How to create robust modelling and high definition blade geometry

In the last blog, we highlighted the new modules in TURBOdesign Pre for the meanline design of axial fans and pumps stages and predicting the performance map of radial inflow turbines. In this blog, we will further discuss new features and functionality in TURBOdesign Suite v6.7 to enable designers to improve efficiency, achieve higher performance and deliver faster designs to achieve and maintain market-leading products.

What else is new?

Script version of TURBOdesign Pre

TURBOdesign Pre can now also be run in batch mode similarly to TURBOdesign1 script version. TURBOdesign Pre script version enables the user to run cases without interaction with the interface. It can be used to perform a high volume of calculations or to perform optimization calculations.

Improved mesh for blades with curved leading and trailing edge

The grid generated for cases which have curved leading and/or trailing edges has been improved by smoothing the mesh across the leading and/or trailing edge.

New geometry export functionality

The geometry export functionality of TURBOdesign1 has been enhanced with a new blade geometry construction procedure, as shown in Figure 7. The 3D blade geometry is generated by applying the normal thickness distribution directly to the 3D camber surface generated by TURBOdeign1, removing the problems found when making use of the tangential thickness. The highly refined thickness stored in the .geo files of version 6.7 also allows a much-improved definition of leading and trailing edges.
The leading and trailing edge modification can also be applied; this is performed by directly performing the elliptic modification to the thickness distribution. This approach is more robust than the Leading and Trailing Edge Modification tool, producing better results.
The export formats available are:

  • Iges
  • STEP
  • TurboGrid
  • BladeGen


Figure 8 and Figure 9 display geometries exported with the new functionality.

The conversion functionality is currently available only for geometries generated by the TURBOdesign1 solver version 6.7 and is not backwards compatible. As the geometry is built differently, it will slightly differ from those originally created by TURBdesign1.

construct-3D-blade-geometry

Figure 7: A new procedure to construct the 3D blade.

computational-domain-for-CFD-analysis-generated-geometry

Figure 8: Computational domain for CFD analysis generated with the new geometry export functionality.

3D-solid-blade-geometry-axial-fan

Figure 9: 3D solid blade geometry for axial fan generated with the new geometry export functionality.

Improved genetic algorithm optimizer

The multi-objective genetic algorithm used in TURBOdesign Optima (NSGAII) has been further enhanced and improved to provide a better spread of points on the Pareto Front with lower number of population size and lower number of generations hence improving the computational efficiency of the algorithm. 

a) optimization-point-distribution-solution-tsdv6.6.jpeg-3  b)   improved-optimization-solution-tdsv6.7.jpeg

Figure 10: Optimization point distribution and parent front for population 20 and 20 generation. (a): Solution generated by version 6.6, (b): Solution generated by version 6.7.

Discover 6.7 update to TURBOdesign Suite's new features and functionality to enable designers to improve efficiency, achieve higher performance and deliver faster designs to achieve and maintain market-leading products.

 

 Webinar: Introducing TURBOdesign Suite v6.7

TDSv6.7-1

Register for our webinar on Wednesday 28th November to see the new TURBOdesign updates.

This webinar is offered several times. Select the time that works best for you.

Register for: 9am GMT (6pm JST) webinar
Register for: 5pm GMT (12pm EDT) webinar

Book a LIVE demo on the design of a turbomachinery application of your choice.

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Darshan Patel

Marketing Manager

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