ResearchOur ServicesTest Rigs
High-Speed Axial Compressor

High-Speed Axial Compressor

The high-speed axial compressor facility at the Institute of Turbomachinery and Fluid Dynamics (TFD) is characterized by its realistic transonic flow conditions. Due to the availability of various rotor versions including rotors with 4-stage controlled diffusion airfoils (CDA) or 4.5-stage tandem blading as well as 3- and 6-stage configurations, the high-speed axial compressor facility is ideally suited for investigating multi-stage flow effects. As the volume enclosed between the exit of the last stator row and the adjustable throttle ring at the diffuser exit is small, these effects can be studied over the complete working range of a given compressor design. The reduced dimensions of the pressurized exit components allow the compressor to be operated under unstable flow conditions without risking blade damage.

Field of Application

Investigation of active and passive flow-control methods under realistic flow conditions in order to reduce secondary flow losses and to enlarge the compressor working range

Description

Applicable measurement techniques a the high-speed axial-compressor facility are comprised of a variety of conventional probes extending from steady- and unsteady-state multi-hole probes to CTA probes. Multiple measuring positions are available for these probes upstream and downstream of each blade row. Additionally, the compressor-testing environment can be equipped with a L2F system for optical flow measurements downstream of the third-stage stator.

Experimental results of the axial compressor flow are supplemented with results of computational fluid dynamics (CFD) simulations. This procedure results in an experimental validation of numerical simulation results and facilitates the numerical investigation of flow phenomena which are too complex to be obtained experimentally.

In recent years, major investigations related to the reduction of secondary flow losses using three-dimensional blade shapes with bow and sweep, as well as endwall contouring have been performed a high-speed axial compressor facility at TFD. Additionally, the phenomenon of acoustic resonance in axial compressors has been observed and proven experimentally by Hellmich in 2008. Currently, research projects which are focusing on methods for active flow control are being carried out with the four-stage configuration. The control methods considered include the injection of high-momentum fluid as well as the suction of low-momentum fluid. Simultaneously, the secondary flow losses of the 4.5-stage tandem configuration are being investigated experimentally.

Picture - Components of the high-speed axial-compressor facility Picture - Components of the high-speed axial-compressor facility Picture - Components of the high-speed axial-compressor facility
Components of the high-speed axial-compressor facility
Picture - Four-stage rotor configuration of the high-speed axial-compressor facility Picture - Four-stage rotor configuration of the high-speed axial-compressor facility Picture - Four-stage rotor configuration of the high-speed axial-compressor facility
Four-stage rotor configuration of the high-speed axial-compressor facility
Picture - Numerically predicted corner separation near the hub of the second stage stator Picture - Numerically predicted corner separation near the hub of the second stage stator Picture - Numerically predicted corner separation near the hub of the second stage stator
Numerically predicted corner separation near the hub of the second stage stator

Measurement Techniques

  • Steady and unsteady pressure sensors
  • Temperature sensors (type K and Pt100)
  • Combined radial and peripheral traversing downstream of each stator row using steady and unsteady multi-hole flow-vector probes
  • Radial traversing downstream of each rotor row using steady and unsteady multi-hole flow-vector probes
  • Determination of velocity vectors and turbulent characteristics of the flow field by using constant temperature anemometry (CTA) and constant current anemometry (CCA)
  • Application of Laser-2-focus (L2F) system between rotor and stator of the third compressor stage
  • Optional tip-timing system
  • Vibration control using acceleration sensors
  • Torque measurement using a torque shaft

Specifications (Four-Stage Configuration)

Number of stages 4
Rotational speed 18.000 1/min
Mass-flow rate 8.11 kg/s at 60 kPa total inlet pressure
Pressure ratio (total-to-total)2,87
Power input max. 950 kW
Inlet pressure (variable)  
approx. 55 - 95 kPa

Contact

Mona Amer, M.Sc.
Group Leader
Aeroacoustics / Aeroelasticity and Wind Energy
Address
An der Universität 1
30823 Garbsen
Building
Room
202
Address
An der Universität 1
30823 Garbsen
Building
Room
202