发明名称 |
ADDITIVE MANUFACTURING PROCESS GROWN INTEGRATED TORSIONAL DAMPER MECHANISM IN GAS TURBINE ENGINE BLADE |
摘要 |
A blade is provided for a gas turbine engine. The blade includes an airfoil portion with at least one internal cavity and a damper located within the internal cavity. The damper includes a cantilever spring arm. A fan blade is provided for a gas turbine engine. The fan blade includes an airfoil portion with at least one internal cavity; and a damper located within the internal cavity. The damper includes a cantilever spring arm that terminates with a rub surface pad adjacent to a friction bridge between a concave pressure side and a convex suction side of the airfoil portion. A method is also provided for damping a blade of a gas turbine engine. The method includes deflecting a cantilever spring arm to contact a rub surface pad with a friction bridge between a concave pressure side and a convex suction side of an airfoil portion of the blade. |
申请公布号 |
US2016341221(A1) |
申请公布日期 |
2016.11.24 |
申请号 |
US201515112032 |
申请日期 |
2015.01.23 |
申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Twelves, Jr. Wendell V.;Propheter-Hinckley Tracy A.;Cabrila Pauline |
分类号 |
F04D29/66;F04D29/38;F04D29/32 |
主分类号 |
F04D29/66 |
代理机构 |
|
代理人 |
|
主权项 |
1. A blade for a gas turbine engine, comprising:
an airfoil portion with at least one internal cavity; and a damper located within the internal cavity, the damper including a cantilever spring arm. |
地址 |
Hartford CT US |