The Laval test rig consists of a subsonic wind tunnel powered by a centrifugal compressor, driven by a 470 kW electrical motor. The compressor is taken from an ABB VTC 254 turbocharger. In the current configuration, the wind tunnel has been adapted primarily for film cooling experiments.
The Laval wind tunnel can has a rectangular test section of dimensions 40mm x 181 mm x 400 mm. Typical freestream velocities can go up to 160 m/s or a Mach number of M=0.5, i.e. a mass flow rate of about 1.5 kg/s. A boundary layer based Reynolds number of 700 000 is thus attainable. The freestream flow can be heated to a temperature of 120°C by a steam heat exchanger which can be accurately regulated and controlled. A water-cooled heat exchanger extracts the heat from the freestream downstream of the test section before it returns in a closed loop to the compressor. The boundary layer thickness of the flow is controlled by a suction arrangement. The boundary layer is sucked off through multiple, 1.2 mm diameter, discrete holes of covering an area of 60 mm x 180 mm. The extracted air is fed back into the loop downstream.
In order to study mixing and jet impingement a secondary air supply
also exists to provide air which can be cryogenically cooled down to
–40°C. This cooled air can be injected through different hole
arrangements to study various jet-in-crossflow configurations. The
different temperatures between the injectant and the freestream are
required to mimic the density ratios typically found in jet engines. In
order to study unsteady effects the cool air can also be pulsated via
an in-house designed pulsator, with frequencies up to 500 Hz.
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