For investigations on turbomachinery components, the Institute of Jet Propulsion operates the component test facility, which currently consists of three test rigs. The heart of the facility is the high-speed cascade wind tunnel (HGK), which was taken over from DLR Braunschweig in 1985 and has since been a significant part of the research work at the institute. The test stands at the component test facility are regularly modernized and expanded. In this sense, the multi-purpose wind tunnel was added in 2015, the HGK was thoroughly renovated in 2017, and the inlet guide vane test stand was built in 2018. The measurement technology used is also constantly being further developed to ensure that research work is up to date.

High-Speed Cascade Wind Tunnel (HGK)

The high-speed cascade wind tunnel (HGK) is one of the few cascade wind tunnels worldwide enabling an independent variation of the Mach number (influence of compressibility) and the Reynolds number (influence of viscous effects). This is achieved, on the one hand, by an appropriate adjustment of the pressure level of the wind tunnel arranged in a pressure chamber and, on the other hand, by the independent adjustment of the temperature by means of an extensive cooling device. Therefore, measurements under turbomachine-like conditions can be carried out in this experimental facility. Only in this way the transferability of results on blade cascade models to the real conditions in turbomachinery blading is ensured.

The secondary air supply of the component test facility, driven by an additional screw compressor, offers extended investigation possibilities. Air is guided into the pressure chamber of the HGK through a piping system. Connected to hollow blades with blow-out holes, various effects of cooling air injection can be investigated.