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Aerodynamics of Tandem Vanes

Tandem Cascade (CAD)
Tandem Cascade (CAD)
Lupe


The project aims to examine the aerodynamics of tandem vanes in a compressor cascade with the particular interest of the 3D wall interaction.

Conventional blade designs achieve higher stage pressure ratios with an increased turning of the flow limited by the increased risk of separation. Therefore, modern compressor design engineering focuses on new blade designs to prevent separation while retaining the higher turning of the flow. Tandem blades are a novel approach to increase the stage pressure ratio by avoiding separation.
For tandem blades, the flow deflection is now realized by two blades positioned directly after one another. As a result the critical blade loading is split onto two blades allowing a higher pressure rise but also a more stabilized flow guidance thus reducing the risk of flow separation. The figures of the tandem blades visualize the reduced boundary layer development due to the shortened chord length and the optimized flow guidance.

The objective of the project is to develop validated computational approaches to support the early design phase of compressor modules with large deflection angles and to get detailed information about the influence of the secondary flow structures on the blade performance.

Total pressure loss distribution captured during wake measurements
Total pressure loss distribution captured during wake measurements
Lupe

The objective of the project is to develop validated computational approaches to support the early design phase of compressor modules with large deflection angles and to get detailed information about the influence of the secondary flow structures on the blade performance.

This is supported by both experimental and numerical investigations. In the course of this project, four different configurations for 35° and 50° deflection angles and two different Lift Split (LS) variations are compared against conventional single CDA blades. In order to get a full understanding of the secondary flow development and in particular the influence of the stagnation point on the sidewall characteristics, both the axial and tangential pitch can be varied as well as the oncoming boundary layer thickness.
With the use of tandem blades, the resulting losses can be reduced or avoided. Therefore the influence of the aerodynamic loading and the boundary layer thickness of the inflow on the blade performance
are investigated. The project is carried out in cooperation with the Research Association for Combustion Engines e.V.

The project is carried out in cooperation with the Research Association for Combustion Engines e.V. (Forschungsvereinigung Verbrennungskraftmaschinen e.V.)

Person of contact: Dipl.-Ing. Alexander Heinrich

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References

Increasing Blade Turning by Active Flow Control and Tandem Configurations: A Comparison

C. Tiedemann, A. Heinrich, D. Peitsch
(TU Berlin)

23rd ISABE Conference, International Symposium on Air Breathing Engines,
Manchester, UK, Sep 3-8 2017, ISABE-2017-22575


Experimental Investigations of the Aerodynamics of Highly Loaded Tandem Vanes in a High-Speed Stator Cascade

A. Heinrich, C. Tiedemann, D. Peitsch
(TU Berlin)

ASME Turbo Expo 2017
Charlotte, USA, June 26-30 2017, GT2017-63235


3D Numerical and Experimental Investigation of High Turning Compressor
Tandem Cascades


J. Eckel, A. Heinrich, C. Janke, J. Ortmanns, D. Peitsch

Deutscher Luft- und Raumfahrtkongress 2016,
Braunschweig, Germany, September 13-15 2016, DLRK 2016-420320


Experimental Investigations of Secondary Flow Development around Tandem Vanes in a 2D Linear Stator Compressor Cascade


A. Heinrich, C. Tiedemann, D. Peitsch
(TU Berlin)

11th European Turbomachinery Conference, ETC 11,
Madrid, Spain, March 23 - 27 2015, ETC2015-237


A new linear high speed compressor stator cascade for tandem configurations

A. Heinrich, C. Tiedemann, D. Peitsch
(TU Berlin)

15th International Symposium on Transport Phenomena and Dynamics of Rotating Machinery, ISROMAC-15
Honolulu, Hawaii, USA, February 24-28 2014, ISROMAC-FR307


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