The icing wind tunnel (IWT) was established at Cranfield University in 2003. The facility is capable of producing impact ice on models mounted within a range of different test sections.

At present, the Cranfield IWT (figure 1) is the largest in the UK. The IWT can produce realistic icing conditions that are encountered in aviation, which is of interest to researchers in the field of icing science and organisations engaged in the development of ice detection and mitigation systems.

Figure 1: Cranfield icing wind tunnel (IWT) facility.

Understanding ice formation: why is icing an issue for aircraft?

One of the fundamental aspects with icing science is the behavior of ice as a material and the interface with the substrate. It is challenging to predict ice accretion, strength of surface adhesion and the behaviour in response to applied thermo-mechanical loads.

A considerable amount of research, both experimental and computational, has been conducted in the past few decades to understand the secrets behind ice formation. Water droplets in clouds can cool well below freezing point and yet remain liquid. It is often only when the droplets touch a solid object that they freeze. Aircraft, tall buildings, wind turbines and even crops can be greatly affected by the ice which forms on them due to windborne droplets. This type of ice is called impact ice, which is characterised by supercooled water droplets.

On aircraft, the presence of ice on aerodynamic surfaces can lead to loss of lift, affect the controllability of the aircraft and in worst cases lead to a stall. This is a serious hazard and requires mitigation. Ice protection systems (IPS) usually form a necessary part of every certified aircraft. These systems allow the aircraft to become capable of flight into known icing (FIKI).

The Cranfield IWT is capable of reproducing these atmospheric icing conditions encountered in flight. This is of interest to aerospace organisations engaged in icing research such as Airbus, Rolls-Royce, Safran, TEI, Parker-Meggitt and Spirit Aerosystems.

A medium for icing research

Over the years, the Cranfield IWT has undertaken several high complexity research projects. Some of these were major research projects funded by the European Union or Innovate UK. Alternatively, industrial partners also hire the Cranfield IWT facility to perform icing test campaigns through commercial contracts.

The facility consists of a closed loop, horizontal icing tunnel capable of working section flow speeds of 100m/s and a minimum temperature of -30 °C. The maximum liquid water content which can be delivered by the tunnel spray system is 5g/m3. The vertical droplet facility, which forms a part of the IWT, can produce a stream of mono-dispersed droplets, which are used to study droplet impact and freezing dynamics using flow visualisation techniques like high speed shadowgraphy.

The projects undertaken in the facility can range from testing of new ice protection equipment, validating design tools for simulating ice growth, examining the potential role of ice phobic surface coatings and demonstration of novel ice protection concepts.

Case studies: ICE GENESIS (EU Horizon 2020) - engine cascade rig (work package 8)

The aim of this project was to understand and measure ice accretion under various test matrix 
conditions within a cascade rig, which replicated a stage of stator vanes, strut and internal 
guide vanes (IGV) from an aircraft gas turbine engine. A secondary objective of this project
was to assess the performance of a new electrothermal ice protection system for the IGVs. 

The project consisted of the design, construction, integration and calibration of a new test 
configuration, which replaced the standard test section of the IWT. This configuration split the 
incoming air from the convergent section of the tunnel into two flow sections. The flow was 
divided into a bypass section and a core flow section. The ice formation under various icing 
conditions was observed with high-definition video cameras and thermal imaging cameras. 
Each blade within the cascade rig was instrumented to obtain its temperature under icing 
conditions. The characteristics were measured with the ice protection systems activated or 
switched off.

Post test, the shape of the ice accreted on the blades was determined using a 
3D scanning system which was setup in the freezer room adjoining the IWT. This was made 
possible due to a cassette-release system, which allowed the rapid disassembly of the stator 
blade row from the cascade without affecting the ice formed on the blades.

Safran Aero Engines and the Austrian Institute of Icing Science (AIIS) were the major collaborators on this project. Figure 2 shows the ice accreted in the IGV blades (left) and the 3D scanned image of 
ice accreted on a stator vane (right). Figure 3 shows the 3D CAD model of the primary flow 
section of the cascade rig integrated with the IWT. The bypass section is omitted for clarity.

Figure 2: ICE GENESIS cascade rig core flow section and 3D scanned blade.

Figure 3: ICE GENESIS cascade rig integrated with Cranfield IWT (primary flow section only).

At forefront of icing science and engineering

The Cranfield IWT holds a unique place within the atmospheric icing research community due 
to its participation in major research projects on icing and a demonstrated track record of 
performing world-class research on icing topics. The tunnel continues to operate and provide 
a unique and valuable service to the community through research on both fundamental icing 
science as well as more applied aspects such as novel ice protection and detection systems.

Author

Dr Abhay Vincent is a Research Fellow in Impact Ice Adhesion in the Centre for Propulsion and Thermal Power Engineering at Cranfield University.