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.

Evaluation of adhesive failure cases of L joint structures under tensile loading

2018 ◽  
Vol 32 (19) ◽  
pp. 1840058
Author(s):  
Do-Hoon Shin ◽  
Dong-Keun Hyun ◽  
Yun-Hae Kim
Keyword(s):  
Low Cost ◽  
Fuel Efficiency ◽  
Tensile Loading ◽  
Failure Strength ◽  
Adhesive Failure ◽  
Manufacturing Method ◽  
High Fuel Efficiency ◽  
Wide Range ◽  
Temperature Time ◽  
Secondary Bonding

In aerospace, aircraft weight is one of the important factors essential for long range and high fuel efficiency. Instead of fastening, bonding methods like co-curing, co-bonding and secondary bonding are used on the aircraft parts. Secondary bonding was developed for integrated parts because of easy handling, less defect ratio and low cost. During manufacturing, the integrated parts using secondary bonding, bonding strength can show a wide range of failure strengths. Due to inconstant failure strength, the design value can be dropped and reinforcement methods should be applied. To avoid over-designing and to get a constant value for failure, the adhesive failure cases are studied in this project. In this study, L joining composite parts are investigated under tensile loading. Different conditions are tested to select a suitable manufacturing method for secondary bonding methods. From the experimental results, the secondary bonding was sensitive at exposed temperature/time and shape conditions of the fillet. The results show that the failure strength depends on the shape of fillet and exposed time for curing.

Design of a Nonlinear Adaptive Controller for an Electrohydraulic Actuator1

1998 ◽  
Vol 123 (3) ◽  
pp. 449-456 ◽  
Author(s):  
K. Ziaei ◽  
N. Sepehri
Keyword(s):  
Low Cost ◽  
Dead Zone ◽  
Flow Characteristics ◽  
Adaptive Controller ◽  
Recursive Least Squares ◽  
Plant Model ◽  
Low Performance ◽  
Improved Performance ◽  
And Performance ◽  
Model Reference Adaptive

This paper presents a new implementation of indirect model reference adaptive (MRA) control scheme for positioning of hydraulic actuators that operate by low-cost proportional valves. A proper linear discrete-time plant model is used which has dead-time and no zeros, eliminating the possibility of unstable pole-zero cancellation. The robustness of the parameter adaptation is achieved by employing the recursive least-squares algorithm in combination with a dead-zone in the adaptive law. It is shown that while the controller is adequate for hydraulic valves with linear flow characteristics, it exhibits low performance in the presence of deadband and nonlinear orifice opening characteristics of low-cost proportional valves. The linear plant model is therefore augmented by adding a static nonlinearity. The resulting nonlinear MRA controller is shown to have improved performance over its linear counterpart. Step-by-step experiments are presented to confirm the effectiveness and performance improvement of the proposed method.

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.

Automated System for Fleet Benchmarking and Assessment of Technical Condition

2017 ◽  
Author(s):  
Brage Mo ◽  
Petter Dehli ◽  
Christian Steinebach ◽  
Tow Foong Lim ◽  
Lokukaluge P. Perera
Keyword(s):  
Business Processes ◽  
Fuel Efficiency ◽  
Power Production ◽  
Condition Index ◽  
Technical Condition ◽  
Automated System ◽  
High Fuel Efficiency ◽  
Performance Reports ◽  
Cost Efficient ◽  
And Performance

On-board Energy systems in vessels have to use fuel efficiently to maintain ship speed at lowest possible costs. This paper describes how to use ship operational data to improve and maintain efficiency of the vessel’s power production with respect to the condition and performance of equipment. The paper describes an overview of an automated Technical Operations Performance (TOP) Monitoring service. TOP monitors the performance of marine main and auxiliary diesel engines by use of the information collected onboard vessels at regular intervals. Performance data are stored in xml-reports sent as email attachments from ship to shore. This communication is reliable and cost efficient for merchant ships that are on-line only for shorter periods. Load, ISO and environmental corrections make results valid for benchmarking and trending. The service aggregates the hierarchical information obtained from different sources by transferring measurement readings into unified indicators, the Technical Condition Index (TCI) [1]. Experts manually check the automatically generated performance reports and add additional guidance on options to improve power production and machinery conditions analyzing the available data with respect to different targets, such as low engine degradation and high fuel efficiency. The performance reports then influence business processes indicating possible causes for loss of performance in equipment and possible erroneous instrumentation, and the need for maintenance actions. The obtained TCI values show the performance of individual units, or for a fleet/class of equipment and vessels.

Interactive Cycle Analysis

1986 ◽  
Author(s):  
B. A. Anderson ◽  
P. J. Trenkamp
Keyword(s):  
Performance Optimization ◽  
Low Cost ◽  
Aircraft Engine ◽  
User Input ◽  
Cycle System ◽  
Time Logic ◽  
And Performance ◽  
Analysis System ◽  
Component Map ◽  
User Friendly

A new Interactive Cycle System has been developed by General Electric’s Aircraft Engine Business Group for the cycle analysis and performance optimization of conceptual and preliminary engine designs. This paper will explore some of the considerations in moving from a large, well-known, batch, detailed design, modeling system to a low-cost, flexible, responsive, user-friendly, interactive cycle analysis system. The resulting system utilizes menu screens for user input and data review, a modular program structure with stacking of modules to achieve the desired engine configuration, a library of component characteristics augmented by parametric component map generators, and an interpretive reader to permit real-time logic creation without the need for compiling.

Modeling the Flow of Molten Silicon in Porous Carbon Preforms and the Subsequent Formation of Silicon Carbide

1994 ◽  
Vol 365 ◽  
Author(s):  
G. Rajesh ◽  
Ram B. Bhagat ◽  
Emily Nelson
Keyword(s):  
Silicon Carbide ◽  
High Performance ◽  
Space Shuttle ◽  
Low Cost ◽  
Fuel Efficiency ◽  
Ceramic Matrix Composites ◽  
Aircraft Engine ◽  
Molten Silicon ◽  
Subsequent Formation ◽  
Silicon Based

Ceramic matrix composites (CMCs) are being considered for a broad range of aerospace applications that include various structural components for the aircraft engine and the space shuttle main engine. Use of silicon-based CMCs which have high thermal conductivity, allows for improvements in fuel efficiency due to increased engine temperatures and pressures, which in turn generate more power and thrust. Furthermore, CMCs offer significant potential for raising the thrust-to-weight of gas turbine engines by tailoring directions of high specific reliability using design-based fiber architecture. One of the low-cost processing techniques for the silicon-based CMCs is the reactive melt infiltration [1] of silicon into the preform of carbon-coated silicon carbide fiber. However, fabrication of high performance SiC/SiC composites requires a deeper understanding of the infiltration kinetics such that fibers are protected from adverse reaction with the molten metal, that the preform is thoroughly infiltrated, and that there is no residual silicon left unreacted.

AeroEngineS: Multi-Platform Application for Aero Engine Simulation and Compressor Map Operating Point Prediction

2019 ◽  
Author(s):  
Evangelia C. Pontika ◽  
Anestis I. Kalfas ◽  
Ioanna Aslanidou
Keyword(s):  
Gas Turbine ◽  
Thermodynamic Cycle ◽  
Aircraft Engine ◽  
Design Tool ◽  
Operating Conditions ◽  
Operating Point ◽  
Engine Simulation ◽  
Aero Engine ◽  
Compressor Map ◽  
User Friendly

Abstract This paper presents the development of AeroEngineS (Aircraft Engine Simulation), a multi-platform app with graphical user interface for aero engine simulation and compressor map operating point prediction. Gas turbine performance simulation is a crucial part of the design process. It provides information about the required operating conditions of all the components and the overall performance of the engine so that engineers can determine whether the current engine configuration meets the performance requirements. Some gas turbine simulation programs have been developed in the last decades, however, there was a lack of an open-source, lightweight, user-friendly, but still very accurate, application which would be easily accessible from all platforms. AeroEngineS can be used as a user-friendly preliminary design tool, since, during this design phase, details about the geometry are not known yet. The main aim is to calculate simply and quickly the basic parameters of the thermodynamic cycle and the performance, in order to determine which design is able to meet the required specifications. AeroEngineS constitutes a free and simple app which can primarily serve educational purposes as it is easily accessible by students from any platform to assist them in aero engine technology courses. Secondarily, it has the potential to be used even by engineers as a quick tool accessible from all devices. The app consists of two basic stand-alone functions. The first function is aero engine simulation at Design Point which solves thermodynamic calculations. The second function is compressor map operating point prediction using a novel method of combining scaling techniques and Artificial Neural Networks.

Mechanical Design of a Low Cost Transhumeral Prosthesis

2017 ◽  
Author(s):  
Luis Arturo Gómez Malagón ◽  
João Luiz Vilar Dias
Keyword(s):  
Mechanical Design ◽  
Low Cost

Programmable Integrated Photonics

2020 ◽  
Author(s):  
José Capmany ◽  
Daniel Pérez
Keyword(s):  
Integrated Circuit ◽  
Performance Monitoring ◽  
Low Cost ◽  
Limiting Factors ◽  
External Control ◽  
Integrated Photonics ◽  
New Paradigm ◽  
Photonic Integrated Circuit ◽  
And Performance ◽  
Application Fields

Programmable Integrated Photonics (PIP) is a new paradigm that aims at designing common integrated optical hardware configurations, which by suitable programming can implement a variety of functionalities that, in turn, can be exploited as basic operations in many application fields. Programmability enables by means of external control signals both chip reconfiguration for multifunction operation as well as chip stabilization against non-ideal operation due to fluctuations in environmental conditions and fabrication errors. Programming also allows activating parts of the chip, which are not essential for the implementation of a given functionality but can be of help in reducing noise levels through the diversion of undesired reflections. After some years where the Application Specific Photonic Integrated Circuit (ASPIC) paradigm has completely dominated the field of integrated optics, there is an increasing interest in PIP justified by the surge of a number of emerging applications that are and will be calling for true flexibility, reconfigurability as well as low-cost, compact and low-power consuming devices. This book aims to provide a comprehensive introduction to this emergent field covering aspects that range from the basic aspects of technologies and building photonic component blocks to the design alternatives and principles of complex programmable photonics circuits, their limiting factors, techniques for characterization and performance monitoring/control and their salient applications both in the classical as well as in the quantum information fields. The book concentrates and focuses mainly on the distinctive features of programmable photonics as compared to more traditional ASPIC approaches.

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