scholarly journals Strength Assessment of Fan Blade with Different Materials

2019 ◽  
pp. 266-283
Author(s):  
Polyminna Dileep ◽  
C. Mohan Naidu
Keyword(s):  
Structural Analysis ◽  
Weight Reduction ◽  
Fuel Efficiency ◽  
Aircraft Engine ◽  
Sandwich Composite ◽  
Strength Assessment ◽  
Static And Dynamic Analysis ◽  
Composite Blade ◽  
Aero Engine ◽  
Fan Blade

Weight reduction of turbofan engines is one of the main concerns of aero engine manufacturers in order to cut fuel burn. To achieve higher fuel efficiency, aero engine manufacturers develop turbofans with higher bypass ratio, which can only be achieved with larger (and heavier) fan sections. This makes weight reduction in fan components a major consideration and becomes a key driver for the use of composite materials in future engines. The objective of this project is to design, perform structural analysis and optimization of a Composite fan blade. Development of a fan blade is comparable to a future large aircraft engine fan blade. This thesis is about the structural analysis of a composite fan blade with a honeycomb sandwich construction with a polymer matrix composite and honeycomb Aluminium core compared with baseline solid basic fan blade made of titanium. The focus of this work is to design the sandwich composite blade with honeycomb core and conduct static and dynamic analysis.

A General Ply Design for Aero Engine Composite Fan Blade

2017 ◽  
Author(s):  
Jiaguangyi Xiao ◽  
Yong Chen ◽  
Qichen Zhu ◽  
Jun Lee ◽  
Tingting Ma
Keyword(s):  
Composite Laminates ◽  
Composite Structures ◽  
Stacking Sequence ◽  
Composite Blade ◽  
Arduous Task ◽  
Aero Engine ◽  
Margin Of Safety ◽  
Fan Blade ◽  
The Impact ◽  
Ply Orientation

Composite fan blade ply lay-up design, which includes ply drop-off/shuffle design and stacking sequence design, makes fan blade structures different from traditional composite structures. It gives designers more freedom to construct high-quality fan blades. However, contemporary fan blade profiles are quite complex and twisted, and fan blade structures are quite different from regular composite structures such as composite laminates and composite wings. The ply drop-off design of a fan blade, especially for a fully 3D fan blade, is still an arduous task. To meet this challenge, this paper develops a ply lay-up way with the help of a software called Fibersim. The fully 3D fan blade is cut into ply pieces in Fibersim. As a result, an initial ply sequence is created and ply shuffle could revise it. Because of the complexity of ply shuffling, the ply shuffle table developed in this paper mainly refers to the design experience gained from simple plate-like laminate structures and some criterion. Besides, the impact of different ply orientation patterns on the reliability of composite fan blade is studied through static and modal numerical analysis. The results show that this ply lay-up idea is feasible for aero engine composite fan blade. Under the calculated rotating speeds, the ply stacking sequence 4 (i.e.[−45°/0°/+45°/0°] with the outer seven groups are [−45°/0°/−45°/0°]) shows the greatest margin of safety compared with other stacking sequences. Modal analysis shows that plies with different angles could have relatively big different impacts on blades vibration characteristics. The composite fan blade ply design route this paper presents has gain its initial success and the results in this paper might be used as basic references for composite blade initial structural design.

scholarly journals Whole Engine Interaction in a Bladed Rotor-to-Stator Contact

2014 ◽  
Author(s):  
Marie-Océane Parent ◽  
Fabrice Thouverez ◽  
Fabrice Chevillot
Keyword(s):  
Aircraft Engine ◽  
Special Focus ◽  
Aero Engine ◽  
Elastic Link ◽  
Bladed Rotor ◽  
Engine Dynamic ◽  
Fan Blade ◽  
Model Components ◽  
Type Of Behavior ◽  
Fully Coupled

Reducing the clearances between rotating and fixed parts is an important factor in increasing the performances of turbomachines. The physical counterpart however is an evolution in possible rotor-stator contacts capable of causing unstable dynamic behavior. A proper prediction of the rotor-stator contact occurrences and associated induced phenomena, has therefore become of a great interest for aero-engine mechanical engineers. Most numerical simulations involving rotor-stator contact can be divided into two types of physical behavior. The first focuses on contact induced blade/casing interactions, in only taking into account the blades and casing flexibility. The second type of behavior takes into account the shaft dynamic while neglecting blade flexibility. Future designs of aircraft engines will however raise the need to combine these two types of models. Since, the structural components are more flexible, the dynamic coupling between engine modules is increased. This paper proposes a study based on a structure representative of the whole aircraft engine, including the contacts that may arise between the fan-blade tips and fan casing. We have introduced a fully-coupled phenomenological model with flexible blades, shaft and casing. Furthermore, this model includes an elastic link between shaft and casing to simulate the fan frame behavior. We begin by explaining the linear results, which highlight the dynamic couplings between these various model components. During a second step, this paper presents the nonlinear results obtained by introducing a contact law. These results demonstrate the influence of the whole engine dynamic on contact-related behavior with special focus on the system dynamic stability.

Aero Engine Development for the Future

1983 ◽  
Vol 197 (3) ◽  
pp. 149-157 ◽  
Author(s):  
H W Bennett
Keyword(s):  
Mechanical Design ◽  
Low Cost ◽  
Fuel Efficiency ◽  
Thermodynamic Cycle ◽  
Aircraft Engine ◽  
Advanced Technology ◽  
High Fuel Efficiency ◽  
Aero Engine ◽  
Improved Performance ◽  
And Performance

A historical survey of the development and future trends in aero engine design and performance are given. Emphasis is placed on the achievement of low cost of ownership through high fuel efficiency. Simple basic principles controlling the conceptual design and performance are described. The choice of engine thermodynamic cycle is discussed with emphasis on the civil transport engine. The differing requirements of the military aircraft engine are briefly stated. Short-term possibilities for improved performance and longer term speculative proposals are made. Advanced technology requirements in materials, mechanical design and aerodynamics are outlined.

scholarly journals Design of Center Pillar with Composite Reinforcements Using Hybrid Molding Method

Materials ◽  
2021 ◽  
Vol 14 (8) ◽  
pp. 2047
Author(s):  
Ji-Heon Kang ◽  
Jae-Wook Lee ◽  
Jae-Hong Kim ◽  
Tae-Min Ahn ◽  
Dae-Cheol Ko
Keyword(s):  
Composite Materials ◽  
Weight Reduction ◽  
Fuel Efficiency ◽  
Vehicle Body ◽  
Process Time ◽  
Fiber Reinforced ◽  
Fiber Reinforced Plastic ◽  
Molding Method ◽  
Reinforced Plastic ◽  
Composite Reinforcements

Recently, with the increase in awareness about a clean environment worldwide, fuel efficiency standards are being strengthened in accordance with exhaust gas regulations. In the automotive industry, various studies are ongoing on vehicle body weight reduction to improve fuel efficiency. This study aims to reduce vehicle weight by replacing the existing steel reinforcements in an automobile center pillar with a composite reinforcement. Composite materials are suitable for weight reduction because of their higher specific strength and stiffness compared to existing steel materials; however, one of the disadvantages is their high material cost. Therefore, a hybrid molding method that simultaneously performs compression and injection was proposed to reduce both process time and production cost. To replace existing steel reinforcements with composite materials, various reinforcement shapes were designed using a carbon fiber-reinforced plastic patch and glass fiber-reinforced plastic ribs. Structural analyses confirmed that, using these composite reinforcements, the same or a higher specific stiffness was achieved compared to the that of an existing center pillar using steel reinforcements. The composite reinforcements resulted in a 67.37% weight reduction compared to the steel reinforcements. In addition, a hybrid mold was designed and manufactured to implement the hybrid process.

scholarly journals Design & Weight Optimization of a Wheel Rim for Sport Utility Vehicle.

2018 ◽  
Vol 172 ◽  
pp. 03006
Author(s):  
Harish Panjagala ◽  
Balakrishna M ◽  
Shasikant Kushnoore ◽  
E L N Rohit Madhukar
Keyword(s):  
Structural Analysis ◽  
Point Of View ◽  
Weight Optimization ◽  
Strength Assessment ◽  
Suitable Material ◽  
The Road ◽  
Wheel Rim ◽  
Standard Values ◽  
Design Weight ◽  
Structural Point

Automobile have various parts which are important for good running of the vehicle. The most important safety components from a structural point of view are the road wheels. They are required to be lighter and more fascinating to the buyer all the time. This implies that it's important to perform a lot of accurate strength assessment on wheel styles. The wheel rim plays a major role in vehicle dynamics. This paper deals with the design and model of different wheel rims based on weight optimization and also structural analysis has been carried out. It has been compared with standard values by varying two different materials. In addition, from the obtained outputs of simulations and the weight optimization, we suggested Aluminium alloys as most suitable material for SUV. Model is created by using SOLIDWORKS software 2015 and structural analysis &; weight optimization is done by using ANSYS WORKBENCH 16.0.

A Study on the Effect of Bird Hit Damage on the Dynamic Response of Aero-Engine Fan Blade

2013 ◽  
Author(s):  
Hithesh Channegowda ◽  
Raghu V. Prakash ◽  
Anandavel Kaliyaperumal
Keyword(s):  
Dynamic Characteristics ◽  
Natural Frequencies ◽  
Mode Shapes ◽  
Foreign Object Damage ◽  
Aero Engine ◽  
Need To Evaluate ◽  
Bird Impact ◽  
Post Impact ◽  
Fan Blade ◽  
Critical Components

Fan blades of an aero-engine assembly are the critical components that are subjected to Foreign Object Damage (FOD) such as bird impact. Bird impact resulting in deformation damage onto set of blades, which in turn alters the blade mass and stiffness distribution compared to undamaged blades. This paper presents the numerical evaluation of dynamic characteristics of bird impact damaged blades. The dynamic characteristics evaluated are the natural frequencies and mode shapes of post impact damaged set of blades and the results are compared with undamaged set of blades. The frequencies and mode shapes are evaluated for the damaged blades, with varying angles of bird impact and three blade rotational speeds. Study reveals that first bending and torsional frequencies of deformed blades are significantly affected compared to undamaged set of blades. Study emphasize the need to evaluate the natural frequencies deformed blades, that has direct bearing on High Cycle Fatigue (HCF) life of the blade, to ensure post damaged blades operate safely for certain time to reduce inflight accidents and safe landing.

scholarly journals A Numerical Method Used for the Simulation of Self-Excited Vibrations that Arise in the Aircraft Engine Fan Blade Ring

2020 ◽  
Vol 0 (2) ◽  
pp. 12-18
Author(s):  
Viacheslav Vladimirovich Donchenko ◽  
Vitaly Isaevich Gnesin ◽  
Lyubov Vladimirovna Kolodyzhnaya ◽  
Igor Fedorovich Kravchenko ◽  
Oleksii Vladimirovich Petrov
Keyword(s):  
Numerical Method ◽  
Aircraft Engine ◽  
Blade Ring ◽  
Fan Blade

Study on Sandwich Core Modeling for Structural Analysis of Sandwich Composite Structure

2018 ◽  
Vol 926 ◽  
pp. 57-63
Author(s):  
Hyun Bum Park
Keyword(s):  
Structural Analysis ◽  
Composite Structure ◽  
Solid Modeling ◽  
Modeling Method ◽  
Core Structure ◽  
Sandwich Composite ◽  
Damage Area ◽  
The Core ◽  
Sandwich Core ◽  
Sandwich Composite Structure

This study aims to investigate numerically the damage area of a sandwich composite structure. In this work, the optimal sandwich core modeling method was proposed. This study applied two modeling methods to compare their analysis results for the structural analysis of the sandwich composite structure. Firstly, the modeling of sandwich core structure was performed with laminate modeling method. Secondly, the modeling of core structure was performed with core solid modeling method. The laminate modeling method was compared with the core solid modeling method. For the modeling, a carbon/epoxy composite structure was applied to the face sheet. And a nomex honeycomb core was applied to the core. Finally, comparing the result of modeling as actual shape with the one of virtually applying the thickness and modeling, it was examined that the former had three times more stress than the latter.

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