Unsteady Forces and Boundary Layer Behaviour on the Blades of a Low-Speed Axial Compressor
Project leader: | Prof. Dr.-Ing. Konrad Vogeler |
Project Staff: | Dr. -Ing. Ronald Mailach |
Cooperation: | DFG, UniBW München, TU Berlin, Uni Karlsruhe, DLR Köln |
Funding: | DFG |
Time period: | 10/99 - 12/0 |
Description:
Up to now only few experimental investigations on the unsteady blade forces and the unsteady boundary layer behaviour were carried in existing turbomachines.
The blade wakes as well as potential effects are responsible for periodic excitations of blade forces and strongly influence the boundary behaviour on the blades. Starting with the experience from investigations in cascades, miscellaneous measurement techniques are applied in the Low-Speed Axial Compressor to investigate the unsteady flow field as well as the unsteady profile pressure distribution and the boundary layer behaviour on the blades.
- Firstly detailed measurements of the time-averaged flow parameters were carried out. The results are used for the validation of CFD-codes of the partners of the joint project.
- Secondly the profile pressure distribution on the rotor and stator blade surface was investigated using time-resolving piezoresistive miniature pressure sensors. Based on these measurements the unsteady forces of the blades are calculated and discussed.
- Thirdly the unsteady boundary layer behaviour on the blades is analyzed using surface-mounted hot-film sensors. Additional results on the time-averaged boundary layer were obtained using Preston tubes (CPM3-method).
Results:
Fundamental results obtained in this project are discussed in several publications.
Exemplary results:
- Unsteady profile pressure distribution on the 1st stage rotor blades, midspan, design point
Pressure side:
Suction side:
2. Unsteady boundary layer, stator 1, suction side, Mittelschnitt, midspan, design point
Publications from this project:
R. Mailach, L. Müller, K. Vogeler
Rotor-Stator Interactions in a Four-Stage Low-Speed Axial Compressor, Part II: Unsteady Aerodynamic Forces of Rotor and Stator Blades
ASME Turbo Expo GT2004-53099, 49th ASME International Gas Turbine & Aeroengine Technical Congress & Exposition, Vienna, Austria, June 14-17, 2004
R. Mailach, K. Vogeler
Rotor-Stator Interactions in a Four-Stage Low-Speed Axial Compressor, Part I: Unsteady Profile Pressures and the Effect of Clocking
ASME GT2004-53098, 49th ASME International Gas Turbine & Aeroengine Technical Congress & Exposition, Vienna, Austria, June 14-17, 2004
R. Mailach, K. Vogeler
Aerodynamic Blade Row Interactions in an Axial Compressor, Part II: Unsteady Profile Pressure Distribution and Blade Forces
ASME Journal of Turbomachinery, Vol. 126, pp. 45-51, January 2004.
R. Mailach, K. Vogeler
Aerodynamic Blade Row Interactions in an Axial Compressor, Part I: Unsteady Boundary Layer Development
ASME Journal of Turbomachinery, Vol. 126, pp. 35-44, January 2004
R. Mailach, K. Vogeler
Aerodynamic Blade Row Interactions in an Axial Compressor, Part II: Unsteady Profile Pressure Distribution
ASME Turbo Expo GT2003-38765, 48th ASME International Gas Turbine & Aeroengine Technical Congress & Exposition, Atlanta, Georgia, USA, June 16-19, 2003
R. Mailach, K. Vogeler
Aerodynamic Blade Row Interactions in an Axial Compressor, Part I: Unsteady Boundary Layer Development
ASME Turbo Expo GT2003-38765, 48th ASME International Gas Turbine & Aeroengine Technical Congress & Exposition, Atlanta, Georgia, USA, June 16-19, 2003
R. Mailach, L. Müller, K. Vogeler
Experimental Investigation of Unsteady Forces on Rotor and Stator Blades of an Axial Compressor
5th European Conference on Turbomachinery - Fluid Dynamics and Thermodynamics,
Prague, Czech Republic, March 18 - 21, 2003
R. Mailach, K. Vogeler
Wake-Induced Boundary Layer Transition in a Low-Speed Axial Compressor
Journal of Flow, Turbulence and Combustion, Special Issue: Unsteady Flow in Turbomachinery, Vol. 69, Issue 3-4, pp. 271-294, 2002.