公开(公告)号：US20130004320A1

公开(公告)日：2013-01-03

申请号：US13170566

申请日：2011-06-28

申请人： Edmundo Jesus Perret ,  Michael J. Minor ,  Michael L. Miller ,  Stanley B. Brenton

发明人： Edmundo Jesus Perret ,  Michael J. Minor ,  Michael L. Miller ,  Stanley B. Brenton

IPC分类号： F04D29/38 ,  B23P15/00

CPC分类号： F01D5/005 ,  B23P6/002 ,  F01D9/041 ,  F05D2230/80 ,  F05D2240/12 ,  Y10T29/49236

摘要： A method for forming a nozzle segment for a turbine stage of a gas turbine engine to a specific measurement range for a throat area. The nozzle segment comprising an inner platform, and outer platform, and a plurality of airfoils between the inner platform and outer platform. A requested throat area measurement is obtained for the nozzle segment, and a starting stacking angle for a plurality of through holes and pockets corresponding to the airfoils for both the inner platform and outer platform is selected, which are then machined. The airfoils, inner platform, and outer platform are assembled to form a vane segment that is machined to obtain a finished throat area. The finished throat area is measured, and a determination is made if the measured finish throat area complies with the requested throat area.

摘要翻译： 一种用于将燃气涡轮发动机的涡轮级的喷嘴段形成到用于喉部区域的特定测量范围的方法。 所述喷嘴段包括内平台和外平台，以及在所述内平台和外平台之间的多个翼型件。 对于喷嘴段获得所需的喉部测量，并且选择与用于内平台和外平台的翼型相对应的多个通孔和凹穴的起始堆叠角度，然后对其进行机加工。 组装翼型件，内平台和外平台以形成叶片段，其被加工以获得成品喉部区域。 测量完成的喉部区域，并且确定测量的完成喉部区域是否符合要求的喉部区域。