| 摘要 |
Provided are methods for accurately measuring nozzle 50 flow areas of new or refurbished gas turbine engine vanes 14 . A first vane 114 is suitably fixtured in a laser scanning system 60 comprising a laser spot projector 82 a laser spot sensor 84 , a multi-axis controller 68 and a computer 78 . According to a nozzle flow area measurement method, a convex surface 38 and a concave surface 40 of a first vane 114 are scanned and stored as point clouds 196, 296 with the system. The point clouds 196, 296 are combined into a point cloud 396 and translated to a reference coordinate system 98 . A point cloud 496 representing a nominally sized, second vane 214 is positioned adjacent to one surface of the combined point cloud 396 . An inlet profile 56 is extracted from the intersection of an inlet plane 58 , perpendicular to a combustion gas flow vector 18 direction, and each point cloud 396, 496 . A nozzle 50 flow area is then accurately calculated using integration techniques from the inlet profile 56 . The process is repeated for the second surface of the first vane 114 . In another method, a combined point cloud 396 of a second vane 214 , which is also scanned using the scanning system, replaces the nominal point cloud 496 . The nozzle 50 flow area between the first 114 and second 214 vanes is then measured using the earlier described method steps.
|
