公开(公告)号：WO1994012771A1

公开(公告)日：1994-06-09

申请号：PCT/US1993011254

申请日：1993-11-19

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  SYLVESTRO, Joseph, A. ,  LINASK, Indrik ,  BEABOUT, Brian, K.

IPC: F01D05/18

CPC classification number: F01D5/187 ,  Y02T50/676

Abstract: A turbine airfoil (32) having a cut-back trailing edge (62) and a plurality of diffusing flow dividers (68) upstream of the cut-back trailing edge (62) is disclosed. Various construction details are developed which provide ejection of a diffusing film of cooling fluid over a cut-back trailing edge (62). In one particular embodiment, a turbine airfoil (32) includes a plurality of radially spaced flow dividers (68) extending between a pressure wall (56) and a suction wall (58). Each flow divider (68) includes a rounded leading edge (74), a pair of parallel sidewalls (82) downstream of the leading edge (74), and a pair of converging sidewalls (86) downstream of the parallel sidewalls (82). Adjacent sidewalls of adjacent flow dividers form flow channels (72) having a constant area channel (76) and a diffusing section. The diffusing section includes a covered portion (94) upstream of the cut-back trailing edge (62) and an uncovered portion (96) extending over the cut-back trailing edge (62).

Abstract translation: 公开了一种具有切割后缘（62）和在切割后缘（62）上游的多个扩散分流器（68）的涡轮机翼型件（32）。 开发了各种构造细节，其提供冷却流体的扩散膜在切割后缘（62）上的喷射。 在一个特定实施例中，涡轮机翼片（32）包括在压力壁（56）和吸力壁（58）之间延伸的多个径向隔开的分流器（68）。 每个分流器（68）包括圆形前缘（74），在前缘（74）下游的一对平行侧壁（82）和平行侧壁（82）下游的一对会聚侧壁（86）。 相邻分流器的相邻侧壁形成具有恒定区域通道（76）和扩散部分的流动通道（72）。 扩散部分包括在切割后缘（62）上游的覆盖部分（94）和在切割后缘（62）上延伸的未覆盖部分（96）。

公开(公告)号：WO1994012769A1

公开(公告)日：1994-06-09

申请号：PCT/US1993011023

申请日：1993-11-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： UNITED TECHNOLOGIES CORPORATION ,  LINASK, Indrik

IPC: F01D05/18

CPC classification number: F01D5/187 ,  F05D2240/10 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: A turbine airfoil (44) having a baffleless cooling passage (66) for directing cooling fluid toward a trailing edge (72) is disclosed. Various construction details are developed which provide axially oriented, interrupted channels (104) for turning a flow of cooling fluid from a radial direction to an axial direction. In a particular embodiment, a turbine airfoil (44) has a cooling passage (66) including a plurality of radially spaced walls (76), a plurality of radially spaced dividers (82) downstream of the walls (76), and a plurality of radially spaced pedestals (78) positioned axially between the walls (76) and dividers (82). The walls (76) and dividers (82) define channels (104) having an axial interruption permitting cross flow between adjacent channels (104). The cross flow minimizes the adverse affects of a blockage within a subchannel (92) between adjacent walls (76). The pedestals (78) are aligned with the subchannels (92) such that cooling fluid exiting a subchannel (92) impinges upon the pedestal (78).

Abstract translation: 公开了一种具有用于将冷却流体引向后缘（72）的无挡板冷却通道（66）的涡轮机翼（44）。 开发了各种构造细节，其提供轴向定向的中断通道（104），用于将冷却流体的流动从径向方向转向轴向。 在特定实施例中，涡轮机翼片（44）具有包括多个径向隔开的壁（76），在壁（76）下游的多个径向间隔开的分隔件（82））的冷却通道（66） 径向间隔开的基座（78）轴向定位在壁（76）和分隔件（82）之间。 壁（76）和分隔器（82）限定通道（104），其具有允许在相邻通道（104）之间交叉流动的轴向中断。 交叉流使相邻壁（76）之间的子通道（92）内的阻塞的不利影响最小化。 基座（78）与子通道（92）对准，使得离开子通道（92）的冷却流体撞击基座（78）。

公开(公告)号：EP0774046B1

公开(公告)日：1999-04-14

申请号：EP94901484.9

申请日：1993-11-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： LINASK, Indrik

IPC: F01D5/18

CPC classification number: F01D5/187 ,  F05D2240/10 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: A turbine airfoil (44) having a baffleless cooling passage (66) for directing cooling fluid toward a trailing edge (72) is disclosed. Various construction details are developed which provide axially oriented, interrupted channels (104) for turning a flow of cooling fluid from a radial direction to an axial direction. In a particular embodiment, a turbine airfoil (44) has a cooling passage (66) including a plurality of radially spaced walls (76), a plurality of radially spaced dividers (82) downstream of the walls (76), and a plurality of radially spaced pedestals (78) positioned axially between the walls (76) and dividers (82). The walls (76) and dividers (82) define channels (104) having an axial interruption permitting cross flow between adjacent channels (104). The cross flow minimizes the adverse affects of a blockage within a subchannel (92) between adjacent walls (76). The pedestals (78) are aligned with the subchannels (92) such that cooling fluid exiting a subchannel (92) impinges upon the pedestal (78).

公开(公告)号：EP0774046A1

公开(公告)日：1997-05-21

申请号：EP94901484.0

申请日：1993-11-12

Applicant: UNITED TECHNOLOGIES CORPORATION

Inventor： LINASK, Indrik

IPC: F01D5

CPC classification number: F01D5/187 ,  F05D2240/10 ,  F05D2260/201 ,  F05D2260/202 ,  F05D2260/2212 ,  F05D2260/22141

Abstract: A turbine airfoil (44) having a baffleless cooling passage (66) for directing cooling fluid toward a trailing edge (72) is disclosed. Various construction details are developed which provide axially oriented, interrupted channels (104) for turning a flow of cooling fluid from a radial direction to an axial direction. In a particular embodiment, a turbine airfoil (44) has a cooling passage (66) including a plurality of radially spaced walls (76), a plurality of radially spaced dividers (82) downstream of the walls (76), and a plurality of radially spaced pedestals (78) positioned axially between the walls (76) and dividers (82). The walls (76) and dividers (82) define channels (104) having an axial interruption permitting cross flow between adjacent channels (104). The cross flow minimizes the adverse affects of a blockage within a subchannel (92) between adjacent walls (76). The pedestals (78) are aligned with the subchannels (92) such that cooling fluid exiting a subchannel (92) impinges upon the pedestal (78).