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公开(公告)号：EP3325773A1
公开(公告)日：2018-05-30
申请号：EP16739177.0
申请日：2016-07-18
摘要： An unshrouded turbomachine impeller (1) is disclosed. The impeller comprises a hub (3) and a plurality of sequentially arranged blades (5). Each blade extends from a blade root (5R) at the hub (3) to a blade tip (5T) and is comprised of a first blade edge (9) and a second blade edge (11). A flow vane (13) is formed between each pair of neighboring blades (5). A connection member (21) extends across each flow vane (13) between neighboring blades (5) and rigidly or monolithically connects a first modal displacement region (R1) of a first one of the pair of neighboring blades (5) to a second modal displacement region (R2) of a second one of the pair of neighboring blades (5).
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公开(公告)号：EP2885505A1
公开(公告)日：2015-06-24
申请号：EP13734256.4
申请日：2013-06-21
CPC分类号： F01D5/225 , F01D5/24 , F05D2300/6033
摘要： A damper system and a turbine are provided. The damper system includes a plurality of CMC blades. Each CMC blade has a first member of a tip shroud, the first member opposite a second member of the tip shroud, a radial flange extending between the first member and the second member of the tip shroud, and at least one aperture in the radial flange for receiving a damping member, the dampening member joining and dampening adjacent CMC blades. The turbine includes a plurality of turbine blade tip shroud segments, each tip shroud segment having a first surface that cooperates with the first surface in an adjacent tip shroud segment to form a first opening, each tip shroud segment having a first receiving surface. The turbine includes a damper member that abuts the first receiving surface of each tip shroud segment.
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公开(公告)号：EP2399005B1
公开(公告)日：2012-11-21
申请号：EP10702854.0
申请日：2010-01-27
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公开(公告)号：EP1965093A2
公开(公告)日：2008-09-03
申请号：EP08154363.9
申请日：2000-08-02
IPC分类号： F16F15/12
CPC分类号： F01D5/24 , F16F15/12 , F16F15/1213 , F16F15/126 , Y10S416/50
摘要： A rotor (110), such as a rotor of an aircraft gas turbine engine, uses damper-ring devices for damping unwanted rotor vibrations. One device (126) has inner and outer damper rings (132 and 130) in a groove (118) with the outer damper ring (130) providing ring-rotor frictional damping only at large vibrational amplitudes and with the inner and outer damper rings providing inter-ring frictional damping at both small and large vibrational amplitudes. Other devices include a damper ring and a viscoelastic layer, a hollow damper ring containing particulate matter, and a damper ring in the form of a cable made of twisted single-wire strands.
摘要翻译： 诸如飞机燃气涡轮发动机的转子的转子（110）使用阻尼环装置来阻尼不想要的转子振动。 一个装置（126）在槽（118）中具有内部和外部阻尼器环（132和130），外部阻尼器环（130）仅在较大的振动幅度下提供环形转子摩擦阻尼并且内部和外部阻尼器环 在小振幅和大振幅下的环间摩擦阻尼。 其他装置包括阻尼环和粘弹性层，含有颗粒物质的空心阻尼环，以及由绞合单股线制成的电缆形式的阻尼环。
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公开(公告)号：EP0881361A2
公开(公告)日：1998-12-02
申请号：EP98109379.2
申请日：1998-05-22
发明人： Tsukamoto, Minoru , Mitsubori, Ken
IPC分类号： F01D5/24
CPC分类号： F01D5/24 , Y10S416/50
摘要： An arrangement for attenuating vibrations of blades (2) attached to a peripheral surface (6) of a rotor (1) of an axial turbine.
A through hole (10) is formed in each rotor blade (2) in a generally thickness direction of the blade (2) so that the through holes (10) in combination define a single annular passage near a rotor surface (6) when all of the rotor blades (2) are attached to the rotor (1). A wire (11) is provided to extend through the aligned through holes (10). Thus, the wire (11) frictionally contacts the through holes (10) when the blades (2) are caused to vibrate due to a gas pressure and a centrifugal force generated upon operation of the axial turbine.
Friction contact between the wire (11) and the through holes (10) attenuates vibrations of the blades (2).摘要翻译： 一种用于衰减安装在轴向涡轮机的转子（1）的外围表面（6）上的叶片（2）的振动的装置。 在每个转子叶片（2）中沿叶片（2）的大致厚度方向形成通孔（10），使得通孔（10）组合在转子表面（6）附近限定单个环形通道 的转子叶片（2）附接到转子（1）。 电线（11）设置成延伸通过对准的通孔（10）。 因此，当叶片（2）由于在轴向涡轮机的操作时产生的气体压力和离心力而使叶片（2）振动时，导线（11）摩擦地接触通孔（10）。 导线（11）与通孔（10）之间的摩擦接触使叶片（2）的振动衰减。
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公开(公告)号：EP3317496A1
公开(公告)日：2018-05-09
申请号：EP16731296.6
申请日：2016-06-17
发明人： THOMAS, Neil, Ryan
IPC分类号： F01D5/24
CPC分类号： F01D5/24 , F05D2220/40
摘要： A turbomachinery rotor blade is provided having an aerofoil body, and a hole penetrating the aerofoil body from a suction surface to a pressure surface thereof. The hole is suitable to receive a lacing wire. The blade further has a protrusion from the suction or pressure surface. The protrusion extends in a downstream direction from a downstream side of the hole and/or extends in an upstream direction from an upstream side of the hole, thereby disturbing the suction or pressure surface to locally thicken the aerofoil body adjacent the hole. The maximum radial extent of the protrusion in the radially outward direction of the blade is radially coterminous with the outboard side of the hole, and the maximum radial extent of the protrusion in the radially inward direction of the blade is radially coterminous with the inboard side of the hole.
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公开(公告)号：EP3106622A1
公开(公告)日：2016-12-21
申请号：EP16168849.4
申请日：2016-05-10
申请人： Rolls-Royce Corporation , Rolls-Royce North American Technologies, Inc. , Rolls-Royce High Temperature Composites Inc
CPC分类号： F01D11/005 , F01D5/225 , F01D5/24 , F01D9/04 , F01D11/008 , F01D25/246 , F01D25/26 , F01D25/265 , F05D2220/32 , F05D2240/11 , F05D2240/55 , F05D2300/6033 , Y02T50/672
摘要： A gas turbine engine assembly (50) adapted to separate a high pressure zone (HP) from a low pressure zone (LP) includes a seal assembly (10) configured to block gasses from passing through the interface of two adjacent components (20, 30). The seal assembly includes a rod (12).
摘要翻译： 适于将高压区（HP）与低压区（LP）分开的燃气涡轮发动机组件（50）包括密封组件（10），该密封组件（10）被配置为阻挡气体穿过两个相邻部件（20,30 ）。 密封组件包括杆（12）。
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9.发明授权Method for engineering a single crystal cast gas turbine engine metallic seal and apparatus comprising a corresponding seal 有权一种用于设计用于燃气涡轮机发电设备的单晶铸造金属密封件和设备与相关联的密封方法
公开(公告)号：EP1878873B1
公开(公告)日：2016-08-31
申请号：EP07252722.9
申请日：2007-07-06
IPC分类号： F01D11/00
CPC分类号： F01D11/005 , F01D5/16 , F01D5/22 , F01D5/24 , F01D11/006 , F01D17/04 , F01D25/06 , F02C7/052 , F05C2201/0466 , F05D2300/11 , F05D2300/50 , F05D2300/607 , F16J15/0806 , F16J15/0887 , G01H11/08 , G10K11/24 , Y10T29/4932
摘要： A method is provided for engineering a single crystal cast gas turbine engine first component for cooperating with a second component. An at least local first operational stress on the first component is determined. The first operational stress has a first direction. A crystal orientation within the component or a physical configuration of the component is selected so that the first operational stress produces a desired engagement of the first component with the second component associated with either a negative Poisson's effect or high Poisson's effect in a second direction. Single crystal or highly textured iron- and nickel-base alloys enable one to use such effect in high temperature and/or corrosive environments.
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公开(公告)号：EP2436878A2
公开(公告)日：2012-04-04
申请号：EP11180377.1
申请日：2011-09-07
发明人： Scheunert, Norbert
IPC分类号： F01D5/00
CPC分类号： F01D5/22 , F01D5/24 , F05D2230/64 , F05D2250/232 , F05D2260/30 , F05D2300/603
摘要： Die Erfindung betrifft einen Koppelbolzen (1) zum Koppeln von zwei oder mehreren Turbinenschaufeln (2), wobei die Koppelbolzen (1) zumindest teilweise aus Faserverbundwerkstoff bestehen. Durch die zumindest teilweise Ausbildung aus Faserverbundwerkstoff kann das Gewicht der Koppelbolzen (1) gegenüber im Stand der Technik deutlich herabgesetzt werden.
摘要翻译： 螺栓（1）具有双锥形轮廓或圆锥形端部（3），其自动对中到相应涡轮机叶片（2）的接收孔（4）中，以便将彼此相邻的涡轮机叶片联接。 螺栓部分地由诸如钢和/或钛的复合材料制成。 螺栓被旋转对称地形成为中空轮廓。 通过形成具有加厚部分（5）的涡轮机叶片，接收孔形成为通孔或盲孔。
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