公开(公告)号：US07321185B2

公开(公告)日：2008-01-22

申请号：US11370377

申请日：2006-03-06

申请人： Marc R. Schultz

发明人： Marc R. Schultz

IPC分类号： H01L41/08 ,  H01L41/12 ,  H02N2/00 ,  H02N10/00

CPC分类号： B64C3/52 ,  B64C9/00 ,  B64C23/06 ,  F01D5/145 ,  F01D5/148 ,  F02M29/06 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2250/713 ,  F05D2300/603 ,  F05D2300/614 ,  F05D2300/702 ,  Y02T50/162 ,  Y02T50/44 ,  Y02T50/672 ,  Y02T50/673

摘要： Two similarly shaped, such as rectangular, shells are attached to one another such that they form a resulting thin airfoil-like structure. The resulting device has at least two stable equilibrium shapes. The device can be transformed from one shape to another with a snap-through action. One or more actuators can be used to effect the snap-through; i.e., transform the device from one stable shape to another. Power to the actuators is needed only to transform the device from one shape to another.

摘要翻译： 两个类似的形状，例如矩形的壳彼此附接，使得它们形成所得到的薄翼型结构。 所得到的装置具有至少两个稳定的平衡形状。 通过快照操作可以将设备从一种形状转换为另一种形状。 可以使用一个或多个致动器来实现卡通; 即将设备从一个稳定的形状转换到另一个。 仅需要对致动器的电力才能将设备从一种形状转换到另一种形状。

公开(公告)号：US07290986B2

公开(公告)日：2007-11-06

申请号：US11162433

申请日：2005-09-09

申请人： Mark Edward Stegemiller ,  Chander Prakash ,  Leslie Eugene Leeke ,  Kevin Samuel Klasing ,  Ching-Pang Lee

发明人： Mark Edward Stegemiller ,  Chander Prakash ,  Leslie Eugene Leeke ,  Kevin Samuel Klasing ,  Ching-Pang Lee

IPC分类号： F01D5/20

CPC分类号： F01D5/20 ,  F05D2250/71 ,  F05D2250/712 ,  Y02T50/67

摘要： An airfoil for a gas turbine engine includes a root, a tip, a leading edge, a trailing edge, and opposed pressure and suction sidewalls extending generally along a radial axis. The airfoil includes a tip cap extending between the pressure and suction sidewalls; and spaced-apart suction-side and pressure-side tip walls extending radially outward from the tip cap to define a tip cavity therebetween. The pressure-side tip wall includes a continuously concave curved arcuate portion, at least a section of which extends circumferentially outward from a radial axis of the airfoil.

摘要翻译： 用于燃气涡轮发动机的翼型件包括根部，尖端，前缘，后缘以及大致沿径向轴线延伸的相对的压力和吸力侧壁。 翼型件包括在压力侧和吸力侧壁之间延伸的顶盖; 并且间隔开的吸入侧和压力侧尖端壁从尖端帽径向向外延伸以在它们之间限定尖端腔。 压力侧末端壁包括连续凹入的弯曲弧形部分，其至少一部分从翼型件的径向轴向向外延伸。

公开(公告)号：US07261518B2

公开(公告)日：2007-08-28

申请号：US11088639

申请日：2005-03-24

申请人： Samuel Golinkin ,  Michael J. Lipski ,  John S. Loudon ,  Gennaro J. DiOrio ,  Timothy Ewer

发明人： Samuel Golinkin ,  Michael J. Lipski ,  John S. Loudon ,  Gennaro J. DiOrio ,  Timothy Ewer

IPC分类号： B63H1/20

CPC分类号： F01D5/3046 ,  F01D5/3007 ,  F01D5/3038 ,  F01D5/32 ,  F05D2240/80 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2260/30 ,  F05D2300/50212

摘要： A locking arrangement for a row of radial entry blades (62) of a turbo-machine. A closing blade (66) includes a root portion (74) having an axial attachment shape (78) for engagement with an axially oriented slot having an axial attachment shape (76) formed at the entering slot location (34) of the radial entry rotor disk (56). For applications utilizing blades with curved platform faces (112), a preceding blade (108) and a following blade (110) in the row are designed with one curved face for abutting adjacent radial entry blades and one flat face (120) for abutting the flat closing blade faces (116). The closing blade (84) may be designed with a root portion (88) having two legs (90,92) that are urged apart by a key (86) into tight contact with the adjacent blades.

摘要翻译： 用于涡轮机的一排径向进入叶片（62）的锁定装置。 闭合叶片（66）包括具有轴向附接形状（78）的根部（74），用于与形成在径向进入转子的进入槽位置（34）处的轴向附接形状（76）的轴向定向的槽接合 盘（56）。 对于使用具有弯曲平台面（112）的刀片的应用，行中的前刀片（108）和后刀片（110）设计有一个弯曲面，用于邻接相邻的径向入口刀片和一个平面（120），用于邻接 平的闭合叶片面（116）。 封闭叶片（84）可以设计成具有两个腿部（90,92）的根部（88），所述两个腿部（90,92）被钥匙（86）推压而与相邻叶片紧密接触。

公开(公告)号：US20070144139A1

公开(公告)日：2007-06-28

申请号：US10588600

申请日：2005-08-31

申请人： Osamu Kawamoto ,  Hiroki Nagata ,  Masayuki Fukutani ,  Mineyasu Oana

发明人： Osamu Kawamoto ,  Hiroki Nagata ,  Masayuki Fukutani ,  Mineyasu Oana

IPC分类号： F02C7/052

CPC分类号： F02K3/06 ,  F02C7/05 ,  F02C7/052 ,  F05D2220/326 ,  F05D2220/327 ,  F05D2250/323 ,  F05D2250/71 ,  F05D2260/607 ,  Y02T50/675

摘要： [Object] To provide a gas turbine engine which is simple in structure but can effectively remove foreign matters from the combustion air. [Means] The intake passage 21 includes an inlet portion 29, a curved portion 30 and a reduced diameter portion 31. The bypass duct 24 is curved away from the central axial line CL in a region corresponding to the curved portion 30 and reduced diameter portion 31 of the intake passage 29. Between the intake passage 29 and bypass duct 24 is defined an annular space 32. In the reduced diameter portion 31, the outer liner 20 is formed with a large number of foreign matter introduction openings 33 in a circumferential arrangement for communication between the intake passage 21 and annular space 32. The inner casing 4 is formed with a plurality of foreign matter ejection holes 34 in a circumferential arrangement in a part thereof that curves outward for communication between the annular space 32 and bypass duct 24.

摘要翻译： 提供一种结构简单但能有效地除去燃烧空气中的异物的燃气涡轮发动机。 入口通道21包括入口部分29，弯曲部分30和缩径部分31。 在对应于进气通道29的弯曲部分30和减小直径部分31的区域中，旁通管道24从中心轴线CL弯曲。 在进气通道29和旁通管24之间限定有环形空间32。 在减径部31中，外衬套20形成有大量异物导入开口33，其周向布置成用于连通进气通道21和环形空间32。 内壳4形成有多个异物排出孔34，其周向布置在其一部分中，向外弯曲，用于环形空间32和旁路管道24之间的连通。

公开(公告)号：US20070120011A1

公开(公告)日：2007-05-31

申请号：US11370377

申请日：2006-03-06

申请人： Marc Schultz

发明人： Marc Schultz

IPC分类号： B64C13/00

CPC分类号： B64C3/52 ,  B64C9/00 ,  B64C23/06 ,  F01D5/145 ,  F01D5/148 ,  F02M29/06 ,  F05D2250/70 ,  F05D2250/71 ,  F05D2250/711 ,  F05D2250/712 ,  F05D2250/713 ,  F05D2300/603 ,  F05D2300/614 ,  F05D2300/702 ,  Y02T50/162 ,  Y02T50/44 ,  Y02T50/672 ,  Y02T50/673

摘要： Two similarly shaped, such as rectangular, shells are attached to one another such that they form a resulting thin airfoil-like structure. The resulting device has at least two stable equilibrium shapes. The device can be transformed from one shape to another with a snap-through action. One or more actuators can be used to effect the snap-through; i.e., transform the device from one stable shape to another. Power to the actuators is needed only to transform the device from one shape to another.

摘要翻译： 两个类似的形状，例如矩形的壳彼此附接，使得它们形成所得到的薄翼型结构。 所得到的装置具有至少两个稳定的平衡形状。 通过快照操作可以将设备从一种形状转换为另一种形状。 可以使用一个或多个致动器来实现卡通; 即将设备从一个稳定的形状转换到另一个。 仅需要对致动器的电力才能将设备从一种形状转换到另一种形状。

公开(公告)号：US20070119145A1

公开(公告)日：2007-05-31

申请号：US11289035

申请日：2005-11-29

申请人： Lisa O'Neill ,  Edward Pietraszkiewicz ,  Richard Silverman ,  Barry Beckwith

发明人： Lisa O'Neill ,  Edward Pietraszkiewicz ,  Richard Silverman ,  Barry Beckwith

IPC分类号： F02C7/052

CPC分类号： F04D29/542 ,  B01D45/08 ,  F01D5/082 ,  F01D9/02 ,  F02C7/052 ,  F04D29/701 ,  F05D2250/71 ,  F05D2260/607 ,  F23R3/04

摘要： A compressor diffuser for a gas turbine engine is provided with a dirt separator. The dirt separator ensures the air having moved downstream of the compressor section, and moving toward the combustion section, is separated into a dirtier air flow path directly radially outwardly, and a cleaner airflow path directed radially inwardly. In this manner, the air reaching a combustion section, and the air being utilized for radially inner cooling air is relatively cleaner air. Further, the dirt separator provides a convenient surface for mounting a pressure sensor. In one embodiment, the dirt separator is mounted within the diffuser housing, and in a second embodiment, it is mounted immediately downstream.

摘要翻译： 用于燃气涡轮发动机的压缩机扩散器设置有污垢分离器。 污垢分离器确保已经移动到压缩机部分的下游并且朝向燃烧部分移动的空气被直接径向向外分离成更脏的气流路径和径向向内指向的清洁气流路径。 以这种方式，到达燃烧部分的空气和用于径向内部冷却空气的空气是相对较干净的空气。 此外，污垢分离器提供用于安装压力传感器的方便的表面。 在一个实施例中，污物分离器安装在扩散器壳体内，并且在第二实施例中，其被立即安装在下游。

公开(公告)号：US20070059188A1

公开(公告)日：2007-03-15

申请号：US11242344

申请日：2005-10-03

申请人： Brock Fraser ,  Adam Reinke ,  Neal Narron

发明人： Brock Fraser ,  Adam Reinke ,  Neal Narron

IPC分类号： F04B17/00

CPC分类号： F02C6/12 ,  F01D25/183 ,  F04D25/04 ,  F04D29/063 ,  F04D29/083 ,  F04D29/4206 ,  F05D2220/40 ,  F05D2240/55 ,  F05D2250/314 ,  F05D2250/70 ,  F05D2250/71

摘要： A turbocharger unit having an aerodynamically enhanced pocket, comprising a turbine having a turbine housing and a turbine wheel connected to a shaft along with a compressor having a compressor housing and a compressor wheel mounted on the same shaft. There is an intermediate housing disposed between the turbine housing and the compressor housing, circumscribing the shaft, and having a compressor wheel pocket. There is a series of bearings located in the intermediate housing for supporting the shaft. There is also a series of fluid passages located in the intermediate housing which provide fluid to lubricate the bearings. A seal is used for the prevention of oil from entering the compressor wheel pocket. The compressor wheel pocket has an aerodynamically enhanced pocket for the improvement of pressure balance behind the compressor wheel, preventing the oil in the intermediate housing from entering the compressor housing.

摘要翻译： 一种具有空气动力学增强的袋的涡轮增压器单元，包括具有涡轮机壳体的涡轮机和连接到轴的涡轮机叶轮以及具有安装在同一轴上的压缩机壳体和压缩机叶轮的压缩机。 存在设置在涡轮壳体和压缩机壳体之间的中间壳体，其包围轴并且具有压缩机轮槽。 位于中间壳体中的一系列轴承用于支撑轴。 还有一系列位于中间壳体中的流体通道，其提供润滑轴承的流体。 密封件用于防止油进入压缩机轮袋。 压缩机轮袋具有空气动力学增强的袋，用于改善压缩机叶轮后面的压力平衡，防止中间壳体中的油进入压缩机壳体。

公开(公告)号：US07189055B2

公开(公告)日：2007-03-13

申请号：US11139607

申请日：2005-05-31

申请人： Remo Marini ,  Sri Sreekanth

发明人： Remo Marini ,  Sri Sreekanth

IPC分类号： F01D5/00

CPC分类号： F01D5/081 ,  F05D2240/126 ,  F05D2250/314 ,  F05D2250/322 ,  F05D2250/71

摘要： A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.

摘要翻译： 提供了一种偏转器装置，用于通过向进入燃气涡轮发动机的工作流体流动路径的泄漏流赋予添加的切向速度来提高涡轮机效率。

公开(公告)号：US20060269398A1

公开(公告)日：2006-11-30

申请号：US11139607

申请日：2005-05-31

申请人： Remo Marini ,  Sri Sreekanth

发明人： Remo Marini ,  Sri Sreekanth

IPC分类号： F03B11/00

CPC分类号： F01D5/081 ,  F05D2240/126 ,  F05D2250/314 ,  F05D2250/322 ,  F05D2250/71

摘要： A deflector arrangement is provided for improving turbine efficiency by imparting added tangential velocity to a leakage flow entering the working fluid flowpath of a gas turbine engine.

摘要翻译： 提供了一种偏转器装置，用于通过向进入燃气涡轮发动机的工作流体流动路径的泄漏流赋予添加的切向速度来提高涡轮机效率。

公开(公告)号：US20060239841A1

公开(公告)日：2006-10-26

申请号：US11111224

申请日：2005-04-21

申请人： Edward Panek

发明人： Edward Panek

IPC分类号： F04B17/00

CPC分类号： F01D25/186 ,  F02C7/24 ,  F05D2220/40 ,  F05D2240/127 ,  F05D2250/11 ,  F05D2250/13 ,  F05D2250/71

摘要： A turbocharger (10) with a heat shield (60) positioned between the turbine wheel (30) and the bearing housing (20), wherein the heat shield defines a gap (70) between the turbine wheel (30). The heat shield (60) and is provided with at least one rib (80) extending into the gap. In this gap, in the case of a conventional flat heat shield, the turbine wheel backface may act in the manner of a centrifugal pumping, pumping gas out from within the gap, creating a region of reduced pressure adjacent the outboard side of the turbine shaft bearing, drawing oil out the shaft bearing and into the space between the turbine wheel backface and the heat shield. The inventive heat shield has raised structures designed to interfere with the rotational and centrifugal flow of gas in the gap between heat shield and turbine wheel backface, thus prevent oil bypass.

摘要翻译： 一种涡轮增压器（10），其具有定位在涡轮机叶轮（30）和轴承壳体（20）之间的隔热罩（60），其中，热屏蔽件限定了涡轮机叶轮（30）之间的间隙（70）。 隔热罩（60）并且设置有延伸到间隙中的至少一个肋（80）。 在这个间隙中，在传统的平面隔热罩的情况下，涡轮机背面可以以离心泵送的方式起作用，从气隙中排出气体，产生邻近涡轮轴外侧的减压区域 轴承，抽出轴轴承并进入涡轮机背面和隔热罩之间的空间。 本发明的隔热罩具有设计成干扰隔热罩和涡轮机背面之间的间隙中的气体的旋转和离心流动的凸起结构，从而防止油旁路。