Within the scope of European Commission FP7 project FACTOR, dedicated to combustor-turbine-interaction research, a clean-sheet design of a rotating turbine test rig featuring a non-reacting combustor simulator was created and built among the partners. German Aerospace Center DLR provided the operational facility NG-Turb to which the rig was adapted and was responsible for global rig integration and operation, also including aerodynamic probe measurements of the flow field. The rig and experimental set-up is described and post-processed results from probe traverses in several measurement planes are presented and discussed. Special attention is paid to the comparison and influence of two combustor-NGV clocking positions on the periodic turbine flow field, made possible by rig adaptation during the campaign. The strongly distorted and nonuniform turbine inlet flow created by the combustor simulator proved challenging for the probe measurements, but at the same time set a realistic boundary condition enabling the analysis of ‘CTI’ by flow structures migrating through the blade rows.
The calibration data of a five-hole probe and a six-hole probe designed for measurements in transonic turbomachinery flows are presented. The probes feature a special base pressure hole on the back side to avoid the Mach number insensitivity of pressure probes near Mach number unity. There is only little literature available on the performance of such probes, especially in flows with large radial flow angles. To close this gap, the probes are calibrated for radial flow angles up to 32$$^\circ$$ ∘ . A significant influence of this flow angle on the coefficients used for Mach number determination is shown. At large positive flow angles, the relationship between the pressure coefficient using the base pressure and the Mach number is not biunique for the six-hole probe. Therefore, an experimental study of Mach number measurement deviations is performed at the calibration wind tunnel. Different evaluation methods are examined. The sample standard deviation over 210 randomly distributed points is reduced by 66% compared to the same probe design without the base pressure hole. This is achieved using two calibration coefficients for the Mach number simultaneously in a multidimensional interpolation.
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