Master thesis and internship[BR]- Master's thesis : Secondary flows in tandem blades[BR]- Integration Internship : Safran Group
Marchi, Simone
Promoteur(s) : Hillewaert, Koen
Date de soutenance : 4-sep-2023/5-sep-2023 • URL permanente : http://hdl.handle.net/2268.2/18261
Détails
Titre : | Master thesis and internship[BR]- Master's thesis : Secondary flows in tandem blades[BR]- Integration Internship : Safran Group |
Titre traduit : | [en] Secondary flow in tandem blades |
Auteur : | Marchi, Simone |
Date de soutenance : | 4-sep-2023/5-sep-2023 |
Promoteur(s) : | Hillewaert, Koen |
Membre(s) du jury : | Terrapon, Vincent
Dimitriadis, Grigorios Peeters, Laurens |
Langue : | Anglais |
Nombre de pages : | 100 |
Mots-clés : | [en] Compressor [en] CFD [en] Secondary flows [en] Corner sepration [en] Stall indicator [en] Turbulence models |
Discipline(s) : | Ingénierie, informatique & technologie > Ingénierie aérospatiale |
Organisme(s) subsidiant(s) : | Safran AeroBooster |
Public cible : | Autre |
Institution(s) : | Université de Liège, Liège, Belgique Safran AeroBooster, Liège, Belgique |
Diplôme : | Master en ingénieur civil en aérospatiale, à finalité spécialisée en "aerospace engineering" |
Faculté : | Mémoires de la Faculté des Sciences appliquées |
Résumé
[en] The design of an aircraft engine requires from the low pressure compressor (LPC) at every
engine operating point (CRUISE, CLIMB, TAKE-OFF, etc):
• A specific capacity in mass flow and compression ratio,
• While maximising the efficiency.
In order to achieve this, for a certain chosen architecture:
• Rotors are designed to deliver a certain compression ratio by flow turning,
• Stators are designed to diffuse the flow while counteracting the swirl created by the
rotor.
In certain engine designs, the amount of flow turning required is greater than what a
single blade can provide. This results may create flow detachment and may compromise
the LPC’s ability to ensure each engine operating point at a proper efficiency.
A valid solution is to use tandem blades, meaning two blades within one row among
which the flow turning is divided. that makes the flow more stable and attached.
One of the main causes of loss is the presence of secondary flows, which are created
by the low momentum zones due to the hub and shroud interacting with the blade geometry.
The tandem configuration is a solution to improve the situation and reduce their negative
impact. The interaction of these secondary flows with a tandem blade design is a relatively
new challenge in the industrial and academic community.
The aim of this project is to evaluate the secondary flows in tandem blades by developing
an objective method to quantify and localise the losses and then to distinguish their main
sources. A qualitative analysis of the flow along the two types of tandem blades designed
by Safran AeroBooster(SAB) is carried out. The case study is the Outlet Guide Vane
(OGV) geometry of the booster provided by SAB.
A comparison of different tandem design philosophies is carried out.
This is followed by a study of the effect of the slot geometry between the front and aft
blade.
Finally, an evaluation of the effect of the different turbulence models is evaluated.
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