Abstract
In this paper, the research on two types of unsteady flow problems in turbomachinery including blade flutter and rotor-stator interaction is made by means of numerical simulation. For the former, the energy method is often used to predict the aeroelastic stability by calculating the aerodynamic work per vibration cycle. The inter-blade phase angle (IBPA) is an important parameter in computation and may have significant effects on aeroelastic behavior. For the latter, the numbers of blades in each row are usually not equal and the unsteady rotor-stator interactions could be strong. An effective way to perform multi-row calculations is the domain scaling method (DSM). These two cases share a common point that the computational domain has to be extended to multi passages (MP) considering their respective features. The present work is aimed at modeling these two issues with the developed MP model. Computational fluid dynamics (CFD) technique is applied to resolve the unsteady Reynolds-averaged Navier-Stokes (RANS) equations and simulate the flow fields. With the parallel technique, the additional time cost due to modeling more passages can be largely decreased. Results are presented on two test cases including a vibrating rotor blade and a turbine stage.
Highlights
With the rapid improvements in the performance of computer, the CFD technique has been a useful tool in the turbomachinery industry
Blade flutter is caused by interactions between aerodynamic forces and structural vibrations of the blade and could lead to blade damage and even aero-engine failure
An effective MP model based on CFD technique is presented and applied in two test cases
Summary
With the rapid improvements in the performance of computer, the CFD technique has been a useful tool in the turbomachinery industry. Rotor-stator interaction is another type of unsteady problems and it usually consists of several sources of unsteadiness involving the relative motion between adjacent rows together with boundary layers, wakes and shocks. An effective type of rotor-stator interface treatment is the so-called domain scaling method (DSM) 13 It models a higher number of blade passages or sometimes slightly scales the geometry to make the combination pitch distances in each row identical. Giboni et al[15] study the unsteady labyrinth seal leakage flow and main flow of a turbine by experiment and numerical investigation. For both issues discussed above, multi passages are required to make the periodicity of upper and lower periodic boundaries still exists. Two available test cases with some necessary modifications are studied, including a transonic compressor rotor with blades vibrating and an axial low-pressure turbine stage
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