Aircraft engine compressor test section


Societal benefits
Explore new ways to maintain the efficiency of turbine compressors throughout their life to reduce aircraft engine fuel consumption.

Develop and manufacture a test section as well as support the test campaign to evaluate the performance of a new compressor turbine blade design for a jet engine. Collaborative industrial-academic project subsidized by the SA2GE program (Advanced Aviation Systems for the Environment) and the GARDN program (Green Aviation Research and Development Network). Includes the development of various probes and specialized tools. This equipment makes it possible to vary the blade clearance of a rotor at a very high rotational speed and to evaluate pressures and temperatures at different points in the flow to map the performance and behaviour of the new compressor design.

Development time
55 months

Technological advancements

  • Labyrinth-type mechanical seal
  • System to accurately vary blade tip clearance thus minimizing downtime
  • High precision mechanical instrumentation
  • Development of pressure and temperature probes

Scientific advancements
Development of a prototype turbine compressor that maintains consistent performance throughout the life of an aircraft engine, thereby saving substantial fuel costs.


  • Dimensions: 45″ x 53″ x 115″H [1.1 x 1.4 x 2.9 m]
  • Test section weight: 800 lbs [365 kg]
  • Compressor rotation speed: 0-22000 RPM
  • Compressor diameter: Approx. 12″ Ø [300 mm]
  • Weight of the rotor and its rotating parts: Approx. 35 lbs [15 kg]
  • Electric power: 200 HP
  • Instrumentation: 75 channels
  • Maximum speed of airflow: 325 ft/s [350 km/h]