|External Collaborators / Partners||Cambridge University, UK, Rolls-Royce Plc|
|Commencement Date||01 July 2008|
Gas turbine engines are widely used for aircraft propulsion and power generation. In many cases, axial compressors are used to compress air prior to combustion. The aim of this research project is to improve axial compressor design through better understanding of fundamental flow physics and their effect on blade profile loss. This is achieved through experimental testing and numerical modelling.
The performance of axial compressors and gas turbine engines is fast approaching an asymptote in aero-thermal performance and it is believed that by gaining a deeper understanding of boundary layer transition processes and free-stream turbulence, turbulence model designers will be able to develop new innovative codes and optimisation routines to design machines with greater efficiency, lower weight and improved emissions.
In this project, a large scale two-dimensional linear compressor cascade at the Whittle Laboratory, University of Cambridge, was used to investigate detailed flow phenomena over the leading edge region of a controlled diffusion axial compressor stator blade. A number of experimental techniques were used to investigate the instantaneous, time averaged and time resolved flow, such as ultra-high resolution static pressure tappings, surface mounted hot-films, single element hot-wire probes, 3 hole cobra type probes and particle image velocimetry (PIV).
Supervisors (External)Dr Alan Henderson (School of Engineering)
Members (External)Mr Samuel Perkins (PhD Student)
Authorised by the Head of School, Engineering
1 May, 2012