Prior the jet engines application in flight operation they have to be constructed and developed during a complex sequence of processes. This starts out with the fundamental research as well as experimental cascade investigations.

According to the future requirements, the blade profiles are positioned in a linear cascade with the aim to investigate several geometric and fluid mechanical variations. Here the blade effects can be specifically isolated because of the omission of rotation and symmetry.

With the advantages of good access for most measurement techniques, low costs and fast measuring sequences the cascade tests are proofed tools to verify previous development work for further applications.

Current research projects:

• Design of radial gap and endwall contouring of variable guide vanes in axial compressors 02/08 - 01/11, extension 02/11 - 01/13

Completed research projects:

  
Influencing secondary flows in compressor cascades using a modification of the leading edge near the endwall:

• Reduction of the Secondary Losses In Compressor Cascades – Numerical Simulation ´04
  
• Endwall Boundary Layer Control in Compressor ´04
  
• Influencing the Secondary losses in compressor cascades by a leading edge bulb modification at the endwal ´03
• Influencing the Secondary Losses in Compressor Cascades by a Leading Edge Bulb Modification at the Endwall ´02 
• Secondary Flows in a Compressor Cascade with Fillet Radius ´01