公开(公告)号：US20100196139A1

公开(公告)日：2010-08-05

申请号：US12363892

申请日：2009-02-02

Applicant: Alexander R. Beeck ,  Shantanu P. Mhetras

Inventor： Alexander R. Beeck ,  Shantanu P. Mhetras

IPC: F04D29/08

CPC classification number: F04D29/102 ,  F04D25/16

Abstract: A sealing system is applied to the interface between a stator and a rotor in a turbine engine to minimize fluid leakage across the interface. One interface can be defined between portions of neighboring rotor disks and a stator. The sealing system includes one or more rows of flow guides, such as airfoils, provided on the rotor disk near the upstream end of the interface. These flow guides can impart tangential velocity on the leakage flow. One or more undulating seal structures can be connected to the stator downstream of the flow guides. These undulating seals can have a periodic waveform conformation. The undulating seals can create unsteadiness in the flow and recirculation of the leakage flow, which causes losses. The sealing system can also include other types of seals, such as labyrinth seals and brush seals, to further create a tortuous path for any leakage flow.

Abstract translation: 将密封系统应用于涡轮发动机中的定子和转子之间的界面，以最小化穿过界面的流体泄漏。 一个接口可以在相邻的转子盘和定子的部分之间限定。 密封系统包括设置在接近上游端的转子盘上的一排或多排流动引导件，例如翼型件。 这些流动导向器可以在泄漏流上产生切向速度。 一个或多个起伏密封结构可以连接到导流器下游的定子。 这些起伏密封件可以具有周期性的波形构型。 起伏密封件可能导致泄漏流量的流动和再循环不稳定，从而导致损耗。 密封系统还可以包括其它类型的密封件，例如迷宫式密封件和刷子密封件，以进一步产生用于任何泄漏流动的曲折路径。

公开(公告)号：US07722326B2

公开(公告)日：2010-05-25

申请号：US11717238

申请日：2007-03-13

Applicant: Alexander R. Beeck ,  Sanjay Chopra

Inventor： Alexander R. Beeck ,  Sanjay Chopra

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2220/3215 ,  F05D2250/32 ,  F05D2260/201

Abstract: A cooling system designed to cool the trailing edge of a turbine blade usable in rear stages of a turbine engine. The turbine blade may have a leading edge cooling cavity and a trailing edge cooling cavity separated by an impingement rib. The cooling system may exhaust cooling fluids through the tip of the turbine blade rather than through the trailing edge of the turbine blade to prevent premature failure at the trailing edge of the turbine blade.

Abstract translation: 一种设计用于冷却可用于涡轮发动机后级的涡轮叶片的后缘的冷却系统。 涡轮叶片可以具有前缘冷却腔和由冲击肋分开的后缘冷却腔。 冷却系统可以将冷却流体排出通过涡轮叶片的尖端，而不是通过涡轮机叶片的后缘排出，以防止在涡轮叶片的后缘处的过早失效。

公开(公告)号：US20090081048A1

公开(公告)日：2009-03-26

申请号：US12226534

申请日：2007-03-09

Applicant: Alexander R. Beeck ,  Stefan Hoffmann

Inventor： Alexander R. Beeck ,  Stefan Hoffmann

IPC: F01D5/18

CPC classification number: F23R3/14 ,  F01D5/18 ,  F01D9/065 ,  F02C3/16 ,  F02K3/08 ,  F02K3/10 ,  F23C2900/07001 ,  F23R3/286

Abstract: The invention relates to a blade for a turbine comprising a blade wall, a first channel for guiding a first medium and a second channel for guiding a second medium that can be supplied to the turbine blade separately from the first medium. In order to combine both media, which are supplied separately, into one mixture, a turbine blade has least one chamber which is arranged in the interior or in the blade wall and said chamber is connected to said channels via a respective connection line. In order to provide a particularly simple component that is economical to produce, the chamber and/or the outlet conduit are a least partially delimited and/or formed by an insert accommodated in the wall.

Abstract translation: 本发明涉及一种用于涡轮机的叶片，其包括叶片壁，用于引导第一介质的第一通道和用于引导可与第一介质分开供应到涡轮叶片的第二介质的第二通道。 为了将分别供应的两种介质组合成一种混合物，涡轮机叶片具有布置在内部或叶片壁中的至少一个室，并且所述室经由相应的连接线连接到所述通道。 为了提供生产经济的特别简单的部件，腔室和/或出口导管由容纳在壁中的插入件至少部分地界定和/或形成。

公开(公告)号：US20080226461A1

公开(公告)日：2008-09-18

申请号：US11717238

申请日：2007-03-13

Applicant: Alexander R. Beeck ,  Sanjay Chopra

Inventor： Alexander R. Beeck ,  Sanjay Chopra

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2220/3215 ,  F05D2250/32 ,  F05D2260/201

Abstract: A cooling system designed to cool the trailing edge of a turbine blade usable in rear stages of a turbine engine. The turbine blade may have a leading edge cooling cavity and a trailing edge cooling cavity separated by an impingement rib. The cooling system may exhaust cooling fluids through the tip of the turbine blade rather than through the trailing edge of the turbine blade to prevent premature failure at the trailing edge of the turbine blade.

Abstract translation: 一种设计用于冷却可用于涡轮发动机后级的涡轮叶片的后缘的冷却系统。 涡轮叶片可以具有前缘冷却腔和由冲击肋分开的后缘冷却腔。 冷却系统可以将冷却流体排出通过涡轮叶片的尖端，而不是通过涡轮机叶片的后缘排出，以防止在涡轮叶片的后缘处的过早失效。