| 发明名称 |
AIRFOIL WITH STEPPED SPANWISE THICKNESS DISTRIBUTION |
| 摘要 |
An airfoil in a gas turbine engine includes opposed pressure and suction sides joined together at chordally opposite leading and trailing edges. The pressure and suction sides extend spanwise from a root to a tip of the airfoil. The airfoil has a spanwise distribution of maximum thicknesses of chordwise cross-sections of the airfoil. The spanwise distribution of maximum thicknesses decreases from the root to the tip. In one aspect, the spanwise distribution is stepped between a first portion extending from the root and a second portion extending to the tip. |
| 申请公布号 |
US2016146012(A1) |
申请公布日期 |
2016.05.26 |
| 申请号 |
US201414553119 |
申请日期 |
2014.11.25 |
| 申请人 |
PRATT & WHITNEY CANADA CORP. |
发明人 |
WARIKOO Raman;BALIKE Krishna Prasad;LOBO Keegan;DUONG Hien;VEITCH Thomas |
| 分类号 |
F01D5/14;F01D9/04 |
主分类号 |
F01D5/14 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. An airfoil in a gas turbine engine, the airfoil comprising:
opposed pressure and suction sides joined together at chordally opposite leading and trailing edges, the pressure and suction sides extending spanwise from a root to a tip of the airfoil, the airfoil having a spanwise distribution of maximum thicknesses of chordwise cross-sections of the airfoil, the spanwise distribution of the maximum thicknesses decreasing from the root to the tip, the spanwise distribution being stepped between a first portion extending from the root and a second portion extending to the tip. |
| 地址 |
Longueuil CA |
