1. COMBUSTION TA : Donggi Lee PROF. SEUNG WOOK BAEK
DEPARTMENT OF AEROSPACE ENGINEERING, KAIST, IN KOREA
ROOM: Building N7-2 #3304
TELEPHONE : 3714
Cellphone :
TA : Donggi Lee
ROOM: Building N7-2 #1304
TELEPHONE : 5754
Cellphone :

3. 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

4. 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

5. COMBUSTION ENGINEERING
PROPULSION AND COMBUSTION LABORATORY
COMBUSTION ENGINEERING

6. COMBUSTION ENGINEERING
PROPULSION AND COMBUSTION LABORATORY
COMBUSTION ENGINEERING

7. 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

8. 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

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

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

11. 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

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

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

14. 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

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

16. 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

17. COMBUSTION ENGINEERING
PROPULSION AND COMBUSTION LABORATORY
COMBUSTION ENGINEERING

18. 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

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

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

21. 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

22. 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

23. COMBUSTION ENGINEERING
PROPULSION AND COMBUSTION LABORATORY
COMBUSTION ENGINEERING

24. 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

25. 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

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

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

28. COMBUSTION ENGINEERING
PROPULSION AND COMBUSTION LABORATORY
COMBUSTION ENGINEERING

29. 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