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1. 发明授权

US06695036B2 Method for producing a cast part, model mold, and ceramic insert for use in this method 有权
标题翻译：用于该方法的铸造件，型号模具和陶瓷刀片的制造方法
公开(公告)号：US06695036B2
公开(公告)日：2004-02-24
申请号：US09991991
申请日：2001-11-26
申请人： Herbert Brandl , Alexander Hoffs , Roland Muecke , Sergej Riazantsev , Alexander Beeck
发明人： Herbert Brandl , Alexander Hoffs , Roland Muecke , Sergej Riazantsev , Alexander Beeck
IPC分类号： B22C904
CPC分类号： B22C21/14 , B22C7/02 , B22C9/04
摘要： The invention relates to a method for producing a cast part of a thermal turbo-machine by way of a known casting process. Between a model mold and a ceramic insert, projections are located on the ceramic insert, whereby the projections have an angle (&agr;, &bgr;) between the center line and the outer edge of the projections of less than 30°, and whereby the projections are used both for the fixation of the insert during the casting process and for the reduction of the notch factor inside the recesses created in the cast part.
摘要翻译：本发明涉及通过已知的铸造工艺制造热涡轮机的铸造件的方法。在模型模具和陶瓷插入件之间，突起位于陶瓷插入件上，由此突起在中心线和突起的外边缘之间具有小于30°的角度（α，β），由此突出部用于在铸造过程期间固定插入件并且用于减少在铸造部件中产生的凹部内的凹口因数。

2. 发明授权

US06962484B2 Moving blade for a turbomachine 失效
标题翻译：用于涡轮机的叶片
公开(公告)号：US06962484B2
公开(公告)日：2005-11-08
申请号：US10407251
申请日：2003-04-07
申请人： Herbert Brandl , Alexander Hoffs
发明人： Herbert Brandl , Alexander Hoffs
IPC分类号： F01D5/14 , B22C9/22 , F01D5/16 , F01D5/20 , F01D5/22 , F04D29/38
CPC分类号： F01D5/225 , F01D5/16 , F05D2230/21 , F05D2250/232 , F05D2250/292
摘要： This arrangement relates to a moving blade (1), cast in one piece, for a turbomachine, in particular a turbine or compressor, comprising an aerodynamically shaped profile body (2) which has a shroud band (5). The shroud band (5) projects beyond the profile body (2) in the circumferential direction (6) and has a fin (12). The fin (12) possesses a base portion (14), a transitional portion (15) and a sealing portion (16). An axially measured wall thickness decreases in a transitional portion (15) from the base portion (14) to the sealing portion (16). To avoid a porous structure in the base portion (14), two depressions (17), which reduce the wall thickness of the base portion (14), are integrally molded on the outside of the base portion (14).
摘要翻译：这种布置涉及一种用于涡轮机（特别是涡轮或压缩机）一体铸造的动叶片（1），其包括具有护罩带（5）的空气动力学形状的轮廓体（2）。护罩带（5）在圆周方向（6）上突出超过型体（2），并具有翅片（12）。翅片（12）具有基部（14），过渡部分（15）和密封部分（16）。在从基部（14）到密封部分（16）的过渡部分（15）中轴向测量的壁厚度减小。为了避免基部（14）中的多孔结构，在基部（14）的外侧一体地模制两个减小基部（14）的壁厚的凹部（17）。

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