抄録
Static pressure measurements on the hub surface behind of a nozzle blade ring with rotating disc in a modeled air turbine stage were conducted with the objective of obtaining the effect of rotational speed on the pressure distribution characteristic. On the rotating disc, small cylindrical pins were mounted for simulating the leading-edge of rotor blades and the disc was driven by a VS motor. The effect of rotational speed was examined for several constant mainstream flow rates under a constant axial clearance without secondary flow injection. The hub static pressure distribution with disc rotations is presented for the blade pitch space and the axial space under comparison with without rotation.
