The NASA Rotor 67 fan bladed disk is a subsystem of a turbofan’s compressor set used in aerospace engine applications.
The following sector model, representing a challenging industrial example for which the detailed geometry and flow information is available in the public domain, consists of a disk and a fan blade with a sector angle of 16.364 degrees.
The sector model represents the running condition or hot geometry of the blade. It is already optimized at the running condition under loading. The primary objective of this example problem is to obtain the cold geometry for manufacturing from the given hot geometry using inverse solving.
To verify the results of the inverse solving analysis, a loop test is performed. The cold geometry calculated by inverse solving is used as the input geometry in a standard forward-solving analysis, and the resulting hot geometry at the running condition under loading is compared to the sector model hot geometry to ensure that they are nearly identical.
To highlight the inverse-solving technology, this example problem does not include a cyclic symmetry analysis.