Fundamental Mechanisms, Predictive Modeling, and Novel Aerospace Applications of Plasma Assisted Combustion Yiguang Ju AFOSR MURI Review Meeting Ohio State University Nov 9-10, 2011 Princeton Team members: Wenting Sun, Joe Lefkowitz, Mruthunjaya Uddi, Sang Hee Won Collaborators AFRL: Campbell Carter, Timothy Ombrello International: Fei Qi, Huijun Guo (USTC) 1
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Fundamental Mechanisms, Predictive Modeling,
and Novel Aerospace Applications of Plasma
Assisted Combustion
Yiguang Ju
AFOSR MURI Review Meeting
Ohio State University
Nov 9-10, 2011
Princeton Team members:
Wenting Sun, Joe Lefkowitz, Mruthunjaya Uddi, Sang Hee Won
Collaborators
AFRL: Campbell Carter, Timothy Ombrello
International: Fei Qi, Huijun Guo (USTC) 1
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Standard Form 298 (Rev. 8-98) Prescribed by ANSI Std Z39-18
Motivation
Hypersonic propulsion system
2
Hypersonic propulsion system
X-51A
Ignition time (~10ms)
Flow residence time (~1ms)Da= >>1
Challenges:• Ignition time, Ignition energy
• Flame stabilization
• Combustion completion
F135 engine: (F35, 2011)
Mach 6-8
Ignition instability
Plasma assisted combustion
Plasma
Ions/electrons
Excited species
Kinetic enhancement
Fuel fragmentsTemperature
increase
Transport enhancementThermal enhancement
RadicalsH2, CO
CH4
Understanding: Good poor
O, NO
O2(a∆g)
marginal
3
Change of ignition and extinction diagram: the S-curve transition
Thrust 1. Kinetic effects of non-equilibrium plasma-assisted fuel
oxidation on diffusion flame extinction limits
Thrust 2. Direct ignition and the S-curve transition by in situ nano-
second pulsed discharge
Thrust 3. Plasma flame chemistry study in a flow reactor with
Molecular Beam sampling Mass Spectrum (MBMS)
Thrust 4. Development of a plasma assisted jet stirred reactor with
molecular beam sampling and a high pressure ignition
chamber
12
Thrust 1. Kinetic effects of non-equilibrium plasma-assisted fuel
oxidation on diffusion flame extinction limits
13
Experimental setup
14
FWHM= 12 ns
f = 0~50 kHz
20 & 28 mm ID
15 mm × 22 mm
10 mm
E/N~10-15 Vcm2
10 mm away from exit
Power~1.3 mJ/Pulse
FTIR/GC sampling
(heated)
-40 -20 0 20 40 60 80 100-3000
-1500
0
1500
3000
4500
6000
Vo
lta
ge (
V)
Time (ns)
O2/Ar/He/CH4
The thermocouple was coated with MgO and covered with grounded Nickel-Chrome sheath to remove EMI
OO
ffO
OU
U
L
Ua
1
2
P= 60 Torr
Laser diagnostics schematic
225nm mirrors
Filters
840nm
Collection lens
UV focusing lens
Photodiode
1064nm
225nm mirrors
225.7nm
Nd:Yag SHGTunable
Dye
Laser
BBO
DoublingBBO
Mixing
UV
Separator
Pulser
Boxcar
SRS272
PMT
Flow
direction
15
Numerical model
16
Kinetic model: OSU air
plasma model [1,2] with USC
mech II in addition of
Ar/He/CH4 related reactions.
Physical model: quasi-one
–dimensional flow equation +
steady two-term expansion
Boltzmann equation [1] Species concentrations
from simulation
ReactionsRate Const
(cm3s-1)
Ar(+) + CH4Ar +CH3 (+) + H 6.5×10-10
Ar(+) + CH4Ar +CH2 (+) + H2 1.4×10-10
Ar* + CH4Ar +CH3 + H 5.8×10-10
Ar* + CH4Ar +CH2 +H2 5.8×10-10
He(+) +O2 O(+) + O + He 0.6×10-11T0.5
Ar* + O2Ar+2O 2×10-10
He(+) +O2(a) O(+) + O + He 0.6×10-11T0.5
He+2O He* + O2 1×10-33
He* + CH4 CH + H2 + H+ He 5.6×10-13
Reference:
[1]. A. Bao, Ph.D thesis (2008) OSU [2]. M. Uddi et al, PCI 32(2009) 929 [3]. I.N. Kosarov et al, C&F 156(2009) 221 [4]. A. Hicks et al, JPD, 38(2005) 3812 [5]. D. S.
Stafford et al, JAP, 96(2004) 2451 [6]. M. Tsuji et al, JCP, 94(1991) 277 [7]. A.M. Starik et al, C&F, 157(2010) 313 [8]. I.N. Kosarev et al, C&F 154(2008) 569
Relationship between OH* emission intensity, local maximum temperature and fuel mole fraction, To=650 K, Tf=600 K He/O2 = 0.66:0.34 , P = 72 Torr, f = 24 kHz, a = 400 1/s
hysteresis between ignition and extinction: S curve
Rayleigh Scattering[1,2]
method for T measurement at 532 nm from Nd:YAG laser