| 发明名称 |
GAS TURBINE COMPRESSOR STAGE |
| 摘要 |
The present invention relates to a compressor stage for a gas turbine, in particular, an aircraft engine, having a row of rotating blades (3) and a row of guide vanes (4), which is adjacent downstream, wherein the choke point σ and the aspect ratio ARax, which is defined by the quotient between average channel height (h) and average chord length (lax), satisfy the condition;σ>−1.33×ARax+5.16. |
| 申请公布号 |
US2017074271(A1) |
申请公布日期 |
2017.03.16 |
| 申请号 |
US201615245388 |
申请日期 |
2016.08.24 |
| 申请人 |
MTU Aero Engines AG |
发明人 |
Humhauser Werner;Matzgeller Roland |
| 分类号 |
F04D19/00;F04D29/54;F04D27/00;F04D29/32 |
主分类号 |
F04D19/00 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A compressor stage for a gas turbine aircraft engine, having a row of rotating blades (3) and a row of guide vanes (4), which is adjacent downstream, wherein the choke point σ and the aspect ratio ARax, which is defined by the quotient between average channel height (h) and average chord length lax, satisfy the condition
σ>−1.33·ARax+5.16. |
| 地址 |
Munich DE |
