| 发明名称 |
ROTATING TURBINE COMPONENT WITH PREFERENTIAL HOLE ALIGNMENT |
| 摘要 |
A turbine airfoil includes: a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the rib, the crossover hole having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape; wherein the major axis of the crossover hole lies in plane with the rib and is non-parallel to an imaginary curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls. The orientation of the crossover holes minimizes stress concentration caused by the presence of the crossover holes. |
| 申请公布号 |
US2015226069(A1) |
申请公布日期 |
2015.08.13 |
| 申请号 |
US201314418626 |
申请日期 |
2013.07.30 |
| 申请人 |
General Electric Company |
发明人 |
Pearson Shawn Michael;Brassfield Steven Robert;Molter Stephen Mark;Stegemiller Mark Edward;Ertel Nicholas;Camarillo Vanessa |
| 分类号 |
F01D5/18;B23P15/04 |
主分类号 |
F01D5/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A turbine airfoil, comprising:
a concave pressure sidewall and a convex suction sidewall joined together at a leading edge and a trailing edge, and extending between a root and a tip; an internal rib extending between the pressure sidewall and the suction sidewall; and a crossover hole formed in the rib, the crossover hole having a noncircular cross-sectional shape with a major axis defining a maximum dimension of the cross-sectional shape; wherein the major axis of the crossover hole lies in plane with the rib and is non-parallel to an imaginary curvilinear lateral centerline which defines a locus of points lying halfway between the pressure and suction sidewalls. |
| 地址 |
Schenectady NY US |
