| 发明名称 |
TURBINE UNDER PLATFORM AIR SEAL STRIP |
| 摘要 |
A gas turbine engine stage includes a rotor having a slot. A blade has a root received in the slot, and a shank that extends radially outward from the root to a platform that supports an airfoil. A seal is supported on the shank and in engagement circumferentially between and with the shank and the rotor within the slot. A gas turbine engine includes compressor and turbine sections. The turbine section has a rotor with a slot. A combustor is provided axially between the compressor and turbine sections. A turbine blade in the turbine section includes a root received in the slot and a shank that extends radially outward from the root to a platform that supports an airfoil. |
| 申请公布号 |
US2014165591(A1) |
申请公布日期 |
2014.06.19 |
| 申请号 |
US201213717913 |
申请日期 |
2012.12.18 |
| 申请人 |
UNITED TECHNOLOGIES CORPORATION |
发明人 |
Thomen Seth J.;Chlus Wieslaw A. |
| 分类号 |
F01D5/30 |
主分类号 |
F01D5/30 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine stage comprising:
a rotor having a slot; a blade having a root received in the slot, and a shank that extends radially outward from the root to a platform that supports an airfoil; and a seal supported on the shank and in engagement circumferentially between and with the shank and the rotor within the slot.
|
| 地址 |
Hartford CT US |
