Effects of the viscous forces, compressibility, incidence flow angle and pitch to chord ratio on the secondary flow within a linear blade cascade is investigated by means of flow visualization. Three different impulse cascade configurations defined by different pitch to chord ratio were used for the presented experiments.

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Paper deals with unsteady pressure measurement in an end-wall region of a linear blade cascade, where a secondary flow behaviour was investigated. Effects of compressibility (M2,is), flow turning (α1) and three different pitch to chord ratios (t/c = 0.55; 0.75 and 1.00) were studied. Reynolds number was set as constant Re2,is = 8.5 × 10 5. Unsteady pressure measurements were also performed in the same S /c position at the blade mid-span to obtain comparable reference data.

Abstract. Topic of this contribution is the detection of the laminarturbulent boundary layer transition on the prismatic blade using infrared thermography. Several Reynolds and Mach numbers were investigated, and their influence on the boundary layer transition was evaluated. Results are in good agreement with experiments that were performed earlier with hot-film anemometry.

The static pressure distribution on the end-wall of a linear blade cascade for different inlet flow angles is investigated in this contribution. The experiments were performed for constant values of Reynolds number (Re2,is = 4.5 × 105) and Mach number (M2,is = 0.4). These data are presented in the form of static pressure gradients. The obtained quantitative results are supported by surface flow visualization.