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Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721636532
Category :
Languages : en
Pages : 32
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Book Description
The aerodynamic and structural viability of composite fan blades of the revolutionary Exo-Skeletal engine are assessed for an advanced subsonic mission using the NASA EST/BEST computational simulation system. The Exo-Skeletal Engine (ESE) calls for the elimination of the shafts and disks completely from the engine center and the attachment of the rotor blades in spanwise compression to a rotating casing. The fan rotor overall adiabatic efficiency obtained from aerodynamic analysis is estimated at 91.6 percent. The flow is supersonic near the blade leading edge but quickly transitions into a subsonic flow without any turbulent boundary layer separation on the blade. The structural evaluation of the composite fan blade indicates that the blade would buckle at a rotor speed that is 3.5 times the design speed of 2000 rpm. The progressive damage analysis of the composite fan blade shows that ply damage is initiated at a speed of 4870 rpm while blade fracture takes place at 7640 rpm. This paper describes and discusses the results for the composite blade that are obtained from aerodynamic, displacement, stress, buckling, modal, and progressive damage analyses. It will be demonstrated that a computational simulation capability is readily available to evaluate new and revolutionary technology such as the ESE. Abumeri, Galib H. and Kuguoglu, Latife H. and Chamis, Christos C. Glenn Research Center NASA/TM-2004-212943, E-14383
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781721636532
Category :
Languages : en
Pages : 32
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Book Description
The aerodynamic and structural viability of composite fan blades of the revolutionary Exo-Skeletal engine are assessed for an advanced subsonic mission using the NASA EST/BEST computational simulation system. The Exo-Skeletal Engine (ESE) calls for the elimination of the shafts and disks completely from the engine center and the attachment of the rotor blades in spanwise compression to a rotating casing. The fan rotor overall adiabatic efficiency obtained from aerodynamic analysis is estimated at 91.6 percent. The flow is supersonic near the blade leading edge but quickly transitions into a subsonic flow without any turbulent boundary layer separation on the blade. The structural evaluation of the composite fan blade indicates that the blade would buckle at a rotor speed that is 3.5 times the design speed of 2000 rpm. The progressive damage analysis of the composite fan blade shows that ply damage is initiated at a speed of 4870 rpm while blade fracture takes place at 7640 rpm. This paper describes and discusses the results for the composite blade that are obtained from aerodynamic, displacement, stress, buckling, modal, and progressive damage analyses. It will be demonstrated that a computational simulation capability is readily available to evaluate new and revolutionary technology such as the ESE. Abumeri, Galib H. and Kuguoglu, Latife H. and Chamis, Christos C. Glenn Research Center NASA/TM-2004-212943, E-14383
Author: Norkhairunnisa Mazlan
Publisher: Springer Nature
ISBN: 303088192X
Category : Technology & Engineering
Languages : en
Pages : 517
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Book Description
This book presents an authoritative account of the potential of advanced composites such as composites, biocomposites, composites geopolymer, hybrid composites and hybrid biocomposites in aerospace application. It documents how in recent years, composite materials have grown in strength, stature, and significance to become a key material of enhanced scientific interest and resultant research into understanding their behavior for selection and safe use in a wide spectrum of technology-related applications. This collection highlights how their unique combination of superior properties such as low density, high strength, high elastic modulus, high hardness, high temperature capability, and excellent chemical and environmental stability are optimized in technologies within these field.
Author: Richard Ravenhall
Publisher:
ISBN:
Category :
Languages : en
Pages : 117
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Book Description
This report describes the results of an advanced composite-rotor mechanical-design-feasibility study program. Four advanced composite fan-rotor concepts and one composite reinforced compressor-rotor concept were evolved and evaluated during this study. One particular fan concept, titled 'pinned-blade/hoop rotor, ' received extended evaluation because it allowed the replacement of blades and showed a significant weight and cost advantages over the metal counterpart. This concept was applied to both a subsonic-flight engine and a supersonic-flight engine for potential future development. (Author).
Author: Tezeswi Tadepalli
Publisher: Springer Nature
ISBN: 9811695393
Category : Science
Languages : en
Pages : 743
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Book Description
This book comprises the proceedings of the Virtual Seminar on Applied Mechanics 2021 organized by the Indian Society for Applied Mechanics. The contents of this volume focus on solid mechanics, fluid mechanics, biomechanics/biomedical engineering, materials science and design engineering. The authors are experienced practitioners and the chapters encompass up-to-date research in the field of applied mechanics. This book will appeal to researchers and scholars across the broad spectrum of engineering involving the application of mechanics in civil, mechanical, aerospace, automobile, bio-medical, material science, and more.
Author: National Aeronautics and Space Administration (NASA)
Publisher: Createspace Independent Publishing Platform
ISBN: 9781719390224
Category :
Languages : en
Pages : 48
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Book Description
This report addresses the structural analysis and optimization of a composite fan blade sized for a large aircraft engine. An existing baseline solid metallic fan blade was used as a starting point to develop a hybrid honeycomb sandwich construction with a polymer matrix composite face sheet and honeycomb aluminum core replacing the original baseline solid metallic fan model made of titanium. The focus of this work is to design the sandwich composite blade with the optimum number of plies for the face sheet that will withstand the combined pressure and centrifugal loads while the constraints are satisfied and the baseline aerodynamic and geometric parameters are maintained. To satisfy the requirements, a sandwich construction for the blade is proposed with composite face sheets and a weak core made of honeycomb aluminum material. For aerodynamic considerations, the thickness of the core is optimized whereas the overall blade thickness is held fixed so as to not alter the original airfoil geometry. Weight is taken as the objective function to be minimized by varying the core thickness of the blade within specified upper and lower bounds. Constraints are imposed on radial displacement limitations and ply failure strength. From the optimum design, the minimum number of plies, which will not fail, is back-calculated. The ply lay-up of the blade is adjusted from the calculated number of plies and final structural analysis is performed. Analyses were carried out by utilizing the OpenMDAO Framework, developed at NASA Glenn Research Center combining optimization with structural assessment. Coroneos, Rula M. Glenn Research Center STRUCTURAL ANALYSIS; FAN BLADES; PRESSURE DISTRIBUTION; HONEYCOMB STRUCTURES; POLYMER MATRIX COMPOSITES; CENTRIFUGAL FORCE; ENGINE DESIGN; AIRFOIL PROFILES
Author: James H. Young
Publisher:
ISBN:
Category :
Languages : en
Pages : 281
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Book Description
The program objective was to develop the technology, advance the design concepts, and manufacture composite compressor blades. Volume II covers the testing of these blades and gives a design manual for composite gas turbine engine blades. (Author).
Author: North Atlantic Treaty Organization. Advisory Group for Aerospace Research and Development. Propulsion and Energetics Panel. Symposium
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 432
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Book Description
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 374
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Book Description
Author: David G. Randall
Publisher:
ISBN:
Category :
Languages : en
Pages : 368
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Book Description
The successful application of advanced composites as the structural material for aircraft jet engine rotating parts will significantly reduce engine weight and improve engine performance characteristics. To solve the component design, manufacturing, and quality assurance problems associated with such an application, a program was conducted to design and develop BORSIC/Aluminum third-stage fan blades, which would operate satisfactorily in the TF30-P-7 or P-9 engine models. Program objectives were to improve the existing design of a composite material fan blade, manufacture the blade, and demonstrate its quality by bench and engine environment testing. The scope of the program required to successfully meet these objectives included establishing design and fabrication procedures, developing special tooling, evaluating current nondestructive inspection techniques and adapting these techniques to composite materials, establishing quality assurance criteria, and developing comprehensive bench and engine environment test programs to adequately demonstrate fan-blade quality. During the program, several sets of BORSIC/Aluminum blades weighing 40 percent less than comparable TF30 bill of material titanium blades were successfully produced and tested. Based on this extensive test program, and with the establishment of quality control criteria and repair procedures, the blades were deemed acceptable for evaluation in a flight program. During the total program, 246 engine-configuration blades were manufactured and non-destructively inspected; with an overall acceptance rate of 92.3%.
Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 190
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Book Description
This report describes the results of a 20-month program, beginning in June 1974, designed to investigate parameters which effect the foreign object damage resulting from ingestion of birds into fan blades of a QOSEE-type engine. Work performed on this program included the design, fabrication, and impact testing of QOSEE fan blades to demonstrate improvement in FOD resistance relative to existing blades and also the design and demonstration of a pin root attachment concept. In the first phase of the program, it was found that, in general, for the small objects used, the strains in the blade are proportional to the mass of the impacting object and the square of the relative velocity component normal to the blade chord at the impact location. These parameters can be further combined into an average or nominal force normal to the blade at the impact location. A finite element computer program gave results that compare well with the test data. In the second phase of the program four improved blades exhibited substantial improvement in FOD resistance relative to former designs.
