND, Kevin, Morgane , NOWAKOWSKI, Nathalie , VINCENT, Thomas, Alain, Christian
IPC分类号： F01D25/16 , F02C7/32 , F02C7/36 , F02K3/06 , F02C7/06
CPC分类号： F02C7/32 , F01D25/162 , F02C7/06 , F02C7/36 , F05D2230/60 , F05D2230/72 , F05D2240/90 , F05D2260/4031
摘要： The invention relates to a modular assembly for a turbine engine, comprising an annular bearing support (26) including means for connecting to a first anti-friction bearing (24) designed to be mounted around a first shaft (16) of the turbine engine, and means for connecting to a second anti-friction bearing (31) designed to be mounted around a second shaft (18) of the turbine engine that is not parallel to the first shaft.
摘要翻译：用于涡轮发动机的模块化组件具有环形轴承支撑件，其构造成连接到第一抗摩擦轴承，该第一抗摩擦轴承构造成围绕涡轮发动机的第一轴安装。模块化组件还包括构造成围绕涡轮发动机的第二轴安装的第二抗摩擦轴承，其中第二轴不平行于所述第一轴。

8. 发明公开

EP3114409A1 CHAMBRE DE COMBUSTION ANNULAIRE DE TURBOMACHINE 有权
标题翻译： RINGFÖRMIGEBRENNKAMMERFÜREINEN TURBINENMOTOR
公开(公告)号：EP3114409A1
公开(公告)日：2017-01-11
申请号：EP15706859.4
申请日：2015-01-27
申请人： Safran Helicopter Engines
发明人： SAVARY, Nicolas , BERTEAU, Patrick , CARRERE, Bernard , DUBOURDIEU, Jean-Marc , NAUDOT, Ludovic
IPC分类号： F23R3/00 , F23R3/52 , F23R3/60
CPC分类号： F23R3/52 , F02C7/20 , F05D2230/50 , F05D2230/51 , F05D2230/64 , F05D2230/642 , F05D2240/35 , F05D2240/90 , F05D2260/30 , F23C5/02 , F23D11/103 , F23R3/002 , F23R3/007 , F23R3/28 , F23R3/283 , F23R3/42 , F23R3/425 , F23R3/46 , F23R3/48 , F23R3/50 , F23R3/54 , F23R3/56 , F23R3/58 , F23R3/60 , F23R2900/00005 , F23R2900/00017 , F23R2900/00018 , F23R2900/00019
摘要： The invention relates to an annular turbine engine combustion chamber having an axial direction (X), a radial direction, and an azimuthal direction. Said chamber includes a first annular wall (12) and a second annular wall (14). Each wall defines at least part of the enclosure of the annular combustion chamber. The first and second walls (12, 14) have complementary interlocking elements (12d, 14d). The first wall (12) has at least one first through-hole (12f), while the second wall (14) has at least one second through-hole (14f). The combustion chamber also includes at least one pin inserted into a pair of holes that include a first hole (12f) and a second hole (14f). Said pin (18) is formed by an injector and securely interlocks the first and second walls (12, 14).
摘要翻译：一种用于涡轮机（100）的环形燃烧室（10），所述燃烧室具有轴向方向（X），径向方向和方位方向，并且包括第一环形壁（12）和第二环形壁），限定所述环形燃烧室（10）的体积的至少一部分的每个壁，所述第一和第二壁（12,14）呈现互补的配合元件（12d，14d），所述第一壁（12）至少呈现一个第一通孔（12f），而第二壁（14）呈现至少一个第二通孔（14f），燃烧室（10）还具有接合在一对孔中的至少一个销（18）孔（12f）和第二孔（14f），所述销（18）锁定第一和第二壁（12,14）的配件。

9. 发明公开

EP3096040A1 ACTIVE SYSTEM FOR BEARING OIL DAMPER SUPPLY AND VIBRATION CONTROL 有权转让
标题翻译：里维埃拉系统
公开(公告)号：EP3096040A1
公开(公告)日：2016-11-23
申请号：EP16169379.1
申请日：2016-05-12
申请人： United Technologies Corporation
发明人： PARNIN, Francis
IPC分类号： F16F15/023 , F01D25/16 , F16C27/04
CPC分类号： F01D25/164 , F01D25/20 , F05D2220/32 , F05D2240/50 , F05D2240/54 , F05D2240/90 , F05D2260/96 , F05D2270/301 , F05D2270/303 , F05D2270/309 , F05D2270/334 , F16C19/06 , F16C19/527 , F16C27/045 , F16C35/067 , F16C2360/23 , F16F15/0237
摘要： A bearing damping system includes a pump 72 configured to pump a fluid. The system further includes a variable position valve 78A,78B,78C having a plurality of open positions each configured to generate different pressures in the fluid downstream from the variable position valve. The system also includes a bearing assembly. The bearing assembly includes a bearing housing 60. The bearing assembly also includes a stationary bearing race 54 positioned within the bearing housing 60. The bearing assembly also includes a rotating bearing race 46 spaced apart from the stationary bearing race 54 and configured to be attached to a rotating component. A bearing element 57 is disposed between the stationary bearing race 54 and the bearing housing 60. A fluid compartment 66 is defined by the space between the bearing housing 60 and the stationary race 54 and is configured to receive the fluid from the second conduit 82.
摘要翻译：轴承阻尼系统包括构造成泵送流体的泵72。该系统还包括具有多个打开位置的可变位置阀78A，78B，78C，每个打开位置被配置为在可变位置阀下游的流体中产生不同的压力。该系统还包括轴承组件。轴承组件包括轴承壳体60.轴承组件还包括定位在轴承壳体60内的固定轴承座圈54.轴承组件还包括与固定轴承座54间隔开的旋转轴承座圈46，并配置成附接到旋转部件。轴承元件57设置在固定轴承座54和轴承座60之间。流体隔室66由轴承壳体60和固定座圈54之间的空间限定，并构造成从第二导管82接收流体。

10. 发明公开

EP2971679A2 ENGINE MOUNT WAITING FAIL SAFE LUG JOINT WITH REDUCED DYNAMIC AMPLIFICATION FACTOR 有权转让
标题翻译： FAIL-SAFE PUSH CONNECTION电机营缩小的动态增益系数
公开(公告)号：EP2971679A2
公开(公告)日：2016-01-20
申请号：EP14801436.8
申请日：2014-03-04
申请人： United Technologies Corporation
发明人： ZHENG, Zhijun , FOSTER, Joseph, P. , DAILEY, Stephen, P. , SANDY, David, F.
IPC分类号： F02C7/20 , B64D27/00 , F16B21/10
CPC分类号： B64D27/26 , B64D2027/266 , B64D2027/268 , F01D25/24 , F01D25/28 , F02C7/20 , F05D2220/32 , F05D2230/60 , F05D2230/642 , F05D2240/90 , F05D2260/311 , F16B5/025 , Y02T50/44 , Y02T50/671
摘要： An engine mount may include a clevis and a lug defining a hole therethrough. A pin may be joined to the clevis and may extend through the hole of the lug with the pin and the lug defining a clearance therebetween. A trigger system may be disposed on the lug and operatively associated with the pin.

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