This Blog post gives a brief outline of the throughflow method for turbomachinery flows and presents the calculated performance results of a Single-Stage Axial-Flow Compressor validation.

 

The throughflow method for turbomachinery performance prediction is a quasi-three dimensional CFD method that solves azimuth-averaged flow in the meridional plane.  Using an azimuth-averaged approach reduces the grid resolution requirement in the tangential direction to only two points (one cell), with a corresponding reduction in the computational cost relative to a full 3-D CFD simulation. For example, for a 3-D case with 100 grid points in the tangential direction, the throughflow case will run approximately two orders-of-magnitude times faster than a corresponding 3-D CFD simulation.

 

Throughflow methods provide a reasonable trade-off between speed and accuracy and are useful for performing parametric-studies early in the conceptual and preliminary design phases [1].  An integrated throughflow solver is incorporated in the Concepts NREC’s Agile Engineering Design System®.

 

Easy Access to Throughflow Solver Loss Models

 

In lieu of resolving the tangential flow direction, throughflow solvers use body-force source terms to capture blade profile losses and turning effects and shock losses.  The loss models are derived primarily from the Koch-Smith model for compressors and the Ainley-Mathieson model for turbines. 

 

The Concepts NREC’s Agile Engineering Design System® provides access to an integrated throughflow solver (grid generation, pre-processing, post-processing, etc.) and it provides options for different loss and deviation models, Figure 1.  The built-in throughflow solver also provides a set of default settings.  These losses and settings can be calibrated to match actual performance data.

 

The accuracy and utility of the methodology was indicated by performing a set of throughflow validation cases [1]. 

 Through Flow Loss Models-965267-edited.png

Figure 1: Some of the options for Through-Flow Loss Models

 

Overview of GT2015-43763 Validation Cases

 

Reference [1] presents a set of validation cases.  These cases include: NACA cascade loss-bucket calculations (loss-coefficient versus incidence angle); DCA cascade loss-bucket calculations; performance map calculations for the DFLVR Single-Stage Axial-Flow Compressor and a study of the Cambridge Low-Speed Turbine.

 

The DFLVR Single-Stage Axial-Flow Compressor is a high-speed compressor tested in Germany in the 1970s.  The compressor produces a pressure ratio of 1.51 while operating at a relative tip Mach number of 1.4 at the design point.  Results for this case were presented in 2015 [1] and are repeated here.

 

 Meridonal View of Through Flow  Solver-838225-edited.png

Figure 2: Meridional View of DFLVR Single-Stage Axial Compressor Throughflow Model

 

The compressor meridional view is shown in Figure 2 and was generated by the throughflow solver pre-processor.  A set of throughflow Single-Stage Axial-Flow Compressor validation runs was built by accepting the default parameters for the loss models and running 55%, 85%, and 100% speed-lines.  At least nine throughflow cases were run for each speed.  The efficiency and pressure-ratio results are compared to experimental data and 3-D CFD results in Figure 3.

Reference [1] concluded that the throughflow solver did quite well in capturing the magnitude and characteristic losses in the stage for the DFLVR Single-Stage Axial Compressor.  They also noted that the low-speed line is somewhat higher in performance relative to the test performance values.

 Predicted performance using default models-915078-edited.png

Figure 3: Predicted Performance using Default Models/Settings, Reference [1]

 

Remarks

The throughflow solver is fast and allows easy access to loss model settings and parameters via a graphical user interface window.  Algorithm updates/settings that build on the improvements presented in [1] are being considered.

 

References

[1] Andersen, M. and Bonhaus, D.L., "A Comprehensive Throughflow Solver Method for Modern Turbomachinery Design," ASME Turbo Expo 2015, GT2015-43763, June 15-19, 2015, Montreal, Canada.