| 发明名称 |
COOLING ARRANGEMENT FOR GAS TURBINE BLADE PLATFORM |
| 摘要 |
A gas turbine engine blade (10), having: an airfoil (12) having a pressure side (22) and a suction side (24); an inner platform (30), having: a gas path surface (40); a coolant surface (42); and at least one row (114) of film cooling holes (112) spanning there between and disposed on the pressure side of the airfoil. The film cooling holes are angled to include a directional component substantially parallel with the pressure side at a trailing end of the airfoil, and the at least one row is oriented substantially parallel to a mateface wall (122) of the inner platform. An array (130) of turbulators (132) is disposed on the coolant surface. |
| 申请公布号 |
US2016102562(A1) |
申请公布日期 |
2016.04.14 |
| 申请号 |
US201414890925 |
申请日期 |
2014.05.20 |
| 申请人 |
SIEMENS ENERGY, INC. |
发明人 |
Evans Charles M.;Narcus Andrew R.;McClelland Robert J.;Moehrle Frank |
| 分类号 |
F01D5/18 |
主分类号 |
F01D5/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine blade, comprising:
an airfoil comprising a pressure side and a suction side; an inner platform, comprising: a gas path surface; a coolant surface; and at least one row of film cooling holes spanning there between and disposed on the pressure side of the airfoil, the film cooling holes angled to comprise a directional component parallel with the pressure side at a trailing end of the airfoil, and the at least one row is oriented parallel to a mateface wall of the inner platform; and an array of turbulators disposed on the coolant surface. |
| 地址 |
Orlando FL US |
