Design And Analysis Of Composite High Pressure Vessel With . - IJERT
International Journal of Engineering Research & Technology (IJERT)ISSN: 2278-0181Vol. 3 Issue 11, November-2014Design and Analysis of Composite High Pressure Vesselwith Different Layers using FEASubhash N. Khetre1P. T. Nitnaware212P.G. Scholar, Mechanical Department,Alard College of Engg. & Management,Marunje, PuneSavitribai Phule Pune University,Pune (India)Assistant professor,Mechanical Department, D Y PATILCollege of Engineering, Akurdi, PuneSavitribai Phule Pune University,Pune (India)Arun Meshram33Assistant professor, Mechanical Department,Rajarshi Shahu College of Engineering,Tathawade, PuneSavitribai Phule Pune University,Pune (India)Composite pressure vessels tend to fail in their composite pressurevessels parts; the design of these parts is the most important issue forsuch vessels [32]. A number of factors must be taken into account indesigning composite pressure vessels, including the strength of thematerials selected, the effect of winding stability, geometricvariables, and so on. The winding stability and composite pressurevessels shapes must be chosen carefully to obtain an optimal design[15]. Several previous studies have examined the optimal design ofcomposite pressure vessels, but the effects caused by the width of thewinding Layers on the stability of winding pattern in the compositepressure vessels have not been studied. Therefore, the aim of thisstudy is to optimize the design of composite vessels operating underan internal pressure [16].The design variables used in the optimization problem include thewinding angle. The effects of winding process parameters on theslippage tendency at the edges of the band are also considered. Theresults presented may prove to be helpful for designers of compositepressure vessels. In addition, the procedure employed in this studycan also be utilized during the primary design stage. All Compositeoverwrapped pressure vessels (COPV’s) are made of a thin metallicliner wrapped with a high-strength low-density composite.[8] Themetallic liner provides shape, toughness, tightness and interface withthe gas feeding systems while the overwrapped composite ensuresmechanical strength to withstand high pressures and protects thevessel against scratches, indents and other forms of impact damage.Other examples of pressure vessels are fuel tanks, rocket motor cases,diving cylinders, recompression chambers, distillation towers,pressure reactors, autoclaves, vessels in mining operations, oilrefineries and petrochemical plants, nuclear reactor vessels,submarine and space ship habitats, Pneumatic reservoir, hydraulicreservoir under pressure, rail vehicle airbrake, reservoirs, roadvehicle airbrake, reservoirs and storage vessels for liquefied gasessuch as ammonia, chlorine, propane, butane, and LPG. [31]IJERTAbstract—the composite Material like aluminium and fibermatrix to sustain different criteria. In the present work, structureof the composite pressure vessel and different orientations ofsymmetric shells designed. For pressure were investigated and 3D finite element analyses using APDL Programming. FEAsoftware is used for failure analysis on the composite shell ofcontinuous angle ply laminas. The Tsai-Wu failure criterion isapplied for the checking the first-ply failure of layers in a simpleform. Some analytical and experimental solutions are comparedwith the finite element solutions, in which commercial softwareANSYS 15.0 was utilized and close results are obtained betweenthem.Key words: Non Linear FEA, Partial differential equation, StressConcentration Criteria, Failure Criterion T-Sai WuI.INTRODUCTION:In many applications in mechanical engineering [1-6] a compositecomponent must sustain for many years, stress levels that are asignificant fraction of its ultimate tensile strength, and often indeleterious environments. Various applications in pressure vessels inaerospace, automotive and nuclear power. A generally recognizedproblem is creep fracture, a catastrophic failure event that typicallyoccurs with little or no warning [6]. However, due to the lack ofthrough-the-thickness reinforcement, structures made from thesematerials are highly liable to failures caused by delamination.Therefore within a design process a structures resistance todelamination should be addressed to maximize its durability anddamage tolerance. The phenomenon of progressive failure inlaminated composite structures is yet to be understood, and as aresult, reliable strategies for designing optimal composite structuresfor desired life and strength are in demand [33].Various methods,utilizing analytical and experimental approaches, have been presentedfor designing the composite pressure vessels shapes of pressurevessels [27]. During the past two decades, several authors haveperformed detailed analyses of composite pressure vessels by usingthe theory of orthotropic plates.IJERTV3IS111412II.OBJECTIVE OF PROJECT:The objective of the project is to:a. Design of pressure vessel for operating 0.34 MPa as perASME Code section VIII.b. Analysis of composite pressure vessel using FEA.www.ijert.org(This work is licensed under a Creative Commons Attribution 4.0 International License.)1460
International Journal of Engineering Research & Technology (IJERT)ISSN: 2278-0181Vol. 3 Issue 11, November-2014c.To check at how many layers composite pressure vesselfails using T-Sai Wu failure criteria.A finite-element simulation of a composite pressure vessel isperformed first to gain insight into its mechanical behaviors, and thensimulation results are processed using failure analysis to determine atwhich layer composite pressure vessel fails when winding layersdecreases from 20-Layers to 5-Layers.Unidirectional lamina a single lamina (also called layer or ply) orseveral lamina (plural) with same material and orientation in alllaminate and bonded together, where at least some lamina havedifferent orientation or material.[37] Bulk composite for whichlamina cannot be identified including bulk molding compoundcomposite particle- reinforced composite and so on.C. Composite Pressure vessels design:Design according to T-Sai Wu failure criteria as given below. 3 A BAnd if the criteria used is the inverse of strength index 3 Where 3 is the value of T Sai Wu failure criteria.A Fig. 2.1 Laminated Composite MaterialIII. 1 B DESIGN AND ANALYSIS OF COMPOSITEPRESSURE VESSEL USING ANSYS: 3A.,,are coupling coefficients of T Sai WuWheretheory.3.4 APDL Programming of Composite Pressure vesselsUsing ANSYS 15.0:/prep7/title!--- define parameters --ce1 161.3e9 ! E11ce2 8.82e9 ! E22theta 45! Layer orientation anglesrenf .5e-4 ! Cross-section area of a single reinforcing fiber.s 1.0! Distance between two adjacent reinforcingfibersp 50.e5! Internal pressurepi 3.1415926535897932384626433832795/prep7!--- element type --et,1,SHELL281! 8-Node Structural Shellkeyopt,1,2,1 ! Use the improved shell optionkeyopt,1,8,1 ! Store all layer results!--- materials--! ! Matrixmp,ex,2,ce2mp,prxy,2,0.33mp,alpx,2,5e-6! -composite lay-up of the main wall--sectype,1,shellsecdata,1.9e-3,1,,5!Aluminum linersecdata,0.1e-3,2,,5!1st matrix section EpoxyIJERTComposite Pressure vessels Equipment Design Data:The mechanical properties of the liner are aluminium andfiber matrix in composite filament winding using ASME Code-IIIand Stiffness, toughness as follows:Table IProperties of carbon FibersSr.MechanicalNominal Value (SI)No1E11 - Longitudinal161.3 GPa2E22 – Transverse8.82 GPa3Shear Modulus5.14 GPa(G12 - In-Plane)4Poisson's Ratio0.300(ν12 - In-Plane) 2 B. Composite Pressure vessels material of construction:The composite material depends upon following parametersof material like strength, hardness, ductility, Creep resistance,corrosion factors. The fiber matrix always use in one dimensional.Table IIConfiguration of matrix and Aluminium IDOrientationPointsessAngle1.9e-3103Main outlet1.9e-3103wallThe fibers have a one-dimensional constitutive relation and aresignificantly stiffer than the bonding material. For simplicity, it isassumed that all materials in this problem are linear-elastic andtemperature independent.IJERTV3IS111412www.ijert.org(This work is licensed under a Creative Commons Attribution 4.0 International License.)1461
International Journal of Engineering Research & Technology (IJERT)ISSN: 2278-0181Vol. 3 Issue 11, ffset,bot!---reinforcing fibers--sectype,2,reinf,smearsecdata,3,srenf,s,, a,3,srenf,s,, a,3,srenf,s,, a,3,srenf,s,, botcsys,0IV.!2nd matrix section Epoxy!3rd matrix section Epoxy!4ht matrix section Epoxy!5ht matrix section Epoxy!6ht matrix section Epoxy!7ht matrix section Epoxy!8ht matrix section Epoxy!reinforce section for layer #1!reinforce section for layer #2!reinforce section for layer #3!reinforce section for layer #4!reinforce section for layer #5!reinforce section for layer #6!reinforce section for layer #7!reinforce section for layer #8Fig. 4.2 Von-misses stress at 6-Layers.For Layer-6 inverse of T Sai Wu strengthRatio index 1.02064.ANALYSIS OF ONE/EIGHT PART OFCOMPOSITE PRESSURE VESSELS FORPRESSURE 0.34 MPa:For Layer 6- deformation 0.054661IJERTThe failure analysis is applied to calculation which addresses theT-Sai Wu Criteria, static analysis and displacement analysis.during the analysis, ANSYS 15.0 is used and analysis is carriedout in the different steps. The purpose of analysis is to insuresafety of the composite pressure vessels and supporting structure.Sustained loads are by using operating pressure conditions.Fig. 4.3 Inverse of T Sai Wu strength ratioIndex at 6-Layers.For Layer -8 Deformation 0.052663Fig. 4.1 Deformations at 6-Layers.For Layer 6- von misses stress 0.198E10 N/m2Fig. 4.4 Deformation at 8-Layers.IJERTV3IS111412www.ijert.org(This work is licensed under a Creative Commons Attribution 4.0 International License.)1462
International Journal of Engineering Research & Technology (IJERT)ISSN: 2278-0181Vol. 3 Issue 11, November-2014For Layer-8 von misses 0.186E10 N/m2Graph 5.1 Graph of no of layers Vs Inverse ofT-Sai strength indexIn analysis we increase layers from 5 to 20. From graph structurefails at 6-Layer and 7-Layer (inverse of T Sai strength index is1.02064 & 1.008156) but as we add 8-Layer on pressure vessel itsstrength increased (inverse of T Sai strength index is 0.988183).Fig. 4.5 Von-misses stress at 8-Layers.For Layer-8 inverse of T Sai Wu strengthRatio index 0.988183.VI.CONCLUSIONIJERTAnalyses are carried out for number of layer from 5-Layer to 20Layer. But here Results are noted between Layer 8 to Layer 5 inTable 5.1, we can reduce number of layers to obtain optimizeddesign. At 8-Layers value is 0.988180 structure is safe and is atoptimum level. At 7-Layer its value is 1.00815 i.e. fails, which ismatches with the value of test results. Therefore we can conclude thatT-Sai Wu failure criteria can yield fairly good results with consistentaccuracy for the composite pressure vessels.ACKNOWLEDGEMENT:I gratefully acknowledge Mechanical engineering department ofAlard COE&M, Pune for technical support and providing theresearch facilities. I would also like to thank to Dr. S. B. Padwal,Principal (Alard COE&M, Pune) and Prof. V. R. Bajaj HOD(Mechanical department) for their help and dedication toward myresearch and related research, also my friends for their directly &indirectly help, support and excellent co-operation.Fig. 4.6 Inverse of T Sai Wu strength ratioIndex at 8-Layers.V.VII.RESULTS AND DISCUSSIONAnalysis is carried out from Number of Layer-5 to 20-Layer. Buthere Results are noted down between Layer 8 to Layer 5 in belowTable-III The total analysis and modeling APDL, designprocedure, learning and training time is includingapproximately seventy-four hours taken by the software,Project work.Table IIIDeformation and Inverse Tsai strength indexNo. .0546610.0536210.0526630.214 E 100.198 E 100.193 E 100.186 E 10Inverse T-Sai Wustrength 01.0206401.0081560.988180It is observed that during analysis, Failure occurs in compositepressure vessels by using T-Sai Wu Criteria. When value of inverseof T-Sai Wu strength ratio index is greater is than one than compositepressure vessel fails.IJERTV3IS111412www.ijert.org(This work is licensed under a Creative Commons Attribution 4.0 International License.)1463
International Journal of Engineering Research & Technology (IJERT)ISSN: 2278-0181Vol. 3 Issue 11, th of delamination.Normalized delamination length.E11, E22, G12, m12Gt1, t2Material constants.Strain energy release rate.Thicknessesofupperandlowersublaminates, respectively.Normalized delamination thickness.h t1/tL, r, tLength, Radius And Thickness Of TheOverall cylindrical shell, respectively.X, Y, ZNodal Force Components In The X, Y AndZ.PPressure.PcCritical Buckling Pressure Of An IntactCylinder Under External Pressure Alone.PcrCritical Buckling Pressure Of A DelaminateCylinder.Compressive axial load.RCritical axial compression of an intactRccylinder under axial compressive alone.Critical axial compression of a ialu(or ux), v(ordisplacements, respectively.uy), w(or uz)Axial, circumferential and radial coordinates,x, y, zrespectively.Angle of the delamination region. underwater vehicle applications. Composite Structures 2010;92 : 2241–2251[22] H.S. da Costa Mattos.Analysis of burst tests and long-termhydrostatic tests in produced water pipelines. EngineeringFailure Analysis 2012; 22: 128–140[23] Hashin Z. Failure criteria for unidirectional fiber composites. JAppl Mech 1980; 47:329–34.[24] Tsai SW. A survey of macroscopic failure criteria forcomposite materials. Journal of Reinforced Plastics andComposites 1984; 3(1):40–62.[25] Alves LM, Silva MB, Martins PAF. Fabrication of small sizeseamless reservoirs by tube forming. International Journal ofPressure Vessels and Piping 2011;88: 239-47.[26] P.B. Gning, M. Tarfaoui.Damage development in thickcomposite tubes under impact loading and influence onimplosion pressure: experimental observations. Composites:Part B 36 (2005) 306–318[27] Song Lin, Xiao long Jia. Thermo-mechanical properties offilament wound CFRP vessel under hydraulic and atmosphericfatigue cycling. Composites: Part B 2013; 46: 227–233[28] Nahas MN. Survey of failure and post-failure theories oflaminated fiber reinforced composites. Journal of CompositesTechnology and Research 1986; 8(4):138–53.[29] Sleight DW. Progressive failure analysis methodology forlaminated composite structures. NASA Report 1999;4:8–63.[30] Cox B, Yang QD. Cohesive models for damage evolution inlaminated composites. International Journal of Fracture 2005;133(2):107–37.[31] Rami HA. Cohesive micromechanics: a new approach forprogressive damage modeling in laminated composites.International Journal of Damage Mechanics 2009;18(8):691–719.[32] Chang RR. Experimental and theoretical analyses of first-plyfailure of laminated composite pressure vessels. CompositeStructures 2000; 49(2):237–43.[33] Lapczyk I, Hurtado JA. Progressive damage modeling in fiberreinforced materials. Composites A: Applied Science andManufacturing 2007; 38(11):2333–41.IJERT[1] Vasiliev V, Krinakov AA, Razin AF. New generation offilament–wound composite pressure vessels for commercialapplications. Composite Structure 2003; 62:449–59.[2] Azam Tafreshi, Delamination buckling and post buckling incomposite cylindrical shells under combined axial compressionand external pressure. Composite Structures 2006; 72: PP 401–418.[3] Verijenko EV, Adali S, Tabakov PY. Stress distribution incontinuously heterogeneous thick laminated pressure vessels.Composite Structures 2001; 54:371–7.[4] E. Frulloni, J.M. Kenny. Experimental study and finite elementanalysis of the elastic instability of composite lattice structuresfor aeronautic applications. Composite Structures 2007;78:519–528[5] Azam Tafreshi, Colin G. Bailey. Instability of imperfectcomposite cylindrical shells under combined loading.Composite Structures 2007; 80:49–64[6] Myung-Gon Kim , Sang-Guk Kang. Thermally induced stressanalysis of composite/aluminum ring specimens at cryogenictemperature. Composites Science and Technology 2008; 68:1080–1087[7] Varga L, Nagy A, Kovacs A. Design of CNG tank made ofaluminium and reinforced plastic. Composites 1995; 26:457–63.[8] P.B. Gning, M. Tarfaoui, Damage development in thickcomposite tubes under impact loading and influence onimplosion pressure. Composites: Part -B 362005; 36:306–318[9] Zheng JY, Liu PF. Elasto-plastic stress analysis and burststrength evaluation of Al-carbon fiber/epoxy compositecylindrical laminates. Computational Materials Science 2008;42(3):453–61.[10] Parnas L, Katrice N. Design of fiber-reinforced compositepressure vessels under various loading conditions. CompositeStructures 2002; 58:83–95.[11] Tutuncu N, Winckler SJ. Stresses and deformations in thickwalled cylinders subjected to combined loading andtemperature gradient. Journal of Reinforced Plastic andComposite 1993; 12(2):198–209.[12] Chapelle D, Perreux D. Optimal design of a type 3 hydrogenvessel: part Idanalytic modelling of the cylindrical section.International Journal of Hydrogen Energy 2006; 31:627–38.[13] Yang FQ, Zhang TP, Liu ZD, Wang XY. Finite elementmodeling and buckling analysis of COPV. Vacuum andCryogenics 2005;11(1):40–5 [in Chinese].[14] Chen RX. Design analysis on the filament-wound gas cylinder.Journal of Solid Rocket Technology 2008;31(6):625–34 [inChinese].[15] Lifshitz JM, Dayan H. Filament-wound pressure vessel withthick metal liner. Composite Structures 1995;32(1–4):313–23.[16] Parnas L, Katirci N. Design of fiber-reinforced compositepressure vessels under various loading conditions. CompositeStructures 2002; 58(1): 83–95.[17] Chapelle D, Perreux D. Optimal design of a Type 3 hydrogenvessel. Part I. Analytic modeling of the cylindrical section.International Journal of Hydrogen Energy 2006;31(5):627–38.[18] Tsai SW. Composite s design.USA, Think Composites, 1985.[19] Hinton MJ, Soden PD. Predicting failure in compositelaminates: the background to the exercise. Composites Scienceand Technology 1998;58(7):1001–10[20] Shigley, Mischke & Budynas. Machine Design, PressureVessel Design.[21] Chul-Jin Moon, In-Hoon Kim. Buckling of filament-woundcomposite cylinders subjected to hydrostatic pressure forAbbreviationAa a/LIJERTV3IS111412www.ijert.org(This work is licensed under a Creative Commons Attribution 4.0 International License.)1464
for designing the composite pressure vessels shapes of pressure vessels [27]. During the past two decades, several authors have performed detailed analyses of composite pressure vessels by using the theory of orthotropic plates. Composite pressure vessels tend to fail in their composite pressure vessels parts; the design of these parts is the .
Types of composite: A) Based on curing mechanism: 1- Chemically activated composite 2- Light activated composite B) Based on size of filler particles: 1 - Conventional composite 2- Small particles composite 3-Micro filled composite 4- Hybrid composite 1- Chemically activated, composite resins: This is two - paste system:
78 composite materials Composite materials resources. Composite Materials Resources scouting literature Chemistry, Engineering, Inventing, Model Design and Building, Robotics, and Space Exploration merit badge pamphlets Books Marshall, Andrew C. Composite Basics, 7th ed. Marshall Consulting Publishing, 2005. Rutan, Burt. Moldless Composite
Composite 3 19 57 37. Prime 38. Prime 39. Neither 40. Neither 41. Composite 11 11 121 42. Composite 3 23 69 43. Prime 44. Prime 45. Composite 3 13 39 46. Composite 7 7 49 47. There are two whole numbers that are neither prime nor composite, 0 and 1. 48. False; the square of a
Federal Aviation Administration CE F, General Composite Structure Guidance Background –With the evolving/advancing composite technology and expanding composite applications, AC 20-107 “Composite Aircraft Structure” will require revision Deliverables –Revision to AC 20-107, “Composite Aircraft Structure,” to
Connecting the HDMI to Composite / S-Video Scaler 1. Connect the included HDMI cable from the Hi-Def source to the HDMI connector of the HDMI to Composite / S-Video Scaler. 2. Connect a Composite cable (RCA-type) between the HDMI to Composite / S-Video Scaler and the Composite input on the display or A/V receiver. Optionally connect an
(P 0.05). The packable composite -with or without fluid composite- showed lower microleakage, whereas microhybrid and fiber-reinforced composites without fluid composite, showed higher mi-croleakage. Discussion: The fluid composite significantly decreased the microleakage at gingival margins of Class II composite restorations.
Daily Math Practice D Math Buzz 093 Circle prime or composite. 13 prime composite 15 prime composite 22 prime composite 17 prime composite 23 prime composite Multiply. 6 x 728 _ 4 times as many as 397. _ 559 x 9 —–——
MaMa Internal Power Centers Mastering the Energy of Body & Mind A. Thomas Perhacs
