Gas turbine design has been characterized over the years by a continuous increase of the maximum cycle temperature, justified by a corresponding increase of cycle efficiency and power output. In such way, turbine components heat load management has become a compulsory activity, and then, a reliable procedure to evaluate the blades and vanes metal temperatures is, nowadays, a crucial aspect for a safe components design. In the framework of the design and validation process of high pressure turbine cooled components of the BHGE NovaLTTM 16 gas turbine, a decoupled methodology for conjugate heat transfer prediction has been applied and validated against measurement data. The procedure consists of a conjugate heat transfer analysis in which the internal cooling system (for both airfoils and platforms) is modeled by an in-house one-dimensional thermo-fluid network solver, the external heat loads and pressure distribution are evaluated through 3D computational fluid dynamics (CFD) analysis and the heat conduction in the solid is carried out through a 3D finite element method (FEM) solution. Film cooling effect has been treated by means of a dedicated CFD analysis, implementing a source term approach. Predicted metal temperatures are finally compared with measurements from an extensive test campaign of the engine in order to validate the presented procedure.
Conjugate Heat Transfer Methodology for Thermal Design and Verification of Gas Turbine Cooled Components
Contributed by the International Gas Turbine Institute (IGTI) of ASME for publication in the JOURNAL OF TURBOMACHINERY. Manuscript received July 17, 2018; final manuscript received August 1, 2018; published online October 15, 2018. Editor: Kenneth Hall.
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Winchler, L., Andreini, A., Facchini, B., Andrei, L., Bonini, A., and Innocenti, L. (October 15, 2018). "Conjugate Heat Transfer Methodology for Thermal Design and Verification of Gas Turbine Cooled Components." ASME. J. Turbomach. December 2018; 140(12): 121001. https://doi.org/10.1115/1.4041061
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