Key points are not available for this paper at this time.
Abstract Designing future gas turbines needs sufficiently accurate methods for determining the temperature distribution parts under high mechanical and thermal loads. Furthermore, to calibrate analytical thermal models with engine test data, which is an important step in the development process, strong engineering judgement and experience is required, and generally an extensive iterative process is needed to reach the predefined matching quality. Coupled simulations can significantly improve quality of conjugate heat transfer calculations and reduce the thermal matching effort. A method for strong aero-thermal coupling for specific demands of aero engine heat transfer is presented. It is based on a partitioned approach designed to integrate standard processes, methods and tools (like mapping methods and solvers) for industrial applications. An efficient approach to take the interaction of the material with the convecting fluid into account is to embed stationary CFD analysis in a flight mission calculation. This enables much fewer steps than necessary for a monolithic coupling like CHT and therefore saves computational effort. The presented multi-fidelity approach includes strong system coupling of 1D, 2D and 3D models. A high pressure compressor of a real aero engine has been thermally investigated using the reported coupling method. CFD was used in the rotor drum cavity and standard thermal modeling with FEM for the solid parts combined with flow network/correlations for the low fidelity flow areas. Steady state calculations for high and low loading cases and a transient acceleration were performed. The results are compared with measurements via a calibrated standard thermal model.
Israel et al. (Mon,) studied this question.