List of facilities

  1. Oxford Turbine Research FacilityOxford Turbine Research Facility (OTRF). This major test facility was designed and built by the Department of Engineering Science for the MOD (DERA) then operated on the Pyestock and Farnborough sites for about twenty years. It is now owned by the University and is housed in the Southwell Building. It comprises one and a half stages of axial turbine. The piston tunnel achieves engine representative Reynolds number and Mach number during a flow pulse of about 0.5seconds. The rotor spins at 9500rpm and thin film gauge instrumentation enables heat transfer on the blades, vanes and endwalls to be measured. On shaft torque measurements and high resolution total pressure, velocity and temperature surveys are used to measure stage efficiency. The vanes and blades can be cooled by air or foreign gas (to achieve engine density ratio). The OTRF now includes a temperature distortion representative of rich burn OTRF and RDF. It has research programmes through to 2016.
  2. NGV capacity rigThe NGV capacity rig is an engine parts scale facility used to measure the capacity of Trent family HP NGVs. The tunnel is used to support research as well as Engine Development Programmes. The tunnel provides information at high TRL. The mass-flow measurement is traceable to national standard. The vanes are cooled and extensively instrumented with pressure tappings.
  3. Sector rigThe Sector rig achieves metal effectiveness measurements on engine parts at reduced temp but the correct Re and Mach numbers. It has been used to study Trent family cooling systems and advanced engineering technology such as dendritic cooling. The tunnel uses foreign gas to achieve correct coolant to mainstream density ratio.
  4. High Speed Linear CascadeHigh speed Linear Cascade. This is a blow down facility for tip clearance loss measurements. The cascade is fitted with comprehensive instrumentation and can measure both pressure loss and blade tip heat transfer.
  5. Low speed heat transfer rigLow speed heat transfer rigs. There several low speed wind tunnels that are used for heat transfer measurements. They use mesh heater technology to achieve a step change in temperature to perform transient heat transfer experiments. IR camera or liquid crystals are used for adiabatic wall or htc measurements.
  6. Probe calibration facilityThe lab has a number of Probe calibration facilities. These include a new high Re free jet rig and the recirculating low 9 by 3 supersonic tunnel from NPL for transonic flows.
  7. Seals rigs. These include the High speed blowdown; the stiffness rig and the high speed tribology rig. These facilities can achieve conditions representative of engine seals but at reduced pressure and temperature.
  8. Oxford Tip Clearance FacilityThe Oxford Tip Clearance Facility (OTFC) has an engine radius rotor which spins at 9000rpm in vacuum. It is used for the development of tip speed and tip clearance sensors. The Blades are attached to a disk with engine radius.
  9. Turbine combustor interaction rig. This new rig uses 200mm span Rohacell vanes. Combustor dilution jets and RIDN and RODN flows are represented at large scale. Measurements include adiabatic wall temperature and coolant dilution.
  10. Gun TunnelThe Gun Tunnel can be operated in two modes. In GT mode, a double diaphragm burst mechanism propels a piston supersonically down the barrel to shock heat the test gas to about 1000K stag temp which gives a test time of 25-30ms and 90K static temp at about Mach 7. In GT LICH mode a valve and choked orifice propels the piston subsonically to isentropically compress the test gas. This gives steady “cold” test times of around 300ms and about 600k total temp, 60K static temp at Mach 7. The tunnel can be used for altitude simulation of around 20-40km and speeds from typically 0.5- 1.0 km/s. The tunnel can also be fitted with a contoured Mach 8 nozzle, and includes the option of injection of foreign test gases into test section models (such as scramjet models) using a separate Ludwieg tube rated to 140 Bar.
  11. LDWTThe LDWT is an closed-circuit wind tunnel, originally designed to create continuous hypersonic flow at low pressure (~10-1 -100 mbar). The concept is straightforward: There is a test chamber which is 1.5 m in diameter by ~1.5 m wide. Air (or other gas being used) is introduced from one side of the test chamber through a carefully designed nozzle. At the other side of the test chamber lies a powerful oil diffusion vacuum pumping system.
  12. Two Transient Single Blow (TSB) facilities use mesh technology and rhoacell test sections to measure bulk heat transfer coefficients of compact heat exchangers of differing sizes.
  13. The acoustic liner heat transfer facility is a purpose built wind tunnel to replicate the intake Re numbers of typical jet engine intakes. Using PID controlled heaters, the tunnel can run steady experiments to measure the thermal conductivity of varying geometry acoustic liners at engine representative pressure gradients.