公开(公告)号：US20150098831A1

公开(公告)日：2015-04-09

申请号：US14568706

申请日：2014-12-12

Applicant: ALSTOM Technology Ltd

Inventor： Herbert BRANDL ,  Hans-Peter BOSSMANN ,  Philipp INDLEKOFER

IPC: F01D5/30 ,  F01D9/04

CPC classification number: F01D5/303 ,  F01D5/147 ,  F01D5/3007 ,  F01D5/3092 ,  F01D9/04 ,  F01D11/008 ,  F05D2240/30 ,  F05D2260/36

Abstract: A rotor blade arrangement (20), especially for a gas turbine, which can be fastened on a blade carrier (19) and includes in each case a blade aerofoil element (10) and a platform element (14), wherein the platform elements (14) of a blade row form a continuous inner shroud. With such a blade arrangement, a mechanical decoupling, which extends the service life, is achieved by the blade aerofoil element (10) and the platform element (14) being formed as separate elements and by being able to be fastened in each case separately on the blade carrier (19).

Abstract translation: 一种特别用于燃气轮机的转子叶片装置（20），其可以紧固在叶片载体（19）上并且在每种情况下包括叶片翼型件（10）和平台元件（14），其中平台元件 叶片排形成一个连续的内护罩。 利用这种叶片装置，延长使用寿命的机械解耦通过叶片机翼元件（10）和平台元件（14）形成为分离的元件并且能够在每种情况下分开地固定在 叶片载体（19）。

公开(公告)号：US20130058788A1

公开(公告)日：2013-03-07

申请号：US13668136

申请日：2012-11-02

Applicant: Alstom Technology Ltd

Inventor： Herbert BRANDL ,  Igor TSYPKAKYIN ,  Philipp INDLEKOFER

IPC: F01D5/08 ,  B23P15/02 ,  F01D5/02

CPC classification number: F01D5/225 ,  F01D5/187 ,  Y10T29/49341

Abstract: A turbine blade is provided and includes a tip end carrying a shroud and at least one fin, which extends radially away from the shroud. The fin includes a first sidewall and a second sidewall, which are spaced apart, arranged parallel to each other, and are connected to the shroud, and a cutting edge, which is connected to the first and second sidewalls. The cutting edge thereby creates a hollow space between the sidewalls, the shroud, and the cutting edge, and further extends radially away from the first and second sidewalls. Also provided is a method of manufacturing the blade by casting the blade as single piece with the hollow fin or by forging the blade; and machining the fin to create the first and second sidewalls and cutting edge thereby opening the hollow space between said sidewalls and the cutting edge.

Abstract translation: 涡轮机叶片被设置并且包括承载护罩的末端和至少一个翅片，其从护罩径向延伸。 翅片包括第一侧壁和第二侧壁，第一侧壁和第二侧壁间隔开，彼此平行设置并且连接到护罩，以及连接到第一和第二侧壁的切割边缘。 因此，切割边缘在侧壁，护罩和切割边缘之间形成中空空间，并进一步从第一和第二侧壁径向延伸。 还提供了通过将叶片与中空翅片一体铸造或通过锻造叶片来制造叶片的方法; 并且加工翅片以产生第一和第二侧壁和切割刃，从而打开所述侧壁和切割边缘之间的中空空间。