On the design and structural analysis of jet engine fan blade structures

2013 ◽  
Vol 60 ◽  
pp. 1-11 ◽  
Author(s):  
Leye M. Amoo
Keyword(s):  
Structural Analysis ◽  
Jet Engine ◽  
Fan Blade

J0110103 A dynamic behavior analysis of jet-engine fan blade under impact loading

2015 ◽  
Vol 2015 (0) ◽  
pp. _J0110103--_J0110103-
Author(s):  
Bidhar Kumar SUJIT ◽  
Yoshinori SHIIHARA ◽  
Nobuhiro YOSHIKAWA ◽  
Hiroshi KUROKI ◽  
Masahiro HOJO
Keyword(s):  
Behavior Analysis ◽  
Dynamic Behavior ◽  
Impact Loading ◽  
Jet Engine ◽  
Fan Blade

Bird strike analysis of jet engine fan blade

2014 ◽  
Author(s):  
Narender Lakshman ◽  
Ratnesh Raj ◽  
Yagnavalkya Mukkamala
Keyword(s):  
Bird Strike ◽  
Jet Engine ◽  
Fan Blade

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.

Adjoint-Based Optimization of a Modern Jet-Engine Fan Blade

2020 ◽  
Author(s):  
Andrea Giugno ◽  
Shahrokh Shahpar ◽  
Alberto Traverso
Keyword(s):  
Design Space ◽  
Characteristic Curve ◽  
Free Form ◽  
Design Parameters ◽  
Jet Engine ◽  
Discrete Adjoint ◽  
Active Design ◽  
Fan Blade ◽  
Adjoint Gradient ◽  
Real Test

Abstract A Multi-point Approximation Method (MAM) coupled with adjoint is presented to increase the efficiency of a modern jet-engine fan blade. The study performed makes use of Rolls-Royce in-house suite of codes and its discrete adjoint capability. The adjoint gradient is used along with MAM to create a Design Of Experiment to enhance the optimization process. A generalized Free-Form Deformation (FFD) technique is used to parametrize the geometry, creating a design space of 180 parameters. The resulting optimum blade at design conditions is then evaluated at off-design conditions to produce the characteristic curve, which is compared with real test data. Finally, a preliminary Active Design Subspace (ADS) representing the fan efficiency is created to evaluate the robustness of the objective function in respect to the most significant design parameters. The ADS allows to collapse a large design space of the order of hundreds parameters to the few most important variables, measuring their contribution. This map is valuable in many respects to the fan designers and manufacture engineers to identify any ridges where the performance may deteriorate rapidly, hence a more robust part of the design space can easily be visualized and identified.

Numerical Simulation of Bird Strike Damage on Jet Engine Fan Blade

2004 ◽  
Author(s):  
Kazuo Shimamura ◽  
Tadashi Shibue ◽  
Donald J. Grosch
Keyword(s):  
Numerical Simulation ◽  
Impact Force ◽  
Bird Strike ◽  
Soft Body ◽  
Jet Engine ◽  
Fan Blade ◽  
The Impact ◽  
Interaction Problem ◽  
Numerical Simulation Technique ◽  
Good Agreement

Aircraft jet engine should be designed to keep the required performance against for the event of foreign object ingestion, such as bird-strike. For the purpose to realize highly efficient and more advanced design of fan blade of jet engine, a numerical simulation technique for bird-strike problem has developed. Good agreement was obtained between simulation results and the soft body impact tests described in this paper. It was also shown that bird-strike problem has to be recognized as a fluid-structure interaction problem, because the impacted bird behaves like fluid and the impact force is highly influenced by the deformation of fan blade.

Structural ultimate strength analysis of a first stage fan blade in a turbine jet engine RD-33

2016 ◽  
Vol 232 (1) ◽  
pp. 77-84 ◽  
Author(s):  
Adam Kozakiewicz ◽  
Stanisław Kachel ◽  
Stanisław Jóźwiak ◽  
Przemysław Jóźwiak
Keyword(s):  
Ultimate Strength ◽  
Strength Properties ◽  
Raw Material ◽  
Strength Analysis ◽  
Material Structure ◽  
Jet Engine ◽  
Emergency Situations ◽  
Typical Material ◽  
Fan Blade ◽  
Material Conditions

Statistical data clearly points out compressor train outage as one of the main reasons for the breakdown of aircraft power units. Outages are caused by various factors, including material conditions as the main one. Therefore, structural ultimate strength analysis of constructional raw material properties used in the production process of such an important part of an engine is not only of tremendous significance during the designing phase but also in a research phase and expertise associated with emergency situations. Considering the above-mentioned factors the article presents the outcomes of chemical composition, morphology, and phase structure of metallic material used to produce first row fan blades of RD-33 turbine jet engine, which is (currently) used by the Polish Air Force. Apart from typical material structure analysis, also the basic mechanical strength properties of materials have been determined including hardness, tensile, and impact tests. These may now constitute the basis for the analysis of substitute materials selection allowing the production of analyzed engine part.

scholarly journals Global Optimisation of a Transonic Fan Blade Through AI-Enabled Active Subspaces

2021 ◽  
pp. 1-33
Author(s):  
Diego Lopez ◽  
Tiziano Ghisu ◽  
Shahrokh Shahpar
Keyword(s):  
Pressure Ratio ◽  
Computational Cost ◽  
High Dimensional ◽  
Jet Engine ◽  
Cfd Models ◽  
Active Subspaces ◽  
Fan Blade ◽  
Novel Strategy ◽  
Optimisation Methods ◽  
Transonic Fan

Abstract The increased need to design higher performing aerodynamic shapes has led to design optimisation cycles requiring high-fidelity CFD models and high-dimensional parametrisation schemes. The computational cost of employing global search algorithms on such scenarios has typically been prohibitive for most academic and industrial environments. In this paper, a novel strategy is presented that leverages the capabilities of Artificial Neural Networks for regressing complex unstructured data, while coupling them with dimensionality reduction algorithms. This approach enables employing global-based optimisation methods on high-dimensional applications through a reduced computational cost. This methodology is demonstrated on the efficiency optimisation of a modern jet engine fan blade with constrained pressure ratio. The outcome is compared against a state-of-the-art adjoint-based approach. Results indicate the strategy proposed achieves comparable improvements to its adjoint counterpart with a reduced computational cost, and can scale better to multi-objective optimisation applications.

Jet Engine Design Optimization Using a Knowledge-Based Master Model

2012 ◽  
Author(s):  
Ilya Tyapin ◽  
Marcus Sandberg ◽  
Michael Kokkolaras ◽  
Anders Lundbladh ◽  
Ola Isaksson
Keyword(s):  
Objective Function ◽  
Design Optimization ◽  
Structural Characteristics ◽  
Problem Formulation ◽  
Performance Model ◽  
Structural Deformation ◽  
Jet Engine ◽  
Knowledge Based ◽  
Loading Case ◽  
Fan Blade

This paper presents a preliminary design optimization study of a jet engine structure using a knowledge-based master modeling approach. The objective function is derived based on input-output relationships of a cost-performance model, where specific fuel consumption, pressure loss and direct cost are considered. The advantage of this problem formulation is that it entails a single composite objective function that takes into account mass, structural characteristics, dynamic response and translates them to a direct operational cost function to be minimized. A fan-blade-off scenario is considered as the loading case in this paper. The loss of one fan blade during nominal operation causes a rotor imbalance and structural deformation.

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