| 发明名称 |
METHOD FOR CHECKING COOLING HOLES OF A GAS TURBINE BLADE |
| 摘要 |
A method for checking cooling holes of a gas turbine blade, including in sequence: step 1: injecting a liquid plastic material into a cooling hole of a gas turbine blade; step 2: stopping the flow of the liquid plastic material, and curing the liquid plastic material to form a model; step 3: separating the model from the gas turbine blade; step 4: scanning the model. By scanning the model, the cooling holes of the gas turbine blade can be checked, so as to obtain more data about the position, dimensions and shape thereof, while improving the accuracy and efficiency of measurement. |
| 申请公布号 |
US2015000387(A1) |
申请公布日期 |
2015.01.01 |
| 申请号 |
US201314374426 |
申请日期 |
2013.02.25 |
| 申请人 |
SIEMENS AKTIENGESELLSCHAFT |
发明人 |
Jiang Tao;LI Hong Tao;Neuenhahn Thomas |
| 分类号 |
F01D5/14;G01B11/24;G01B11/14;F01D5/18;G01B11/26 |
主分类号 |
F01D5/14 |
| 代理机构 |
|
代理人 |
|
| 主权项 |
1. A method for checking at least one of positions, angles, dimensions, and shapes of cooling holes which pass between an outer surface and an interior cavity of a gas turbine blade, comprising in sequence:
step 1: injecting a liquid plastic material into at least one cooling hole of the gas turbine blade; step 2: stopping the flow of the liquid plastic material, and curing the liquid plastic material to form a model of the at least one cooling hole; step 3: separating the model from the gas turbine blade; step 4: scanning the model to determine at least one of the positions, angles, dimensions, and shapes of the model of the at least one cooling hole. |
| 地址 |
München DE |
