COMBUSTION TA : Donggi Lee PROF. SEUNG WOOK BAEK DEPARTMENT OF AEROSPACE ENGINEERING, KAIST, IN KOREA ROOM: Building N7-2 #3304 TELEPHONE : 3714 Cellphone : 010 - 5302 - 5934 swbaek@kaist.ac.kr http://procom.kaist.ac.kr TA : Donggi Lee ROOM: Building N7-2 #1304 TELEPHONE : 5754 Cellphone : 010 - 8504 - 5841 kingdonggi@kaist.ac.kr

COMBUSTION ENGINEERING PHYSICAL PICTURE OF COMBUSTION WAVE VERY SMALL IGNITION ENERGY – EXTINGUISHED Vs = SPACE VELOCITY OF THE FLAME ; I.E. RELATIVE TO WALL Vu = VELOCITY OF UNBURNED MIXTURE RELATIVE TO WALL Vf = VELOCITY OF THE FLAME RELATIVE TO THE UNBURNED MIXTURE Vf = Vs –Vu :BURNING VELOCITY PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING INSTANTANEOUS GENERATION OF A C-J DETONATION STAGNANT BURNED GAS Vc P(x) V(x) VCJ P1 U = 0 PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING STRUCTURE OF THE DETONATION WAVE INDUCTION ZONE 2S UNBURNED V2 COMBUSTION VCJ CJ (2) IGNITION DELAY TIME P1 T2 P2S VCJ T2S PCJ T1 V2 V2S P1 PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING USUALLY GET Chapman-Jouguet DETONATION ; PROPERTIES OF C-J DETONATION MASS-MOMENTUM-ENERGY FOR C-J WAVES AND PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING VALID FOR C-J DETONATION OR DEFLAGRATION PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING FOR DETONATION, OR OR OR PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING C-J DETONATION VELOCITY DEPENDS ONLY ON THE HEAT RELEASE Q, INDEPENDENT OF . THEREFORE, VARIES WITH ONLY BECAUSE THE SPEED OF SOUND CHANGES. PRESSURE RATIO, OR PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING FROM MASS, MOMENTUM, AND ENERGY OR OR PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING MACH NUMBER OF BURNED GASES RELATIVE TO THE WALLS FOR C-J (HIGH SUBSONIC) PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING COMPARISON BETWEEN PRESSURE BEHIND A SHOCK & C-J DETONATION FOR THE SAME MACH NUMBER Q 2S (1) PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING FOR C-J DEFLAGRATION, (GOOD FOR C-J DETONATION & DEFLAGRATION) FOR C-J DEFLGRATION, PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING GET (FOR C-J DETONATION) FOR DEFLAGRATION M= 1/6 EXAMPLE FOR THE C-J DETONATION OF MIXTURE PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING DIFFERNTIAL EQUATION OF TRANSPORT OF MATTER AND ENERGY INCLUDING COMBUSTION REAL COMBUSTION PHENOMENA INVOLVE HUNDREDS OF INTERACTING CHEMICAL REACTIONS. BUT FOCUS ATTENTION ON A MODEL OF COMBUSTION, WHICH ACCORDS WITH REALITY IN RESPECT OF THE OVERALL EFFECTS. PURPOSE : QUANTITATIVE PREDICTIONS OF COMBUSTION PHENOMENA PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

SIMPLE CHEMICALLY REACTING SYSTEM (SCRS) FUEL + OXIDANT PRODUCT 1 S 1+S S : STOICHIOMETRIC RATIO REACTANTS PRODUCE A UNIQUE PRODUCT IN FIXED PROPORTIONS BY MASS. INDEPENDENT OF TEMPERATURE PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING H : HEAT OF COMBUSTION IF AND PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING FOR STEADY 1-D DIFFUSION-CONTROLLED FLAMES THE FUEL AND OXIDIZER COMBINE WITH A FIXED STOICHIOMETRIC RATIO S : AND IF PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING OBEYS THE SAME DIFFERENTIAL EQUATION AS THE MASS FRACTION OF A CHEMICALLY INERT MATERIAL DOES. PRECISE KNOWLEDGE OF THE ‘S IS NOT NECESSARY. FOR SCRS NO VISCOUS SHEAR WORK NO KINETIC ENERGY EFFECTS NO EXTERNAL ENERGY SOURCES PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING THE TWO STREAM MIXING PROCESS (AN IDEALIZATION OF COMBUSTION CHAMBER FLOWS) FOR ANY EXTENSIVE PROPERTY OF A FLUID WHICH IS FREE FROM SOURCES AND SINKS : CONSERVED PROPERTY : MIXTURE FRACTION PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING EX) min : MASS FRACTION OF AN INERT COMPONENT , , AND ANY LINEAR COMBINATION OF SUCH CONSERVED PROPERTIES: IF THE MIXING PROCESS IS ADIABATIC AND FREE FROM WORK INPUT, STAGNATION ENTHALPY IS A CONSERVED PROPERTY PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING THE FUEL AND OXIDANT MASS FRACTION ARE LINKED WITH IF F : FUEL, A : OXYGEN WITH DILUENT PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING AFTER CHEMICAL REACTION IS COMPLETED. PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING

COMBUSTION ENGINEERING IT SHOULD BE OBSERVED THAT THE MIXTURE FRACTION WILL OBEY THE SAME DIFFERENTIAL EQUATIONS AS DO AND . PROPULSION AND COMBUSTION LABORATORY COMBUSTION ENGINEERING