公开(公告)号：US06607350B2

公开(公告)日：2003-08-19

申请号：US10105197

申请日：2002-03-26

申请人： Alec G Dodd

发明人： Alec G Dodd

IPC分类号： F01D1116

CPC分类号： F01D11/22 ,  F01D17/02

摘要： Tip clearance apparatus for a gas turbine engine comprises a shroud ring having curved portions so as to allow eccentric offset and hence asymmetric movement of the shroud. The shroud ring is mounted within a guide also having corresponding curved portions and movement of the shroud ring is controlled by the use of sensors.

摘要翻译： 用于燃气涡轮发动机的顶端间隙装置包括具有弯曲部分的护罩环，以便允许护罩的偏心偏移并因此允许不对称的运动。 护罩环安装在也具有相应弯曲部分的引导件内，并且通过使用传感器来控制护罩环的移动。

公开(公告)号：US06413045B1

公开(公告)日：2002-07-02

申请号：US09610113

申请日：2000-07-05

申请人： Stephen N Dancer ,  Alec G Dodd

发明人： Stephen N Dancer ,  Alec G Dodd

IPC分类号： F01D1108

CPC分类号： F01D5/145 ,  F01D5/143 ,  F01D5/225 ,  Y02T50/673

摘要： The shroud (26) of a shrouded turbine blade (22) has a convex leading edge (30) the apex of which extends towards the trailing edge of the shroud (24) of an adjacent, preceding guide vane. The extension enables the containment of a reverse flow of high pressure gas from the juncture of the blade aerofoil and shroud, until the pressure has dropped sufficiently to avoid nullifying gas flow from the corresponding portion of the guide vane (20) and thereby reduces excessive hot gas leakage from between the opposing shrouds edges.

摘要翻译： 被覆盖的涡轮机叶片（22）的护罩（26）具有凸出的前缘（30），其顶点朝向邻近的前导向叶片的护罩（24）的后缘延伸。 该延伸部能够从叶片机翼和护罩的接合处容纳逆流的高压气体，直到压力已经足够下降以避免从导叶（20）的相应部分排出气流，从而减少过热 气体从相对的护罩边缘之间泄漏。

公开(公告)号：US06675868B2

公开(公告)日：2004-01-13

申请号：US10151945

申请日：2002-05-22

申请人： Alec G Dodd

发明人： Alec G Dodd

IPC分类号： B22C1900

CPC分类号： B22C21/14 ,  B22C7/02

摘要： A machine for forming and fitting core support pins into wax (70) surrounding a core (68) prior to covering the wax (70) with a frit (76), includes one or more punch devices (30), (82) within its structure, so as to enable the forming of one or more indentations in each pin, intermediate its ends, thereby providing a designed weakness in the pin to cause it to more reliably follow slight relative movement which occurs between the pins and the part being cast, thus reducing stresses in the surface of the part.

摘要翻译： 在用玻璃料（76）覆盖蜡（70）之前，将芯支撑销形成和装配在围绕芯（68）的蜡（70）中的机器包括在其内部的一个或多个冲压装置（30），（82） 结构，以便能够在每个销中形成一个或多个凹口，在其端部之间，从而在销中提供设计的弱点，以使其更可靠地跟随在销和被铸造的部件之间发生的轻微的相对运动， 从而减少零件表面的应力。

公开(公告)号：US06179557B2

公开(公告)日：2001-01-30

申请号：US09351133

申请日：1999-07-12

申请人： Alec G Dodd ,  Jagnandan K Bhangu

发明人： Alec G Dodd ,  Jagnandan K Bhangu

IPC分类号： F01D514

CPC分类号： F01D25/14 ,  F01D9/00 ,  Y02T50/675

摘要： Shrouds (40) surrounding a stage of turbine blades (44) are cooled by a compressor airflow which is led to the downstream end of the shrouds before contacting them. The airflow passes through apertures (56) in plates (50) then over the shrouds (40) in an upstream direction, to exit from apertures (62) in the shrouds (40) in parallel with and in the same direction as the gasflow. Airflow needed is reduced relative to prior art needs, resulting in improved engine efficiency, and ejection of the air does not disturb the gasflow.

摘要翻译： 围绕涡轮机叶片（44）的阶段的护罩（40）由压缩机空气流冷却，该压缩空气在接触它们之前被引导到护罩的下游端。 气流通过板（50）中的孔（56），然后在上游方向上穿过护罩（40），从而与护罩（40）中的平行于并沿与气流相同的方向上的孔（62）离开。 相对于现有技术的需要，所需的气流减少，导致发动机效率的提高，并且空气的排出不会扰乱气流。

公开(公告)号：US6129513A

公开(公告)日：2000-10-10

申请号：US294136

申请日：1999-04-20

申请人： Mark A Halliwell ,  Alec G Dodd

发明人： Mark A Halliwell ,  Alec G Dodd

IPC分类号： F01D9/04 ,  F01D11/02 ,  F01D11/08

CPC分类号： F01D9/04 ,  F01D11/025

摘要： A fluid seal comprises a plurality of seal segments (24) which form a peripheral ring at the tip of turbine rotor blades (20). The upstream end (25) of each seal segment (24) is mounted on the static structure (27). The downstream end (26) of each seal segment (24) is supported by an inner flange (34) on a vane (32). The vane (32) is also provided with a radially outer flange (36) which locates in a radially inclined slot (31) in the casing (30). During engine transients, the vane (32) expands axially forward relative to the casing (30). The outer flange (36) rides up the inclined slot (31) which causes the seal segment (24) to move radially outward and increases the seal clearance. However, during stabilized engine running, the relative axial movement between the casing (30) and the vane (32) is reduced. The outer flange (36) contracts down the inclined slot (31) to move the seal segment (24) radially inwards; the combination reduces the tip clearance and prevents excessive gas leakage.

摘要翻译： 流体密封件包括在涡轮转子叶片（20）的尖端处形成周边环的多个密封段（24）。 每个密封段（24）的上游端（25）安装在静态结构（27）上。 每个密封段（24）的下游端（26）由叶片（32）上的内凸缘（34）支撑。 叶片（32）还设置有位于壳体（30）中的径向倾斜的槽（31）中的径向外凸缘（36）。 在发动机瞬变期间，叶片（32）相对于壳体（30）轴向向前膨胀。 外凸缘（36）沿倾斜槽（31）上升，导致密封段（24）径向向外移动并增加密封间隙。 然而，在稳定的发动机运行期间，壳体（30）和叶片（32）之间的相对轴向运动减小。 外凸缘（36）沿倾斜槽（31）向下收缩以使密封段（24）径向向内移动; 该组合减少了顶端间隙，并防止气体泄漏。

公开(公告)号：US07021896B2

公开(公告)日：2006-04-04

申请号：US10843381

申请日：2004-05-12

申请人： Alec G Dodd

发明人： Alec G Dodd

IPC分类号： F01D5/18

CPC分类号： F01D5/187

摘要： A turbine blade (20) has cooling air passageways (30) and (30a, 30b, 30c.) through the leading edge wall portion (24) which are positionally arranged so as to intersect each other within the wall thickness so as to transmit mechanical stresses into the thicker, non-perforated material of the blade aerofoil (22). Further passageways near the blade root portion (42) do not intersect, the reduced cooling in that area causes expansion and stress absorption.

摘要翻译： 涡轮叶片（20）具有穿过前缘壁部分（24）的冷却空气通道（30）和（30a，30b，30c），所述前缘壁部分位于所述壁厚度内彼此相交， 以将机械应力传递到叶片翼型（22）的较厚的非穿孔材料中。 在叶片根部（42）附近的其它通道不相交，在该区域中减少的冷却导致膨胀和应力吸收。

公开(公告)号：US06467167B2

公开(公告)日：2002-10-22

申请号：US09759529

申请日：2001-01-16

申请人： Alec G Dodd

发明人： Alec G Dodd

IPC分类号： B21D5378

CPC分类号： F01D5/189 ,  B23P15/04 ,  Y10T29/49336 ,  Y10T29/49337 ,  Y10T29/49339

摘要： A hollow liner (14) for fitting in the interior of a aerofoil vane (10) is crimped prior to fitting within the vane (10). Following fitting, the liner (14) is expanded so as to fit snugly within the vane (10). The technique permits the insertion of liners (14) into vanes (10) that are so configured as to preclude the insertion of conventional liners.

摘要翻译： 用于安装在翼型叶片（10）的内部的空心衬套（14）在装配在叶片（10）之前被卷曲。 在安装之后，衬套（14）膨胀以便紧密地配合在叶片（10）内。 这种技术允许将衬垫（14）插入叶片（10），叶片（10）被配置成阻止常规衬垫的插入。

公开(公告)号：US6048170A

公开(公告)日：2000-04-11

申请号：US210851

申请日：1998-12-15

申请人： Alec G Dodd

发明人： Alec G Dodd

IPC分类号： F01D11/00 ,  F01D11/24 ,  F01D25/24 ,  F01D25/26

CPC分类号： F01D25/246 ,  F01D11/005 ,  F01D11/24

摘要： A variable diameter shroud ring (21) for the turbine of a gas turbine engine (10) comprises a support structure (25) which carries an annular array of circumferentially spaced apart ceramic segments (26). The radially outer surfaces of the segments (26) are overlaid by a plurality of circumferentially extending metallic sheets (38). The sheets (38) serve to inhibit gas leakage through gaps between the segments (26) as the diameter of the shroud ring (21) is varied.

摘要翻译： 用于燃气涡轮发动机（10）的涡轮机的可变直径护罩环（21）包括承载环形间隔开的陶瓷段（26）的环形阵列的支撑结构（25）。 所述段（26）的径向外表面由多个周向延伸的金属片（38）重叠。 当护罩环（21）的直径变化时，片材（38）用于阻止通过节段（26）之间的间隙的气体泄漏。

公开(公告)号：US06598657B2

公开(公告)日：2003-07-29

申请号：US10092533

申请日：2002-03-08

申请人： Alec G Dodd

发明人： Alec G Dodd

IPC分类号： B22D2704

CPC分类号： B22D27/045

摘要： A mold support (110) is disclosed for supporting a plurality of molds (109) in a casting apparatus having a first zone for introducing molten material into the molds and a second zone in which the material in the molds can cool. The mold support (110) is capable of relative movement from the first zone to the second zone thereby forming a solidification front in the material in each mold, whereby the solidification front moves through the material as the material solidifies. Each mold (109) defines a main axis (A) along which the solidification front can move and a centrally extending plane (P) perpendicular to the main axis. The mold support (110) comprises carrying means upon which the molds (109) can be disposed. The geometry of the carrying means is such that the centrally extending plane of a first mold (109) arranged on the carrying means at or towards a central region thereof is not co-planar with the centrally extending plane of a second mold spaced from the first mold (109) away from the central region, and such that the main axis (A) of each mold (109) extends substantially perpendicular to the solidification front to be formed therein.

公开(公告)号：US06511285B2

公开(公告)日：2003-01-28

申请号：US10062511

申请日：2002-02-05

申请人： Alec G Dodd

发明人： Alec G Dodd

IPC分类号： F01D904

CPC分类号： F01D25/246 ,  F01D5/146 ,  F01D9/041 ,  F01D11/005

摘要： Two stages of relatively rotatable guide vanes (22,24) are arranged in tandem. Shroud portions (42,46) on the vanes overlap in loose engagement, until an associated gas turbine engine starts operating. Gas loads then act on the downstream vane stage (24) and move it in a downstream direction until the opposing flanks of radially opposing lands (44,48) on respective shrouds (42,46) engage, whereupon, gas leakage via the overlap onto the turbine casing (40) is at least substantially reduced.

摘要翻译： 两级相对旋转的导向叶片（22,24）串列布置。 叶片上的护罩部分（42,46）以松散接合重叠，直到相关联的燃气涡轮发动机开始运转。 然后，气体负载作用在下游叶片台（24）上并沿着下游方向移动，直到相应的护罩（42,46）上的径向相对的平台（44,48）的相对侧面接合，于是气体通过重叠泄漏到 涡轮机壳体（40）至少大大减小。