Design and Simulation of Two Stroke Engines

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Design and Simulation of Two-Stroke Engines The continuity equation for mass flow in previous sections is still generally applicable and repeated here, although the entropy gain is reflected in the reference acoustic velocity and density at position 2: mj - m2 = 0 n (2.12.3) mj - mr= 0 v ' These equations become, with rightward retained as the positive direction: rG5 G5 PoiXS^GjacCXu - Xrl) + P02Xs2 :5 A2G5ao2(Xi2 - Xr2) = 0 p01XsfA1G5a01(Xil - Xrl) - pt[CcAt][Csct] = 0 (2.12.4) The above equation for the mass flow continuity for flow from the upstream station 1 to the throat, contains the coefficient of contraction on the flow area, Cc, and the coefficient of velocity, Cs. These are conventionally connected in fluid mechanics theory to a coefficient of discharge, Cd, to give an effective throat area, Ateff, as follows: Cd = CCCS and Ateff = CdAt This latter equation of mass flow continuity becomes: PoiX^A^ao^Xi! - Xrl) - CdPtAtct = 0 The First Law of Thermodynamics was introduced for such flow situations in Sec. 2.8. The analysis required here follows similar logical lines. The First Law of Thermodynamics for flow from superposition station 1 to superposition station 2 can be expressed as: hcl+^L = h 'si s2 + 4 or (cs 2 l+G5aJ)-(c£+G5as 2 2) = 0 (2.12.5) The First Law of Thermodynamics for flow from superposition station 1 to the throat can be expressed as: or c c sl • ' hsl+—= ht+ — 2 l 2 Cp(Tsl-Tt) + ^ ^ = 0 (2.12.6) 110
as: Chapter 2 - Gas Flow through Two-Stroke Engines The momentum equation for flow from the throat to superposition station 2 is expressed A 2
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Design and Simulation of Two-Stroke
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A Second Mulled Toast When as a stu
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Acknowledgments As explained in the
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Table of Contents Nomenclature xv C
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Table of Contents 2.10.1 Flow at pi
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Table of Contents 3.5.3.1 The use o
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Table of Contents 6.1.3 The effect
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Nomenclature NAME SYMBOL UNIT (SI)
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speed of rotation speed of rotation
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attenuation or transmission loss wa
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Design and Simulation ofTwo-Stroke
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Design and Simulation ofTwo'Stroke
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Chapter 4 Combustion in Two-Stroke
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Chapter 4 - Combustion in Two-Strok
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a stratilpl o tions to ivior. If m
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CD 30 -, W 20 - LU CO iS _J LU OC 1
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181 also x3 = — = 0.905 x6 = 2.17
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to be cur .3.20) .3.21) .3.22) for
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3.23) com- :on is hhas has a /eng-
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stroke .3.29) mean me to 3land ssio
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a LU z: en 3 CO a LU z EC D m O ho
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CD 1.2 -i 1.0 - di „„ LU 0.8 cc
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CO —> 111" cc LU < LU _J LU CC £
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Combustion in compression-ignition
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stroke ari more often lseful lental
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lat the ssi ;tribu- ELEVATION VIEWS
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CYLINDER HEAD TYPE IS CENTRAL BORE,
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CO E 50 40 - O O _i Hi > I CO 30 Z)
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CURRENT INPUT DATA FOR 2-STROKE 'SP
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Cylin- PP £ Pa- tics of Paper Chap
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vfitro- ;titi >tants 1970. i(In- Ch
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£2 = Pi P2 I Pi J Chapter 4 - Comb
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CHAINSAW AT 9600 rpm. Chapter 4- Co
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LLI •z. O N -z. 0.21 -, 0.20 DC 0
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Chapter 7 Reduction of Fuel Consump
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Chapter 7 • Reduction of Fuel Con
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Chapter 7 - Reduction of Fuel Consu
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^ s C£ Q 2^ E Q. Q_ z' o ISSI HCEM
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o > z~ Q w CO UJ w g x O z o z o m
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0.35 • 0.34 LU ° 0.33 - c 03 DC
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§ 2000
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y, ,6 Chapter 7 - Reduction of Fuel
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Chapter 7- Reduction of Fuel Consum
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INLET FOR r AIR AND FUEL Chapter 7
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o Q_ Ld < CD 15-, 10- Chapter 7 - R
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Chapter 8 Reduction of Noise Emissi
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Chapter 8 • Reduction of Noise Em
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Chapter 8 - Reduction of Noise Emis
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1 Chapter 8 - Reduction of Noise Em
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• • / . • Appendix Listing of
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Active radical (AR) combustion and
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initial conditions, assumptions reg
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in two-stroke engine (schematic dia
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exhaust timing control valve, effec
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I Exhaust emissions/exhaust gas ana
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Exhaust systems (continued) untuned
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gas constant/universal gas constant
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in crankcase heat transfer analysis
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Mercury Marine air-assisted fuel in
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I PISTON POSITION (computer program
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Pressure wave reflection (in pipes)
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local acoustic velocity, 60 local M
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Roots blower in turbocharged/superc
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Scavenging (continued) scavenging e
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Simulation, engine See Computer mod
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temperature vs. crankshaft angle (c
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work per thermodynamic (Otto) cycle
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Design and Simulation of Two Stroke Engines

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