The paper presents a multi-disciplinary approach foraero-thermal and heat transfer analysis for internal flows. The  
versatility and potential benefit offered by the approach is described through the application to a realistic low pressure tur-  
bine assembly. The computational method is based on a runtime code-coupling architecture that allows mixed models and  
simulations to be integrated together for the prediction of the sub-system aero-thermal performance. In this specific applica-  
tion the model is consisting of two rotor blades, the embedded vanes, the inter-stage cavity and the solid parts. The geometry  
represents a real engine situation. The key element of the approach is the use of a fully modular coupling strategy that aims to combine (1) flexibility for design needs, (2) variable level of modelling for better accuracy and (3) in memory code coupling for preserving computational efficiency in large system and sub-system simulations.  
For this particular example Reynolds Averaged Navier-Stokes (RANS) equations are solved for the fluid regions and  
thermal coupling is enforced with the metal (conjugate heat-transfer). Fluid-fluid interfaces use mixing planes between the  
rotating parts while overlapping regions are exploited to link the cavity flow to the main annulus flow as well as in the cavity  
itself for mapping of the metal parts and leakages. Metal temperatures predicted by the simulation are compared to those  
retrieved from a thermal model of the engine, and the results are discussed with reference to the underlying flow physics.


A Multi-Fidelity Aero-Thermal Design Approach for Secondary Air Systems

Division / Sponsor:
International Gas Turbine Institute (IGTI)

Paper Proceedings: https://asmedigitalcollection.asme.org/GT/GT2020/volume/84058

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