Open Testcases (IST)

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The Institute for Jet Propulsion and Turbomachinery provides the following testcases:

If you are interested in using the data, please download the corresponding license agreement. Please return the signed license agreement to afterwards. We will then provide you with a download of the data.

 

Testcase RadiVer

Centrifugal Compressor Stage RadiVer Copyright: © RWTH Aachen | IST

The data of this test case were evaluated by Dr.-Ing. Kai U. Ziegler within the scope of his doctorate under the supervision of Prof. Dr.-Ing. H. E. Gallus and Prof. Dr.-Ing. R. Niehuis at the Institute of Jet Propulsion and Turbomachinery at RWTH Aachen University. The highly loaded experimental centrifugalcompressor "RadiVer" consists of a semi-open impeller with 15 backward curved solid blades. The diffuser can be either a vaneless or a variable vane diffuser. The latter has 23 wedges which are adjusted with two degrees of freedom. On the one hand, the radial gap ratio between impeller trailing- and diffuser leading edge can be adjusted between 4% and 18% and on the other hand the stagger angle can be varied. Extensive steady/unsteady measurement data are available for the above mentioned configurations.

License Agreement

If you are interested in using the test case, you can download the corresponding license agreement here. Please submit the signed agreement to afterwards. We will contact you and provide the data for download.

 

Relevant References

  1. Ziegler, K. U., Gallus, H. E., Niehuis, R. "A Study on Impeller-Diffuser Interaction—Part I: Influence on the Performance." ASME Journal of Turbomachinery 125, no. 1, pp. 173-182, 2003.
  2. Ziegler, K. U., Gallus, H. E., Niehuis, R. "A Study on Impeller-Diffuser Interaction—Part II: Detailed Flow Analysis." ASME Journal of Turbomachinery 125, no. 1, pp. 183-192, 2003.
 
 

Testcase RadiVer 2

Centrifugal Compressor Stage RadiVer Copyright: © RWTH Aachen | IST

The data of this testcase was generated by Dr.-Ing. Stefan Ubben during his Ph.D. project under the scientific supervision of Univ.-Prof. Dr.-Ing. R. Niehuis (09/1998 – 02/2006) at the Institute of Jet Propulsion and Turbomachinery (IST) of RWTH Aachen University, Germany.

The highly loaded centrifugal compressor stage “RadiVer” was used to carry out detailed measurements of the pressure distribution at diffuser exit and also Particle Image Velocimetry (PIV) measurements inside the diffuser channel. The experimental results are published as an open testcase “RadiVer 2”, extending the database provided in the testcase “RadiVer” from 2003.

License Agreement

If you are interested in using the test case, you can download the corresponding license agreement here. Please submit the signed agreement to afterwards. We will contact you and provide the data for download.

 

Relevant References

  1. Ubben, S., Niehuis, R. "Investigation of the Diffuser Clearance Effect in an Industrial-Like Centrifugal Compressor." ISABE-2005-1223, 2005
  2. Ubben, S. „Experimentelle Untersuchung des Diffusorspalteinflusses in einem Radialverdichter mit variabler Leitradgeometrie.” Doctoral Thesis RWTH Aachen (in German), 2013
  3. Ubben, S., Niehuis, R. "Experimental Investigation of the Diffuser Vane Clearance Effect in a Centrifugal Compressor Stage with Adjustable Diffuser Geometry: Part I – Compressor Performance Analysis." ASME Paper GT2014-26896, 2014
  4. S. Ubben, R. Niehuis. "Experimental Investigation of the Diffuser Vane Clearance Effect in a Centrifugal Compressor Stage with Adjustable Diffuser Geometry: Part II – Detailed Flow Analysis." ASME Paper GT2014-27175, 2014
 
 

Testcase Aachen Turbine

Aachen Turbine Copyright: © RWTH Aachen | IST

The ERCOFTAC test case of the single-stage axial turbine stage was developed in 1995 by the Institute for Jet Propulsion and Turbomachinery under the direction of Prof. Dr.-Ing. H.E. Gallus published. It contains the exact geometry of the turbine stage, experimental measurement data and stationary and transient comparative calculations. The measurement data include radial distributions at the inlet and outlet of the two blade rows as well as profile pressure distributions.

License Agreement

If you are interested in using the test case, you can download the corresponding license agreement here. Please submit the signed agreement to afterwards. We will contact you and provide the data for download.

 

Relevant References

  1. Volmar, T., Brouillet, B., Benetschik, H., Gallus, H.E. "Test Case 6: 1-1/2 Stage Axial Flow Turbine - Unsteady Computation", in: ERCOFTAC Turbomachinery Seminar and Workshop. (1998)
  2. Walraevens, R., Gallus, H.E. "Testcase 6: 1-1/2 Stage Axial Flow Turbine". (1997)
  3. Gallus, H.E. "ERCOFTAC Test Case 6 Axial Flow Turbine Stage", in: Seminar and Workshop on 3D Turbomachinery flow prediction III, Les Arcs, France. (1995)