Investigations of the Effect of Annulus Taper on Transonic Turbine Cascade Flow

Abstract

In a test facility for rotating annular cascades with three conical test sections of different taper angles (0, 30, 45 deg), experiments are conducted for two geometrically different turbine cascade configurations, a hub section cascade with high deflection and a tip section cascade with low deflection. The evaluation of time-averaged data derived from conventional probe measurements upstream and downstream of the test wheel in the machine-fixed absolute system is based on the assumption of axisymmetric stream surfaces. The cascade characteristics, i.e., mass flow, deflection, and losses, for a wide range of inlet flow angles and outlet Mach numbers are provided in the blade-fixed relative system with respect to the influence of annulus taper. Some of the results are compared with simple theoretical calculations. To obtain some information about the spatial structure of the flow within the cascade passages, surface pressure distributions on the profiles of the rotating test wheels are measured at three different radial blade sections. For some examples those distributions are compared with numerical results on plane cascades of the same sweep and dihedral angles and the same aspect ratios. The computer code used is based on a three-dimensional time-marching finite-volume method solving the Euler equations. Both experimental and numerical results show a fairly good qualitative agreement in the three-dimensional blade surface pressure distributions. This work will be continued with detailed investigations on the spatial flow structure.

Experimental and Numerical Analysis of Loss Characteristics of Cooled Transonic Nozzle Guide Vanes

“…Most of the experimental studies of NGV loss in the open literature have been conducted in simplified experiments designed to isolate the impact of particular design features, e.g., film cooling configurations [4][5][6][7]; TE coolant ejection [8][9][10][11]; TE design [12][13][14]; fillets at the vane surface-endwall junctions [15][16][17]; 3D shaping [18][19][20][21][22]; and inlet flow conditions at the combustorturbine interface [23][24][25]. Such experiments are well suited to understanding fundamental aspects of design, but poorly suited to characterizing engine parts in a realistic operating environment.…”