Faculté des Sciences appliquées
Faculté des Sciences appliquées

Final work : Assessment of throughflow closure models for a modern axial compressor

Ruis, Bart ULiège
Promotor(s) : Terrapon, Vincent ULiège
Date of defense : 24-Jun-2021/25-Jun-2021 • Permalink :
Title : Final work : Assessment of throughflow closure models for a modern axial compressor
Translated title : [fr] Évaluation de modèles de fermeture de débit pour un compresseur axial moderne
Author : Ruis, Bart ULiège
Date of defense  : 24-Jun-2021/25-Jun-2021
Advisor(s) : Terrapon, Vincent ULiège
Committee's member(s) : Hillewaert, Koen ULiège
Budo, Arnaud ULiège
Language : English
Number of pages : 79
Keywords : [en] Throughflow method
[en] Navier-Stokes based
[en] Computational Fluid Dynamics
[en] Time-marching
[en] Profile loss
[en] Deviation angle
[en] Tip leakage flows
Discipline(s) : Engineering, computing & technology > Aerospace & aeronautics engineering
Target public : Researchers
Professionals of domain
Institution(s) : Université de Liège, Liège, Belgique
Degree: Master en ingénieur civil en aérospatiale, à finalité spécialisée en "turbomachinery aeromechanics (THRUST)"
Faculty: Master thesis of the Faculté des Sciences appliquées


[en] This master’s thesis is dedicated to the assessment of various closure models for Navier-
Stokes-based throughflow modelling. This is done in the context of a high-subsonic flow
compressor with highly loaded blades of three-dimensional design.
The averaging cascade of Adamczyk is employed to identify the unclosed terms in the
Navier-Stokes throughflow equations. The terms of major importance are identified based
on the literature and related to the physical flow features that they represent. Empirical
models for the blade profile loss, deviation angle, tip leakage loss, and end-wall boundary
layer are then selected from the literature.
The accuracy of these models is assessed through three approaches. First, two-dimensional
blade-to-blade computational fluid dynamics simulations of a stator blade row are performed
to analyse various empirical models for profile loss and deviation. This analysis
confirms that compressibility effects need to be accounted for at elevated Mach number,
particularly for prediction at off-design incidence angle. The profile loss model of König is
shown to be more accurate than the model of Lieblein in this respect. The deviation angle
models of Carter, Lieblein and Wu Dong-Run are shown to give reasonable predictions at
design incidence angle.
The second approach is to feed the empirical models with circumferentially averaged
results of three-dimensional computational fluid dynamics simulations of the entire compressor.
This reveals the deficiency of König’s model for incidence angles much smaller
than the predicted minimum loss incidence angle. Two tip leakage models of Lakshminarayana
are also assessed in this context.
In the third approach, the empirical models are implemented in a Navier-Stokes throughflow
model. The resulting radial distributions of loss and deviation are analysed for all
blade rows at nominal operating conditions. Finally, the results are discussed in terms of
isentropic efficiency, pressure ratio, and total temperature ratio of the entire compressor
operating at off-design conditions.



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  • Ruis, Bart ULiège Université de Liège > Master ingé. civ. aérospat., à fin. (THRUST)


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