Abstract

The results presented in this paper are based on experimental investigations on a generic transonic low pressure turbine profile at high subsonic exit Mach numbers. Here, the flow on the suction side reaches a maximum isentropic Mach number of approximately 1.2 and features a large separation bubble in a transonic flow regime characterized by surface hot-film measurements. The measurements are supplemented by Schlieren images recorded with a high-speed camera at 19.2 kHz. A highly unsteady normal shock wave on the suction side is observable upstream of the trailing edge. It is interacting with laminar separated flow which is rarely documented in literature. The interaction of the normal shock with the boundary layer flow seems to amplifies the ongoing transition process over the separation bubble and the flow reattaches shortly downstream. A statistical analysis of the Schlieren images reveals characteristic low frequencies of the shock wave motions and a pulsation of the separation bubble. Additionally, the statistical information of the time-dependent signal from the surface hot-film sensors demonstrate the instabilities influencing the boundary layer linked to the unsteadiness in the main flow.

Issue Section:
Research Papers
Keywords:
transonic, shock-wave/boundary layer interactions, laminar separation bubble, surface hot-film, transition, boundary layer development, measurement techniques, turbine, measurement advancements
Topics:
Boundary layers, Flow (Dynamics), Mach number, Sensors, Separation (Technology), Shock waves, Turbines, Suction, Cascades (Fluid dynamics), Bubbles, Pressure, Shock (Mechanics), Signals, Turbulence

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