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公开(公告)号：US09200531B2
公开(公告)日：2015-12-01
申请号：US13362654
申请日：2012-01-31
CPC分类号： F01D11/18 , F01D11/125 , F01D25/26 , F05D2220/36 , F05D2230/68 , F05D2300/173 , F05D2300/433 , F05D2300/44 , F05D2300/50212 , F05D2300/603 , Y02T50/672 , Y10T29/49323 , Y10T156/10 , Y10T156/17
摘要： A turbofan engine has a fan having a circumferential array of fan blades. A fan case encircles the fan. There is at least one compressor section, a combustor, and at least one turbine section. The fan case comprises a composite structural member and a metallic member encircled by the composite structural member. The metallic member is mounted to the composite structural member to permit differential thermal expansion proximate the blades.
摘要翻译： 涡轮风扇发动机具有具有圆周阵列的风扇叶片的风扇。 风扇外壳包围风扇。 至少有一个压缩机部分，燃烧器和至少一个涡轮部分。 风扇壳体包括复合结构构件和由复合结构构件包围的金属构件。 金属构件安装到复合结构构件以允许在叶片附近的差别热膨胀。
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公开(公告)号：US08985938B2
公开(公告)日：2015-03-24
申请号：US13324143
申请日：2011-12-13
申请人： Dale William Petty
发明人： Dale William Petty
CPC分类号： F01D11/08 , F01D11/005 , F01D11/18
摘要： An engine has a blade, a casing surrounding the blade, an seal ring, and a passive system for connecting the seal ring to the casing and for accommodating thermal expansion of the seal ring relative to the casing so as to maintain blade tip clearance control. The passive system may include at least one, metallic Z-band extending between the casing and the seal ring.
摘要翻译： 发动机具有叶片，围绕叶片的壳体，密封环和用于将密封环连接到壳体并用于适应密封环相对于壳体的热膨胀的无源系统，以便保持叶片顶端间隙控制。 被动系统可以包括在壳体和密封环之间延伸的至少一个金属Z形带。
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公开(公告)号：US07946807B2
公开(公告)日：2011-05-24
申请号：US11859427
申请日：2007-09-21
申请人： Vincent Philippot
发明人： Vincent Philippot
IPC分类号： F01D11/18
CPC分类号： F01D11/18
摘要： A turbine stator of a gas turbine engine includes a turbine casing, a turbine shroud ring and a shroud ring support connecting the shroud ring to the casing. The stator is one wherein the support is provided with a heat shield positioned on the turbine side. This assembly makes it possible to reduce the take-up of play during transient operating phases.
摘要翻译： 燃气涡轮发动机的涡轮机定子包括涡轮机壳体，涡轮机护罩环和将护罩环连接到壳体的护罩环支撑件。 定子是其中支撑件设置有位于涡轮机侧的热屏蔽的定子。 该组件使得可以在瞬态操作阶段减少播放的占用。
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公开(公告)号：US20100104416A1
公开(公告)日：2010-04-29
申请号：US12260548
申请日：2008-10-29
IPC分类号： F01D11/18
CPC分类号： F01D11/18 , F01D5/225 , F01D11/025 , F05D2220/31 , F05D2300/50212 , F05D2300/505
摘要： A thermally-activated flow clearance reduction for a steam turbine is disclosed. In one embodiment a gap closure component is located about a rotary component and a stationary component of the steam turbine. A temperature differential activates the gap closure component to seal or reduce the radial clearance of the steam flow path between the rotary component and the stationary component.
摘要翻译： 公开了一种用于汽轮机的热活化流动间隙减小。 在一个实施例中，间隙封闭部件围绕蒸汽轮机的旋转部件和固定部件定位。 温差启动间隙关闭部件以密封或减小旋转部件和固定部件之间的蒸汽流动路径的径向间隙。
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公开(公告)号：US6155780A
公开(公告)日：2000-12-05
申请号：US374916
申请日：1999-08-13
申请人： Gregory C. Rouse
发明人： Gregory C. Rouse
摘要： A turbine engine includes a rotatable turbine having a peripheral tip and a backface. A heat shield is positioned adjacent the backface and includes an integral ring extending from a peripheral edge of the heat shield to a position spaced radially outwardly from the peripheral tip of the rotatable turbine to form a tip clearance between the ring and the peripheral tip. The turbine comprises a material having a coefficient of thermal expansion at least approximately four times greater than the coefficient of thermal expansion of the heat shield such that the turbine expands toward the ring as a result of heat within the engine, thereby reducing the tip clearance to minimize air flow along the backface and improve efficiency of the engine.
摘要翻译： 涡轮发动机包括具有外围末端和背面的可旋转涡轮机。 隔热罩定位在背面附近，并且包括从隔热罩的周缘延伸到与可旋转涡轮机的周边末端径向向外间隔开的位置的整体环，以在环和外围末端之间形成顶端间隙。 涡轮机包括具有比隔热板的热膨胀系数大至少大约四倍的热膨胀系数的材料，使得由于发动机内部的热量使涡轮机朝向环膨胀，从而将顶端间隙减小到 最小化背面的气流，提高发动机的效率。
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公开(公告)号：US6065754A
公开(公告)日：2000-05-23
申请号：US60902
申请日：1998-04-15
IPC分类号： F16J15/453 , F01D11/02 , F01D11/18 , F16J15/44 , F16J15/447
CPC分类号： F01D11/025 , F01D11/18 , F16J15/442 , Y10S277/931
摘要： A variable clearance packing ring includes a plurality of circumferentially extending segments disposed in a generally dovetail-shaped slot in the stationary component of a machine having a rotor rotatable about an axis, the packing ring including an arcuate seal face in opposition to the rotor and axially extending flanges within the dovetail slot. Pins project axially from opposite sides of the stationary component for location between the flanges and sealing faces of the segments. A centering ring is mounted on the pins for each segment and has a coefficient of thermal expansion greater than the coefficient of thermal expansion of the segment. The centering rings engage the flanges of the segments at a first location, maintaining the segment seal face in a first clearance position relative to the rotor and engage the flanges at a second location in response to relative thermal expansion of the segment and the centering rings, enabling the segment to be displaced radially inwardly under the bias of a spring to locate the seal face in a second clearance position about the rotor radially inwardly of the first clearance position.
摘要翻译： 可变间隙填料环包括多个周向延伸的段，其设置在机器的固定部件中的大致燕尾形槽中，该机构具有可围绕轴线旋转的转子，该密封环包括与转子相对的弓形密封面， 在燕尾槽内延伸法兰。 引脚从固定部件的相对侧轴向突出，用于位于凸缘和段的密封面之间。 定心环安装在每个段的销上，并且具有大于段的热膨胀系数的热膨胀系数。 定心环在第一位置处接合节段的凸缘，将节段密封面保持在相对于转子的第一间隙位置，并响应于段和定心环的相对热膨胀而在第二位置接合凸缘， 使得所述段在弹簧的偏压下能够径向向内移动，以将密封面定位在围绕第一间隙位置的径向向内的转子的第二间隙位置。
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公开(公告)号：US5927721A
公开(公告)日：1999-07-27
申请号：US963556
申请日：1997-11-03
申请人： Gisbert Schulze , Bernhard Woehrl
发明人： Gisbert Schulze , Bernhard Woehrl
IPC分类号： F16J15/453 , F16J15/16 , F16J15/3288 , F01D11/18
CPC分类号： F16J15/3288 , F05B2220/302
摘要： A brush seal (3) is provided to seal two differently pressurized spaces (R.sub.1, R.sub.2) on opposite sides of a rotor (1) cooperating with a stator (2), for example in a gas turbine engine, around a circumferential gap between the rotor (1) and the stator (2). The brush seal (3) includes seal bristles (5) having free ends extending annularly concentrically and parallel to a rotation axis of the rotor (1) and fixed ends received in a seal housing (6). A perimeter rim of the rotor (1) has an axis-concentric circumferential groove (7) therein, and the free ends of the seal bristles (5) reach into this circumferential groove (7). During operation of the rotor (1), fluid boundary layers are formed respectively between the seal bristles (5) and the side walls (9A, 9B) of the circumferential groove (7). The boundary layers (G.sub.I, G.sub.A) cause the seal bristles (5) to float up out of contact with and substantially centered between the side walls of the circumferential groove (7), and also enhance the seal effect. The axis-parallel orientation of the bristles (5) reduces the radial height of the seal arrangement, and ensures that good radial compensation is still achieved.
摘要翻译： 提供刷密封件（3）以在与定子（2）（例如在燃气涡轮发动机中）配合的转子（1）的相对侧上的两个不同的加压空间（R1，R2）围绕第 转子（1）和定子（2）。 刷密封件（3）包括密封刷毛（5），其具有环形同心圆且平行于转子（1）的旋转轴线的自由端和容纳在密封壳体（6）中的固定端。 转子（1）的周缘在其中具有轴向同心圆周槽（7），并且密封刷毛（5）的自由端到达该周向凹槽（7）。 在转子（1）的操作期间，分别在密封刷毛（5）和周向槽（7）的侧壁（9A，9B）之间形成流体边界层。 边界层（GI，GA）使得密封刷毛（5）浮起而不与周向凹槽（7）的侧壁接触并且基本上居中，并且还增强了密封效果。 刷毛（5）的轴线平行取向减小了密封装置的径向高度，并且确保仍然实现良好的径向补偿。
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38.发明授权Arrangement for influencing the radial clearance of the blading in axial-flow compressors including hollow spaces filled with insulating material 失效用于影响轴流式压缩机中叶片的径向间隙的布置，包括填充有绝缘材料的中空空间
公开(公告)号：US5630702A
公开(公告)日：1997-05-20
申请号：US556074
申请日：1995-11-02
CPC分类号： F01D11/18 , F04D29/164 , F04D29/584
摘要： In an arrangement for influencing the radial clearance of the blading of an axial-flow, highly loaded compressor which essentially comprises a rotor (1) equipped with moving blades (2) and a blade carrier (3) which is equipped with guide blades (4) and is hung in a casing (5), the blade carrier (3) has long and narrow mountings (7) for the guide blades (4), at least one hollow space (9) being arranged in the guide-blade roots (8), a hollow space (10) being present in each case in the embedded state in the peripheral direction between the guide-blade root (8), the two mountings (7) for a guide blade (4) and the blade carrier (3), a further hollow space (11) being present in each case in the peripheral direction between the blade carrier (3) and the mountings (7) for two successive guide blades (4), which hollow space (11) is defined by a plurality of segments (12) distributed over the periphery and connected to the guide-blade roots (8), and the hollow spaces (9, 10, 11) being filled with insulating material (15).
摘要翻译： 在用于影响轴流式高负载压缩机的叶片的径向间隙的布置中，该轴流式高负载压缩机基本上包括配备有活动叶片（2）的转子（1）和装备有导向叶片（4）的叶片载体（3） ）并且悬挂在壳体（5）中，所述叶片承载件（3）具有用于所述引导叶片（4）的长而窄的安装件（7），至少一个中空空间（9）布置在所述导向叶片根部 如图8所示，在引导叶片根部（8），用于引导叶片（4）的两个安装件（7）和叶片承载件（8）之间沿圆周方向以嵌入状态存在中空空间（10） 在两个连续的引导叶片（4）中，在叶片载体（3）和安装件（7）之间沿圆周方向在每个壳体中存在另外的中空空间（11），该中空空间（11）由 分布在外围并连接到引导叶根（8）的多个段（12），并且中空空间（9,10,11）被填充 绝缘材料（15）。
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公开(公告)号：US5330321A
公开(公告)日：1994-07-19
申请号：US59292
申请日：1993-05-11
CPC分类号： F01D11/18
摘要： In a gas turbine engine tip clearance between rotor blades and an encircling shroud liner is controlled by moving the shroud liner radially to match the thermal and centrifugal growth of the rotor assembly. The shroud liner segments are suspended between two axially displaced control rings located in a passageway carrying air ducted from the compressor. One control ring responds very quickly to changes in gas temperature corresponding to centrifugal growth and blade thermal growth. The other ring responds very much more slowly and corresponds to the thermal growth of the disc. The shroud liner segments are suspended from the control rings to adopt a position that constitutes the average between the growth positions of the two control rings.
摘要翻译： 在燃气涡轮发动机中，通过径向地移动护罩衬套以匹配转子组件的热和离心生长来控制转子叶片与环绕护罩衬套之间的间隙。 护罩衬套段悬挂在两个轴向移动的控制环之间，该控制环位于承载从压缩机导出的空气的通道中。 一个控制环对应于离心增长和叶片热生长的气体温度变化非常快速地响应。 另一个环响应非常慢，对应于盘的热生长。 护罩衬套段从控制环悬挂以采用构成两个控制环的生长位置之间的平均值的位置。
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40.发明授权
公开(公告)号：US5314303A
公开(公告)日：1994-05-24
申请号：US298
申请日：1993-01-04
CPC分类号： F01D11/18
摘要： A gas turbine compressor casing has two inner and outer envelopes forming at least one closed cavity and a locking or clamping ring having a thermal inertia higher than that of the envelopes and mounted in the closed cavity in such a way as to limit its contraction during a lowering of the temperature. The thermal inertia difference can be obtained by using for the locking ring a material having a thermal expansion coefficient lower than the coefficient of the envelopes. It can also be controlled by a ventilation means device for ensuring hot air flow in the cavity.
摘要翻译： 燃气涡轮压缩机壳体具有形成至少一个封闭空腔的两个内部和外部信封，以及具有高于信封的热惯性的热惯性的锁定或夹紧环，并以这样的方式限制其在 降低温度。 热惯性差异可以通过将锁定环用作热膨胀系数低于包封系数的材料来获得。 它也可以由通风装置来控制，以确保空腔中的热空气流动。
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