公开(公告)号：US09650915B2

公开(公告)日：2017-05-16

申请号：US14407051

申请日：2013-06-14

申请人： GE AVIO S.R.L.

发明人： Paolo Calza ,  Matteo Usseglio

IPC分类号： F01D5/16 ,  F01D25/06 ,  F01D5/22 ,  F01D9/04

CPC分类号： F01D25/06 ,  F01D5/16 ,  F01D5/22 ,  F01D5/225 ,  F01D9/041 ,  F05D2220/32 ,  F05D2250/312 ,  F05D2260/961 ,  Y02T50/671 ,  Y02T50/673

摘要： An aerofoil array for a gas turbine system has an inner annular platform and an outer annular platform, which extend about a longitudinal axis and radially delimit an annular channel for a gas flow; the annular channel houses a plurality of aerofoils, arranged at a substantially constant angular pitch and comprising respective central portions and respective ends connected to the platforms; the aerofoils are formed by two series of aerofoils having a different geometrical feature in order to intentionally vary the eigenfrequencies and arranged about the longitudinal axis with a sequence that is regularly repeated all along the annular channel; even though the external geometry of the aerofoils is varied, the cross-sections remain unchanged in the central portions, at any given radius with respect to the longitudinal axis.

公开(公告)号：US20220098987A1

公开(公告)日：2022-03-31

申请号：US17388143

申请日：2021-07-29

申请人： GE Avio S.r.l.

发明人： Massimiliano Airaudo ,  Paolo Calza ,  Francesco Bertini ,  Matteo Renato Usseglio ,  Cristian Lizzer ,  Ernesto Sozio ,  Matteo Furfaro ,  Marco Thiene

IPC分类号： F01D5/18 ,  F01D5/14

摘要： A turbine blade including an airfoil portion extending between a leading edge and a trailing edge, a base portion positioned below the airfoil portion, the base portion including an outwardly-extending wing positioned below the airfoil portion, and an aero-brake feature positioned between the outwardly-extending wing and the airfoil portion and extending outward from the base portion, where the aero-brake feature is structurally configured to disrupt axial airflow across the turbine blade.

公开(公告)号：US20150110604A1

公开(公告)日：2015-04-23

申请号：US14407051

申请日：2013-06-14

申请人： GE AVIO S.R.L.

发明人： Paolo Calza ,  Matteo Usseglio

IPC分类号： F01D25/06 ,  F01D9/04

CPC分类号： F01D25/06 ,  F01D5/16 ,  F01D5/22 ,  F01D5/225 ,  F01D9/041 ,  F05D2220/32 ,  F05D2250/312 ,  F05D2260/961 ,  Y02T50/671 ,  Y02T50/673

摘要： An aerofoil array for a gas turbine system has an inner annular platform and an outer annular platform, which extend about a longitudinal axis and radially delimit an annular channel for a gas flow; the annular channel houses a plurality of aerofoils, arranged at a substantially constant angular pitch and comprising respective central portions and respective ends connected to the platforms; the aerofoils are formed by two series of aerofoils having a different geometrical feature in order to intentionally vary the eigenfrequencies and arranged about the longitudinal axis with a sequence that is regularly repeated all along the annular channel; even though the external geometry of the aerofoils is varied, the cross-sections remain unchanged in the central portions, at any given radius with respect to the longitudinal axis.

摘要翻译： 用于燃气涡轮机系统的机翼阵列具有内环形平台和外环形平台，其围绕纵向轴线延伸并径向限定用于气流的环形通道; 环形通道容纳多个翼状件，其以基本恒定的角度间距布置，并且包括相应的中心部分和相应的端部连接到平台; 机翼由具有不同几何特征的两系列机翼形成，以有意地改变本征频率并围绕纵向轴线布置，其具有沿着环形通道定期重复的顺序; 即使翼型的外部几何形状是变化的，横截面在相对于纵向轴线的任何给定半径处在中心部分保持不变。