Measurements of the three dimensional flow field in annular turbine nozzle guide vanes present an important step in the simulation of the real flow conditions in turbomachinery bladings. This paper seeks to determine whether the installation of a rotor closely behind a high hub-to-tip ratio cascade (DH/DT=0.8) is indispensable for establishing correct flow conditions at the cascade exit or whether the use of an axial diffuser of a certain length is sufficient. Also, an attempt is made to separate the possible effects of the rotor blades from that of the rotating rotor disc.

The tests are carried out on a low speed, low aspect ratio, high turning nozzle guide vane. The flow is explored by means of a double head four-hole pressure probe and the results are presented in the form of contour plots and spanwise pitch-averaged distributions of losses, flow angles and static pressure.

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