Title
Istraživanje zamornog veka nosećih strukturalnih elemenata izrađenih od super legura
Creator
Grbović, Aleksandar, 1970-
Copyright date
2012
Object Links
Select license
Autorstvo 3.0 Srbija (CC BY 3.0)
License description
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Language
Serbian
Cobiss-ID
Theses Type
Doktorska disertacija
description
Datum odbrane: 22.06.2012.
Other responsibilities
mentor
Rašuo, Boško, 1949-
član komisije
Gvozdenović, Slobodan, 1950-
član komisije
Dinulović, Mirko, 1967-
Academic Expertise
Tehničko-tehnološke nauke
University
Univerzitet u Beogradu
Faculty
Mašinski fakultet
Alternative title
Investigation of fatigue life in superalloys structural components
Publisher
Beograd : [A. Grbović],
Format
PDF/A (344 listova)
description
Mašinstvo - Vazduhoplovstvo / Mechanical Engineering - Aeronautics
Abstract (sr)
The researches in the field of fatigue failure are mainly aimed at
identifying the factors which determine the fatigue behavior of the structural
components and their inter relations. It is known that the fatigue resistance of
structures is influenced mostly by load sequences, combinations of load types,
as well as by materials and their fatigue properties. Therefore, the fatigue life
cannot be determined without a thorough analysis of these parameters.
Materials known as superalloys exhibit excellent mechanical strength and
considerable creep resistance, especially at high temperatures. However, a
critical property of these alloys is their resistance to fatigue-crack propagation,
particularly at service temperatures. Besides, their fatigue features are not as
easily accessible as of other materials (aluminum or steel, for instance).
Consequently, determining the fatigue life in superalloy structures is not an
easy task to accomplish.
Taking into consideration the superalloy properties set in the NASGRO
database, this thesis has explored the fatigue life of the real structural
components, considering – at the same time – the stresses of both constant and
variable amplitudes. The structural components have been designed in the
CATIA v5, whereas the propagations of the 2D and 3D fatigue cracks through
the structure have been simulated afterwards by the application of the FEM in
the FRANC2D/L, and the application of the extended finite element method
(XFEM) in the Abaqus software.
Special attention has been devoted to the fatigue analysis of the spar of a
light aircraft. Numerical methods have been used to identify the weak points on
the spar, along with the fatigue life of a spar crack and its direction of
propagation. The results gained have corresponded well with the experimental
values obtained on the spar of the alloy 2024-T3. Taking into account the good
correlation between numerical and experimental values, the same finite element
models have been used to estimate the crack life on the spars made of super
alloys. The investigations have shown that the majority of the super alloys
possess fatigue properties similar to aluminum, and in a few of them the life of
fatigue crack has proved to be much longer than in the 2024-T3 alloy.
Authors Key words
fatigue life, superalloys, extended finite element method, numerical
simulations, experimental analysis of aircraft wing spar
Classification
620
Subject
Super legure
Subject
Avioni
Type
Tekst
Abstract (sr)
The researches in the field of fatigue failure are mainly aimed at
identifying the factors which determine the fatigue behavior of the structural
components and their inter relations. It is known that the fatigue resistance of
structures is influenced mostly by load sequences, combinations of load types,
as well as by materials and their fatigue properties. Therefore, the fatigue life
cannot be determined without a thorough analysis of these parameters.
Materials known as superalloys exhibit excellent mechanical strength and
considerable creep resistance, especially at high temperatures. However, a
critical property of these alloys is their resistance to fatigue-crack propagation,
particularly at service temperatures. Besides, their fatigue features are not as
easily accessible as of other materials (aluminum or steel, for instance).
Consequently, determining the fatigue life in superalloy structures is not an
easy task to accomplish.
Taking into consideration the superalloy properties set in the NASGRO
database, this thesis has explored the fatigue life of the real structural
components, considering – at the same time – the stresses of both constant and
variable amplitudes. The structural components have been designed in the
CATIA v5, whereas the propagations of the 2D and 3D fatigue cracks through
the structure have been simulated afterwards by the application of the FEM in
the FRANC2D/L, and the application of the extended finite element method
(XFEM) in the Abaqus software.
Special attention has been devoted to the fatigue analysis of the spar of a
light aircraft. Numerical methods have been used to identify the weak points on
the spar, along with the fatigue life of a spar crack and its direction of
propagation. The results gained have corresponded well with the experimental
values obtained on the spar of the alloy 2024-T3. Taking into account the good
correlation between numerical and experimental values, the same finite element
models have been used to estimate the crack life on the spars made of super
alloys. The investigations have shown that the majority of the super alloys
possess fatigue properties similar to aluminum, and in a few of them the life of
fatigue crack has proved to be much longer than in the 2024-T3 alloy.
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