Abstract A common requirement for turbomachinery testing facilities is the ability to independently control Mach number and Reynolds number. In practice, this means independent of inlet total pressure exit static in a test facility. paper, we present solution problem with particular applicability large-scale annular facilities. We describe design commissioning combined dump diffuser deswirl sys...

This paper reviews the development of computational fluid dynamics (CFD) specifically for turbomachinery simulations and with a particular focus on application to problems with complex geometry. The review is structured by considering this development as a series of paradigm shifts, followed by asymptotes. The original S1-S2 blade-blade-throughflow model is briefly described, followed by the de...

A mesh adaptation methodology for wall-modeled turbomachinery Large Eddy Simulation (LES) is proposed, simultaneously taking into account two quantities of interest: the average kinetic energy dissipation rate and normalized wall distance y+. This strategy first tested on a highly loaded transonic blade with separated flow, compared to wall-resolved LES results, as well experimental data. The a...

The purpose of this work is to compare di erent low-Reynolds-number turbulence models and their suitability for the highly three dimensional return channel with a deswirl cascade. A comparison is made between Chien's k model, Chien's model with a rotational correction, Gatski et al. ARSM and the full Reynolds stress model by Speziale et al.. Experiments are provided by Concepts ETI. MAIN RESULT...

The demand for increased turbomachinery performance, both, towards higher pressures and temperatures, leads to high thermal-loads of specific components can critically affect mechanical integrity. In the particular case rotating-disk configurations, like back-side wheels or in cavities, a very efficient way cooling is jet impingement. An example this situation are pressure-ratio turbochargers, ...

Abstract We note that Eq. (7) in the original paper is wrong, namely, it contains turbomachinery diameter, D, at denominator instead of numerator

Abstract Lattice Boltzmann simulations of corner separation flow in a compressor cascade are presented. The lattice approach is rather new the context turbomachinery, and configuration known to be particularly challenging for turbulence modeling. present methodology characterized by quasi-autonomous meshing strategy limited computational cost (a net ratio 5 compared previous finite-volume compr...