| 发明名称 |
BLADE DISK ARRANGEMENT FOR BLADE FREQUENCY TUNING |
| 摘要 |
A gas turbine engine and a method of tuning a rotor in the gas turbine engine wherein the rotor includes an array of blades extending from a rotor hub each having an airfoil mounted to a blade platform. The method includes adding or removing material from bladed rotor projections to alter the mass of the rotor and change the frequency of the respective airfoil. |
| 申请公布号 |
US2017097016(A1) |
申请公布日期 |
2017.04.06 |
| 申请号 |
US201615202934 |
申请日期 |
2016.07.06 |
| 申请人 |
Pratt & Whitney Canada Corp. |
发明人 |
KULATHU RAM;ABATE ALDO |
| 分类号 |
F04D29/66;F04D29/38;F04D29/32;F01D5/26;F01D5/10 |
主分类号 |
F04D29/66 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A bladed rotor for a gas turbine engine, comprising: a hub and a circumferential array of blades extending from the hub, each blade having an airfoil extending from a gaspath side of a blade platform provided at a periphery of the hub; and an annular array of projections depending from an interior side of the platform at circumferential locations corresponding to every second blade, the projections cooperating to form a circumferentially interrupted rib, a weight of each projection being adjustable to modify a natural frequency of a corresponding blade. |
| 地址 |
Longueuil CA |
