Gas Turbine Facilities – Transonic
Gas Turbine Facilities – Low Speed
Hypersonic Facilities – Low Mach Number
The Transonic Calibration Tunnel facility was commissioned in the period 2010-2015 and now provides fully automated, high accuracy calibrations of probes for turbomachinery applications. The Mach number range is 0 to 1.9, and the tunnel spans a Reynolds number range greater than that normally encountered in turbomachinery applications in industry.
The Supersonic Cascade facility is a new two-dimensional mini-cascade blow-down tunnel, with 8 vane passages of only 15 mm pitch and 40 mm span. It has been developed for testing gas turbine nozzle guide vane profiles at transonic exit Mach numbers and realistic Reynolds numbers with a quick turnaround and high accuracy.
Detailed experimental investigations of the film effectiveness distribution on engine-realistic endwalls geometry can be performed at the Large-Scale Platform Cooling Facility by means of infrared (IR) thermography. The facility is a large-scale, low-speed linear cascade with seven vanes.
The Transonic Rotor Cooling facility at the University of Oxford is a new high-pressure linear cascade designed for low technology-readiness level research of rotor platform cooling. It will be used for aerothermal research into flow interactions between seal leakages across the platform, to develop and assess novel cooling systems, and computational fluid dynamics validation.