Registered attendees of the GPPS Xi’an21 technical conference will receive data sets by ETH Zurich, TU Darmstadt, Seoul National University, and Beihang University if requested.
In the public domain, there are very few turbomachinery geometries and accompanying validation data. The GPPS Xi’an21 technical conference will feature special sessions dedicated to presenting the latest geometries and data sets to be released shortly after the Xi’an technical conference.
The strategy of GPPS is to make experimental data readily available to all researchers, and we invite any new research conducted with it to be presented at future GPPS conferences.
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 data analysis, can only be included in a publication where the named registrant, who received the data, is an author.
Following the GPPS Xi’an21 technical conference, the following data sets will be made available to the attendees of this event, including the latest data sets provided by Beihang University:
ETH Zurich: D-Turbine – 1.5 stage high work axial turbine
• 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
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
Seoul National University: Transitional Boundary Layers Over Smooth and Transitionally Rough Surfaces Without Pressure Gradient
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
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
Beihang University: Low Speed Stage-A
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.
