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GPPS Data Sets

In the public domain, there are very few turbomachinery geometries and accompanying validation data. Following its mission to increase research collaboration worldwide, GPPS makes experimental data readily available to all researchers. GPPS technical conferences feature special sessions dedicated to presenting the geometries and data sets, their release plan to researchers, and enabling discussion and access to any upcoming test cases.
 
Registered attendees of the GPPS Chania20 virtual technical conference were first to receive the geometries and data sets from ETH Zurich, Seoul National University, and TU Darmstadt. In the meantime, Beihang University confirmed two additional data sets that will be made available after the GPPS Xi'an21 technical conference. The registered attendees of our upcoming technical meeting, GPPS Xi'an21, in China on October 18-20, 2021, will receive all data sets if requested after the event. The data will become public domain as described in the release schedule.

The data is intended to be used by the registered attendees (individual, not company use) and must not be further distributed to a third party without the data providers' written permission. The data will remain the property of the data providers. Until the data is released publically, the data, including any analysis of the data, can only be included in a publication where the named registrant, who received the data, is an author.

ETH Zurich: D-Turbine - 1.5 stage high work axial turbine

Reza Abhari
•    The full three-dimensional blade row geometry of the turbine (nozzle guide vane, rotor, and 2nd stator) will be made available

•    Available data measurements are at inlet to NGV, inlet to rotor, exit of rotor, exit of second stator
   - 2-sensor FRAP unsteady data with a typical resolution of 1500 to 2000 measurements points per passage (time-averaged as well as phase-locked averaged)
   - 4-sensor FRAP unsteady data with a typical resolution of 1500 to 2000 measurements points per passage (time-averaged, phase-locked averaged as well as full unsteady) with various probe diameter sizes (3, 4, 5 mm)
   - FENT unsteady entropy data with a typical resolution of 1500 to 2000 measurements points per passage (time-averaged as well as phase-locked averaged)
   - Typically, at two operating conditions

Notes:
FRAP probes provide local unsteady measurements of total pressure, static pressure, velocity, total temperature (steady), and various flow angles;
FENT probe provides local unsteady measurements of total pressure and total temperature

TU Darmstadt: TUDa-GLR-OpenStage

TUDa-GLR-OpenStage

Transonic compressor stage geometry
• TU Darmstadt Rotor 1 with StatorOPT, OGV, radial diffusor
• Hub & shroud contour, running tip clearance
Measurement data, exemplary
• Steady state: inlet conditions and 0D, 1D & 2D exit traverses
• Dynamic: unsteady wall pressure at blade tip (steady state & transient operating conditions, e.g. stall inception), unsteady pressure probe at rotor exit

TUDa-GLR-OpenStage

Seoul National University: Transitional Boundary Layers Over Smooth and Transitionally Rough Surfaces Without Pressure Gradient

Topographies of the test surfaces (a) Smooth and (b) Rough
Fig. 1 Topographies of the test surfaces (a) Smooth and (b) Rough.
The data set contains
1)    statistics for smooth and transitionally rough surfaces as well as
2)    unsteady 2-D velocity data

Such data will enable investigators to examine:
1)    boundary layer integral parameters – boundary layer thickness, displacement thickness, momentum thickness, and shape factor;
2)    boundary layer transition - intermittency;
3)    turbulence characteristics - turbulence intensity, Reynolds stress; and
       more
Streamwise turbulence intensity
Fig. 2 Streamwise turbulence intensity contours for (a) Smooth and (b) Rough Surfaces.

Beihang University: Low Speed Stage-A

Fig. 1 Schematic of the low-speed large-scale compressor test facility.

Fig. 1 Schematic of the low-speed large-scale compressor test facility.

Main design & flow features:
•  Large scale design: flow path outer diameter is 1 meter.
•  Hub to shroud ratio:0.6.
•  The blade loading coefficient in terms of mid-span blade speed is 0.35.
•  Large scale corner separation at the stator hub, even at the design condition.

Available measurement data includes:
•  The compressor static pressure rise and efficiency characteristics.
•  The compressor inlet boundary layer.
•  The oil-flow visualization on the stator blade surface.
•  The flow fields inside the rotor/stator passages.
•  The flow fields at the rotor/stator outlets.
Fig. 2 SPIV results in the rotor passage.

Fig. 2 SPIV results in the rotor passage.

Fig. 3 SPIV results in the stator passage.

Fig. 3 SPIV results in the stator passage.

Fig. 4 Oil-flow results.

Fig. 4 Oil-flow results.

Fig. 5 Five-hole probe results at the stator outlet .

Fig. 5 Five-hole probe results at the stator outlet .

Representative references:
Yu, X.J., et al., Stereoscopic PIV measurement of unsteady flows in an axial compressor stage, Experimental Thermal and Fluid Science, 2007(31): 1049-1060.
Liu, B.J., et al., Assessment of curvature correction and reattachment modification into the shear stress transport model within the subsonic axial compressor simulations. Journal of Power and Energy, 2015, 229(8): 910-927.

Beihang University: Low Speed Stage-B

Fig. 1 Compressor static pressure rise characteristics.

Fig. 1 Compressor static pressure rise characteristics.

Fig. 3 Variations of the blockage parameter caused by the TLV.

Fig. 3 Variations of the blockage parameter caused by the TLV.

Main design & flow features:
•  Large scale design: flow path outer diameter is 1 meter.
•  Hub to tip ratio: 0.6.
•  The blade loading coefficient in terms of mid-span blade speed is 0.52.
•  Strong tip leakage flow and breakdown of the tip leakage vortex at the near-stall condition.

Available measurement data includes:
•  The compressor static pressure rise and efficiency characteristics with different rotor tip gaps.
•  The compressor inlet boundary layer.
•  The oil-flow visualization on the stator blade surface.
•  The flow fields inside the rotor/stator passages.
•  The flow fields at the rotor/stator outlets.
Fig. 2 SPIV results.

Fig. 2 SPIV results.

Representative references:
Liu, B.J. et al., Quantitative Evaluation of the Unsteady Behaviors of the Tip Leakage Vortex in a Subsonic Axial Compressor Rotor. Experimental Thermal and Fluid Science, 2016(79): 154-167.
Du, H. et al., Relationship between the Flow Blockage of Tip Leakage Vortex and its Evolutionary Procedures inside the Rotor Passage of a Subsonic Axial Compressor. Journal of Thermal Science, 2013, 22(6): 522-531.

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