| 发明名称 |
TUNED ROTOR DISK |
| 摘要 |
A gas turbine engine includes a rotor that has a rotor disk and a plurality of circumferentially-spaced blades. The rotor disk and the blades are co-rotatable about an axis. A case circumscribes the rotor. The rotor disk is tuned, with regard to centrifugal and thermal growth responsiveness, to the case for a given operational scenario of the gas turbine engine such that the rotor disk and case together provide a tuned clearance response. The operational scenario involves a series of engine events that include at least two of engine acceleration, engine deceleration, engine steady-state operation. |
| 申请公布号 |
US2016153305(A1) |
申请公布日期 |
2016.06.02 |
| 申请号 |
US201514810847 |
申请日期 |
2015.07.28 |
| 申请人 |
United Technologies Corporation |
发明人 |
Schwarz Frederick M.;Shah Dilip M. |
| 分类号 |
F01D11/18;F01D5/02;F04D29/52;F04D29/16;F04D29/32;F01D5/28;F04D29/02 |
主分类号 |
F01D11/18 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A gas turbine engine comprising:
a rotor including a rotor disk and a plurality of circumferentially-spaced blades, the rotor disk and the blades being co-rotatable about an axis; and a case circumscribing the rotor, the rotor disk being tuned, with regard to centrifugal and thermal growth responsiveness, to the case for a given operational scenario of the gas turbine engine such that the rotor disk and case together provide a tuned clearance response, the operational scenario involving a series of engine events including at least two of: engine acceleration, engine deceleration, and engine steady-state operation. |
| 地址 |
Hartford CT US |
