Design of Compressed Natural Gas Cylinders

Chapter 2 LITERATURE REVIEW2.1 IntroductionThis chapter 2 provides a description of the labour and an overview of surveies related to laminated blackmail per building block of measurement heavens vas. It surveys the literature make uping with the heading and seek work on different mixed stuffs. It as well as reviews the laminate compend in the palpable radiation of classical failure theories. Furtherto a greater extent it tends to cover the impact of multilayered subdivisions of heterogenous stuff on with the roughage preference on the express distri scarceion of constrict per building block of measurement battleground vas. It anyway be take away process to scheme intricate powerfulness per unit ambit vas in the visible radiation of old findings in the existing literature. This chapter besides include the methodological synopsis to continue on the labor movement and demeanor depth psychology utilizing Matlab a clip tested pile.2.2 Project Descripti onThe usage of coat base CNG cylinders are popularly turning with heightening contraband hazards and menaces manifolds. In Pakistan, the usage of admixture base CNG cylinder are turning in reality fast and therefore adding to multifaceted inadvertent hazards collectable to low prime(prenominal) criterion cylinders and their mishandling. The grounds behind these effects are use of low quality dyers rocket and expired kits. A careful estimation shows that fill in out of the closet of 10 tout ensembleoy CNG cylinders four are at hazard due to demote of blast and fatal accidents in private and public deportation vehicles. These in fact are going beginning of serious menaces to human being life and cultivate the demand to look into and convey frontward an chute safe origin. For this jailed, metal CNG cylinders may necessitate to be re come outd and composite or other stuffs may be the best rootage. We pull up stakes research the chance of composite CNG cylinder und er this undertaking.This predominating state of affairs in Pakistan vehemences on the demand to look into the failing of metal based CNG cylinder and come up with an flip feasible solution non but stronger plenty than metal based CNG cylinders but besides cut cut out the hazard of fatal accidents and life menaces to the consumer. In other words, there is a demand to deliver on empirical probe that help us to convey and alternate safe and strong beginning of CNG cylinder fable based on composite or other stuffs and compare its viability and authority with the bing metal based CNG cylinder. This survey seek to bridge bing spread in CNG cylinder fabrication and propose some feasible solution to engender the give out of by taking the restraints with an purpose to hold a feasible alternate solution of advanced strength, environmental friendly composite CNG cylinder. The undertaking attempt to contribute a hazard put down competitory merchandise. In this respect, we considered Carbon/ paste for the most(prenominal) optimized importations with the last facet of strength and high weight subside of CNG cylinder. For farther betterment optimisation of wall thickness and graphic symbol orientation is besides be done. We give prove each bed of laminated army per unit celestial orbit vas with the application of Tsai- hillock failure standards. This application will surely assist us to device a hazard free composite CNG cylinder. The survey will continue with the specific aim enlisted in to following subdivision.2.3 Aims of the surveyThe chief aim of this survey is to look into the failings of bing metal based CNG cylinder and convey up an alternate feasible solution non only when stronger plenty than metal based CNG cylinders but besides cut down the hazard of fatal accidents and life menaces to the consumer. For this intent, we will analyze the fierceness distribution produced in thin wall metal based CNG cylinder in the visible radiation of diffe rent finite function summary encases and place the shoddy parts. Hoop and longitudinal emphasiss will be calculated by metaphysical analysis of thin wall metal cylinder. Keeping in position the sagacity obtained from theoretical and finite character analysis erroneous belief computation will be done. As we have standardized standards, the FEA package with the least mistaking will be selected for farther proceeding.We will plan a laminated CNG cylinder on the same specification as of bing metal CNG cylinder. We will further optimise the target by optimisation of cant and thickness of laminated shove per unit athletic field vas. The Matlab codification will be generated for laminate analysis of composite CNG cylinder. Subsequently on the Matlab computation will be verified by utilizing ANSYS Workbench 15.The consequences of our design for composite CNG cylinder will be justify from bing literature at domestic ( if any ) and multinational degree.To gauge and analyse the consequence of fibre orientation on stress distribution of composite CNG cylinder, analysis will be run on different fibre fish orientation. Before continuing on the undertaking in systematic mode we will wish to seek penetration from bing literature in the event per unit area vas context.2.4 full general Overview of LiteratureThe history of semisynthetic composite stuff is spread over more than 6000 old ages. The earliest semisynthetic composite stuffs were straw and clay combine to organize bricks for edifice building. Fiber-reinforced composite stuffs besides additions popularity ( despite their by and large(p) high cost ) in high-performance merchandises that needs to be whippersnapper yet strong plenty to take rough lading conditions ( Shaffer,1993 ) . later the gradual development in the field of complexs over clip it was 2006 when a eccentric-reinforced complex was introduced for residential every bit good as mercantile usage as a non-corrosive option to steel ( Water man, 2007 ) .A farther development was observed in 2007 wherein a military vehicle named Humvee , the inaugural all-composite military vehicle, was introduced by TPI Composites Inc and Armor Holdings Inc. It was improved in 2008 by uniting C fibre and Kevlar ( five times stronger than steel ) with enhanced thermoset rosins to do military theodolite instances by ECS Composites making 30-percent igniter instances with high strength ( Pamela J, 2009 ) . This lead to a systematic research on the field affair which is reviewed in the following subdivision.2.5 General Overview of composite force per unit area vasAs stated in the old bomber subdivision that systematic research work on composite force per unit area vass was initiated late that is i.e. In offset printing decennary of the new millenary ( Sheffer, 1993 Waterman, 2007 Pamela J, 2009 and Rayapuri Ashok and Ranjith Kumar, 2013 ) . then there is utmost vestry of cognition on composite force per unit area vas. To the best of our cognition, there are merely a few surveies are available in this country but research work associating to Pakistan is farther pantie or non bing.Wang Yingjun ( 2010 ) conducted a survey in Japan and a finite part theoretical account of C fibre reinforced polymer ( CFRP ) force per unit area vas with aluminum line drive is established by ANSYS finite component package. The component utilized in the survey was Shell-99 ( 4 lymph gland ) . The outer filament lesion fibres were overwrapped by both hoop twist and coiling twist methods. He form that safety was critical because of high work force per unit area which was more than 35MPa. He conducted the inactive analysis of the vas. The burst force per unit area was predicted farther. He make when interior force per unit area increased up to 65MPa, the supreme tensile emphasis of the first CFRP ply reached rupture strength of CFRP. So the force per unit area 65MPa was regarded as the explosion force per unit area.Rayapuri Ash ok and Ranjith Kumar ( 2013 ) in their survey discussed design and analysis of multilayer high force per unit area composite vass along with their advantages over single-channel block vas. Using Abaqus FEA package for burst force per unit area analysis of CFRP composite force per unit area vass for assorted roughage orientation careens, they calculated stress concentration on dish-shaped part. They used element type Solid-46 ( 8 node ) and optimized the fibre tip off orientation by analysing the fibre helically for assorted orientations such as +25/-25 s, +35/-35 s, +45/-45 s, +55/-55 s, +65/-65 s, and +75/-75 s. For this intent they utilized burst force per unit area of 35MPa along with rules stipulate in American Society of Mechanical Engineers ( A.S.M.E ) Sec VIII segment 1. The survey found a per centum economy in stuff of 28.48 % utilizing multilayered composite vass in the topographic point of solid walled vas of SA515 Grade 70 steel. They furthered their probe and used multilayered CFRP stuff and saved 91.62 % stuff when compared to SA515 Grade 70 steel stuff vass. The explosion force per unit areas for assorted theatrical role orientations are predicted utilizing the Tsai-Wu failure standards. The 25 fiber orientation angle is obtained as the optimum fibre orientation angle for the composite force per unit area vas subjected to high internal force per unit area issue.B.Vijay Kiran ( 2012 ) developed an analytical theoretical account for anticipation of optimal fiber orientations for given bed thicknesses. He selected fiber hoi polloi fraction= 0.65 and= 0.35 which was gratifying to the present composite force per unit area vas working at 3MPa internal force per unit area. He found optimal value of fiber orientation which was 55 for glass epoxy and 65 angle for C fibre. From the finite component analysis study the maximal emphasis obtained in each lamina ( for 55, 65 degrees weaving angle ) was little than the allowable on the job strength.The factor of Safety 3 was interpreted for the fibre reinforced composite stuff to get the better of stuff and nonsense design and fabrication defects. The mean critical buckling force per unit area was obtained from finite element analysis study was 4.0684N/mm2, which was more than the maximal on the job force per unit area 3N/mm2. Comparison of stiffened and unstiffened complex lash was done by both theoretically and analytically techniques and he found that the stiffened cylinder has more clasping opposition than that of the unstiffened one.Javad Marzbanrad ( 2013 ) investigated the design and analysis of high force per unit area composite vass based on unit burden method along with complete structural analysis and rating of tiredness life-time were performed utilizing finite element commercial codification ABAQUS. He selected fiber volume fraction= 0.75 and= 0.25 and element Shell-99 ( 8 node ) . He found that the fatigue life-time of vas depends on the finite com ponent mesh size, cleft immersion and ratio in an component.K.M.Pandey ( 2014 ) investigated the clasping behaviour of reasonably thin walled filament-wound carbonepoxy cylinders subjected to hydrostatic force per unit area. A entire 9 sort of composite laminates were considered for finite component analysis. He used Finite component package ANSYS 14.0 and collar finite component plan ACOS win, atomic number 62/NASTRAN and MSC/MARC to formalize the consequences. He besides used Element 281 ( 8 node ) to make the finite component theoretical account. The ANSYS shell component theoretical account predicted the buckling force per unit area with 1.5 % divergence from the other three finite component consequences.2.6 MethodologyWe in our survey and convey for a alternate solution will analyze the emphasis distribution produced in thin wall metal based CNG cylinder in the visible radiation of different finite component analysis packages and place the weak parts. Hoop and longitudinal emphasiss will be calculated by theoretical analysis of thin wall metal cylinder.Theoretical analysis of bing metal CNG cylinder will besides be conducted in the visible radiation of taste addition from work by P.Beer and Johnson ( 2006 ) .The demand for theoretical analysis emerged as to supply a base for design of composite CNG cylinder. Keeping in position the penetration obtained from theoretical and finite component analysis mistake computation will be done. As we have standard standards the FEA package with the least mistake will be selected for farther proceeding.We will plan a laminated CNG cylinder on the same specification as of bing metal CNG cylinder. We will further optimise the design by optimisation of angle and thickness of laminated force per unit area vas. The Matlab codification will be generated for laminate analysis of composite CNG cylinder. The Matlab computation will be verified by utilizing ANSYS Workbench 15. The consequences of our design for composite CN G cylinder will be justified from bing literature at domestic and international degree. To gauge and analyse the consequence of fibre orientation on stress distribution of composite CNG cylinder, analysis will be run on different fibre angle orientation.2.7 Matlab codification for design of composite force per unit area vasclear allclc% Design of composite force per unit area vas% Properties of C fibre/epoxy with 60 % volume fraction% SI unit systemfprintf ( Design Of Composite Pressure Vessel )fprintf ( Properties of Carbon character/Epoxy with 60 per centum Volume fraction )fprintf ( Modulus of Elasticity in longitudinal Direction )E1=134*109 % Pafprintf ( Modulus of snap in hide way )E2=7*109 % Pafprintf ( surcharge Modulus )G12=4.2*109 % Pafprintf ( Posion Ratio )v12=0.25fprintf ( longitudinal tensile break strength )XT=1270e6 % Pafprintf ( cross(prenominal) tensile break strength )YT=42e6 % Pafprintf ( Shear Strength )Sh=90e6 % Poision Ratiofprintf ( Lo ngitudinal compressive break strength )XC=1130e6 % Pafprintf ( Transverse compressive break strength )YC=141e6 % Pafprintf ( inner radius of force per unit area vas )r=.1335 % m % Inner radius of force per unit area vasfprintf ( Burust force per unit area applied )p=75e6 % MPa % Pressure appliedfprintf ( Thickness of force per unit area vas )t1=0.01182 % m % Thickness of force per unit area vasfprintf ( Compliance intercellular substance )S= 1/E1 -v12/E1 0 -v12/E1 1/E2 0 0 0 1/G12 fprintf ( Stiffness Matrix )Q=inv ( S )% puree computationfprintf ( emphasize calculation )fprintf ( Sigma-x )sigmax= ( p*r ) / ( 2*t1 ) % Longitudinal emphasis fprintf ( Sigma-y )sigmay= ( p*r ) /t1 % Hoop emphasisfprintf ( Txy )Txy =0 % Shear emphasisfprintf ( Optimized angle in degree )o=54.7 % Optimized angle in grade% Stress computation at merely optimized anglefprintf ( Stress computation at optimized angle )fprintf ( Longitudinal emphasis at optimized angle )sigma1= ( sigmax* ( cosd ( o ) 2 ) ) + ( sigmay* ( Sind ( o ) 2 ) ) % Longitudinal emphasis at optimized anglefprintf ( Transverse emphasis at optimized angle )sigma2= ( sigmax*sind ( o ) 2 ) + ( sigmay*cosd ( o ) 2 ) % cross emphasis at optimized anglefprintf ( Shear emphasis at optimized angle )Taa12= ( sigmax*sind ( o ) *cosd ( o ) ) + ( sigmay*sind ( o ) *cosd ( o ) ) +Txy* ( cosd ( o ) 2-sind ( O ) 2 ) % Shear Stress at Optimized angleS= 1/E1 -v12/E1 0 -v12/E1 1/E2 0 0 0 1/G12 Q=inv ( S ) fprintf ( Angle orientation )Angles= 0 90 54.7 54.7 90 0 fprintf ( Thickness distribution )t= 0.59 1.18 4.13 4.13 1.18 0.59 *10-3h=0 n_layers=length ( T ) for i=1 n_layersh=h+t ( I ) terminal ezed ( 1 ) =-h/2 omega ( n_layers+1 ) =h/2 for i=2 n_layersomega ( I ) =z ( i-1 ) +t ( i-1 ) terminalA=zeros ( 3,3 ) B=zeros ( 3,3 ) D=zeros ( 3,3 ) for i=1 n_layersA= A + ( Qbar ( Q, Angles ( I ) ) * ( omega ( i+1 ) omega ( I ) ) ) B= B + ( Qbar ( Q, Angles ( I ) ) * ( omega ( i+1 ) 2 omega ( I ) 2 ) /2 ) D= D + ( Qbar ( Q, Angles ( I ) ) * ( omega ( i+1 ) 3 omega ( I ) 3 ) /3 ) terminalfprintf ( ABD Matrix )ABD= A B B D fprintf ( Forces Calculation )NM = 103* 499 998 500 0 0 0 fprintf ( Calculating Initail Strain )strainxy = inv ( ABD ) *NM % initial strain + curvaturesQavg=zeros ( 3,3 ) fprintf ( Calculating Q-bar for each bed )for i=1 n_layersQavg= Qavg + ( ( Qbar ( Q, Angles ( I ) ) * ( omega ( i+1 ) omega ( I ) ) ) /h ) fprintf ( layer = % vitamin D, z = % 0.1f mm , I, omega ( i+1 ) * atomic number 19 )Q_bar=Qbar ( Q, Angles ( I ) )terminalfprintf ( Calculating Q-average )Q_avg=Qavgfprintf ( Calculating S-average )Savg=inv ( Qavg )fprintf ( Modulus of snap in x-axis bearing )Ex=1/Savg ( 1,1 )fprintf ( Modulus of snap in y-axis direction )Ey=1/Savg ( 2,2 )fprintf ( Shear Modulus )Gxy=1/Savg ( 3,3 )vxy=-Savg ( 1,2 ) *Exfprintf ( Stress computation for each bed )for i=1 n_layersfprintf ( layer = % vitamin D, z = % 0.1f mm , I, omega ( i+1 ) *1000 )fprintf ( Strain-xy Produced in the bed )strainxyk = strainxy ( 13,11 ) + omega ( I ) *strainxy ( 46,11 )fprintf ( Stress-xy Produced in the bed )stressxyk = Qbar ( Q, Angle ( I ) ) *strainxykstressLT=TM ( Angles ( I ) ) *stressxykfprintf ( layer = % vitamin D, z = % 0.1f mm , I, omega ( i+1 ) *1000 )StrainLT=S*stressLTfprintf ( Longitudinal Strain )Strain_Longitudinal=StrainLT ( 1,1 ) % Longitudinal strainfprintf ( Transverse Strain )Strain_Transverse=StrainLT ( 2,1 ) % Transverse Strainfprintf ( Longitudinal Stress )Stress_Longitudinal=stressLT ( 1,1 ) % Longitudinal Stressfprintf ( Transverse Stress )Stress_Transverse=stressLT ( 2,1 ) % Transverse Stressfprintf ( Shear Stress )Stress_Shear= stressLT ( 3,1 )fprintf ( Applying TsaiHill standards ) of import= ( stressLT ( 1,1 ) /XT ) 2- ( stressLT ( 1,1 ) *stressLT ( 2,1 ) /XT2 ) + ( stressLT ( 2,1 ) /YT2 ) + ( stressLT ( 3,1 ) /Sh ) 2if Alpha & A lt =1fprintf ( Ok Layer is safe )elsefprintf ( Not Ok Layer is non safe )terminalterminal2.8 DrumheadThree is a scarceness of literature in this the country of composite stuffs. Most of the literature available on composite force per unit area vas is about optimisation of fiber orientation while major part of it is about Glass fiber wherein the research workers identified the emphasis distribution utilizing different fiber orientation. These surveies found the consequence curtailing weight decrease by about 29 % ( K.M.Pandey, 2014 Javad Marzbanrad, 2013 and Rayapuri Ashok, 2013 ) .For analysis purpose many of research workers benefited from ANSYS as the finite component analysis package because this to them provides more user friendly interface and extremely refine analysis compatibility. They selected Shell-99 and Solid-46 ( 8 node ) as component for more optimized consequences. Their most important findings were that Carbon/Epoxy had provided the highest strength consequences with a comparatively high weight decrease. They conducted t heir probe at 54.7 because they presume that it could supply the most optimized consequences but it may non be allowable practically as referred by B.Vijay Kiran ( 2012 ) .They have besides selected 4 and 8 node elements wherein 16 node component is preferred because of its more precise consequences. The other surveies under reappraisal besides used maximal shear emphasis theory while on the other manus Tsai-Hill failure theory provide more better consequences in multilayered laminate analysis. These surveies besides used Abaqus package which may give slight attested consequences when compared to analysis through ANSYS Workbench. We in our survey attempt to get the better of this spread and convey a feasible alternate solution of high strength, environmental friendly composite CNG cylinder.We have utilized Matlab for quantitative analysis of laminated force per unit area vas. The merchandise will be active through a battery of trial in order to line up its genuineness and cogenc y.