Fundamental Mechanisms, Predictive Modeling, and Novel … · 2019. 12. 12. · Stage 1. Discharge...
Transcript of Fundamental Mechanisms, Predictive Modeling, and Novel … · 2019. 12. 12. · Stage 1. Discharge...
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Fundamental Mechanisms, Predictive Modeling,
and Novel Aerospace Applications of Plasma Assisted Combustion
AFOSR
MURI Review Meeting
Andrey Starikovskiy Princeton University
November 6, 2012
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Main Tasks
Thrust 1. Experimental studies of nonequilibrium air-fuel plasma kinetics using advanced non-intrusive diagnostics
Task 1: Low-to-Moderate (T=300-800 K) temperature, spatial and time-dependent radical species concentration and temperature measurements in nanosecond pulse plasmas in a variety of fuel-air mixtures pressures (P=0.5-5 atm), and equivalence ratios
Task 4: Moderate-to-high (T=800 – 1800 K) temperature PAC oxidation kinetics in Discharge Shock Tube Facility at pressures up to 10 bar
Task 5: PAC oxidation and combustion initiation at high pressure, high temperature conditions (RCM)
Thrust 2. Kinetic model development and validation Task 8: Development and validation of a predictive kinetic model of non-equilibrium plasma fuel oxidation
and ignition Task 9: Mechanism Reduction and Dynamic Multi-time Scale Modeling of Detailed Plasma-Flame Chemistry
Thrust 3. Experimental and modeling studies of fundamental nonequilibrium discharge processes
Task 10: Characterization and Modeling of Nanosecond Pulsed Plasma Discharges
Thrust 4. Studies of diffusion and transport of active species in representative two-dimensional reacting flow geometries
Task 13: Ignition and flameholding in high-speed non-premixed flows Task 14: High Fidelity Modeling of Plasma Assisted Combustion in Complex Flow Environments
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PAC: New Dimensions in Combustion
P, atm
0.02 1 40
T, K
250
2500
S/I
f
0.1
3.0
E/n
10
B/S
0.1
1
3
0.3
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What is Different at High P
N2 + e N2(C3Pu) + e
N2(C3Pu) + O2 N2 + O(
3P) + O(1D)
N2(C3Pu) N2 (B
3Pg) + hn
N2(B3Pg) + O2 N2 + O(
3P) + O(3P)
H2 + {O(3P); O(1D)} OH + H
HO2; H2O2 …….
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Plasma Assisted Oxidation P = 1atm; T = 300-800 K
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Discharge Development
1 10 100 10001E-3
0,01
0,1
1
ion
O2(4.5 eV)
O2(dis)
N2(el)
O2(a+b)
O2(v)
N2(v)
tr+rot
N2:O
2 = 4:1
En
erg
y l
os
s f
rac
tio
n
E/N, Td
E/n, Td
I, A
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Influence of Vibrational Excitation on Low-Temperature Kinetics
N2 + e = N2(C3) + e
N2(C3) + O2 = N2 + O + O
O2 + e = O + O + e
N2 + e = N2(v) + e
N2(v) + HO2 = N2 + HO2(v)
HO2(v) = O2 + H
Synergetic Effect of High and Low Electric Fields
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Influence of Vibrational Excitation on Low-Temperature Kinetics
Measured and calculated OH decay time. P = 1 atm.
a) 3%H2 + air; b) 0.3%C4H10 + air.
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3000K
1000K
300K
0.01atm 1atm 100atm
Flames
(Ju, Sutton)
Flow Reactors
(Yetter,
Adamovich)
Shock Tube
(Starikovskiy)
RCM
(Starikovskiy)
MW+laser
(Miles)
JSR
(Ju) Streamer
(Adamovich)
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Forrestal Gas and Plasma Dynamic Lab 9 Months Ago
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Forrestal Gas and Plasma Dynamic Lab 4 Months Ago
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Forrestal Gas and Plasma Dynamic Lab 0 Months Ago
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3000K
1000K
300K
0.01atm 1atm 100atm
Flames
(Ju, Sutton)
Flow Reactors
(Yetter,
Adamovich)
Shock Tube
(Starikovskiy)
RCM
(Starikovskiy)
MW+laser
(Miles)
JSR
(Ju) Streamer
(Adamovich)
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Rapid Compression Machine: P = 10-70 atm, T = 650-1200 K
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Driving chamber
Speedcontrol
chamber
Combustionchamber
Oil reservoirPiston lock chamber
g
N2
Fast active valve
P=30 bar of N2
P=1 bar
Solenoid
Piston
Oil
Scheme of the RCM
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Pressure Measurements
Kistler 6025B
piezoelectric
pressure transducer
- range 0-250 bar
- linearity 0.1%
0
10
20
30
40
50
60
70
80
-15 -10 -5 0 5 10 15 20 25 30 35 40 45 50
Time (ms)
Pre
ss
ure
(b
ar)
compression ignition delay
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Temperature Calculations
• We assumed adiabatic core presence during measurement time.
• i- initial values, c- values after compression.
• Uncertainty < 2K
( ) 1ln (ln )
( )
c
i
T
c
i T
p Td T
p T
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Gas Compression in RCM
Ini tial pos i tion
Co l d g a s
Ho t g a s (c o re )
Final pos i tion
Bottom plate
Piston
Piston
Length of the pis ton s trok e
Clearance height
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Useful Range of Time
0
4
8
12
16
20
165 170 175 180 185 190 195
Time, ms
Pre
ssu
re, b
ar
6mm, 1032K, 12.21 bar
9mm, 1025 K, 11.95 bar
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Useful Range of Time
0
5
10
15
20
25
30
0 30 60 90 120 150 180
Time (ms)
Pre
ssur
e (b
ar)
13mm, 958 K,19.77 bar
9mm, 967 K, 20.87 bar
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Useful Range of Time
0
50
100
150
200
250
0,9 0,95 1 1,05 1,1
1000/T(K)
Au
toig
nit
ion
de
lay
tim
e,
ms
9mm
13mm
clearance
height, mm
time, ms
6
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SDBD Plasma Ignition at High Pressure
ICCD images of the
discharge at 1 atm dry air.
Negative polarity of the high-
voltage electrode, 22 kV, 25
ns duration, f = 40 Hz
[Kosarev et al, 2009].
Mixture C2H6:O2=2:7 at 1 bar
and ambient initial
temperature was
successfully ignited in ~100
ms in relatively large volume
[Sagulenko et al, 2009].
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Rapid Compression Machine: Plasma-Assisted Ignition
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Plasma RCM: Electrode Geometries
localized
nanosecond
spark
nanosecond
SDBD
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Plasma RCM: Regimes of Discharge Development
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PAC at High Pressure: ER = 0.4
T2 = 794 K
P2 = 32.0 bar
Propane
Surface DBD
E < 50mJ
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High-Pressure PAC: Lean Conditions
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High Pressure PAC: Discharge Before Compression Stroke
T2 = 836 K, P2 = 40 bar. Discharge before compression
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High-Pressure PAC: Lean Conditions
Discharge 20 ms before compression
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PAC at High Pressure: ER = 1
T2 = 713 K
P2 = 26.5 bar
Propane
Surface DBD
E < 50mJ
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High-Pressure PAC: ER = 1
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High Pressure PAC: ER = 1 Discharge 20 ms Before Compression
T2 = 672 K, P2 = 20 bar
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High Pressure PAC: ER = 1 Discharge 20 ms Before Compression
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Comparison of Different Types of Discharges
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Plasma-Assisted Ignition at High Pressures
CH4 + O CH3 + OH CH3 + OH CH2O+H2 CH3 + O2 CH2O + OH CH3 + O2 +M CH3O2 + M
T2 = 672 K, P2 = 20 bar. T2 = 794 K, P2 = 32 bar
Ignition delay time for
modified mixtures, f=1.0,
EGR=30%. Discharge 20ms
before compression stroke
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Kinetics of Ignition Development
Stage 1. Discharge in
Methane‐Air mixture at temperature ~ 330 K, 1 atm.
Production of metastable
components. Stage 2. Fast adiabatic
compression to a
temperature of 800‐950 K. Metastable components
decomposition and ignition
development.
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3000K
1000K
300K
0.01atm 1atm 100atm
Flames
(Ju, Sutton)
Flow Reactors
(Yetter,
Adamovich)
Shock Tube
(Starikovskiy)
RCM
(Starikovskiy)
MW+laser
(Miles)
JSR
(Ju) Streamer
(Adamovich)
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Shock Tube with Discharge Section. U ≤ 150 kV, M ≤ 3 – MIPT
Test Section of the Shock Tube 0.5 0.6 0.7 0.8
100
101
102
103
104
105
I
II
III
autoignition
autoignition, experimentautoignition, calculations
PAI, calculations
PAI, calculations
PAI, experiments
PAI, experiments
PAIPAI
Ign
itio
n d
ela
y t
ime
, s
1000/T5, K
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PAC Kinetics at High T, Low P
Shock Tube with Discharge Section. U ≤ 500 kV, M ≤ 5 – Princeton
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Hypersonic Shock Tunnel - MIPT
4.0 4.5 5.0 5.5 6.0 6.5
108
109
1010
Inte
nsi
ty,
W/k
g
Velocity, km/s
Non-equilibrium Peak
Intensity, CO:N2=7:3
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Discharge Formation and Flame Stabilization in High Speed Flow - SCRAMJets
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Princeton Shock Tube/Shock Tunnel
Operating regimes for Princeton’s combustion-driven Shock Tube/Shock Tunnel in Air
Comparison with others
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3000K
1000K
300K
0.01atm 1atm 100atm
Flames
(Ju, Sutton)
Flow Reactors
(Yetter,
Adamovich)
Shock Tube
(Starikovskiy)
RCM
(Starikovskiy)
MW+laser
(Miles)
JSR
(Ju) Streamer
(Adamovich)
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Physics of Nonequilibrium
Systems Laboratory
DBD Discharges Development
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Physics of Nonequilibrium
Systems Laboratory
DBD Discharges: 20 kV, 10kHz, 10th pulse
10 Torr 50 Torr
100 Torr 200 Torr
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DBD Discharges: 20kV, 10kHz, 10 Torr Pulse N5
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DBD Discharges: 20kV, 10kHz, 100th pulse
100 Torr 200 Torr
10 Torr 20 Torr 50 Torr
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DBD Discharges: 20 kV, 10kHz ICCD gate 50 ns
Side view: T0=500 K, ϕ=0.3 Side view: T0=300 K, ϕ=0.0, pulse#10
End view: T0=500 K, ϕ=0.3 End view: T0=300 K, ϕ=0.0
200 Torr -
instabilities
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Major International Collaborations and International Projects
Nickolay Aleksandrov (MIPT, Russia) Sergey Pancheshnyi (ABB, Austria) Svetlana Starikovskaya (LPP, France) PROJECTS: PARTNER UNIVERSITY FUND “Physics and Chemistry of Plasma-Assisted Combustion” (Princeton-LPP) RUSSIAN FEDERAL PROGRAM “Plasma-Assisted Combustion Ultra-Lean Fuel-Air Mixtures for Energy Devices Efficiency Increase” (Princeton-MIPT)
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PUBLICATIONS BOOKS Aeronautics and Astronautics. Edited by: Max Mulder; TUDelft, The Nethrlands . ISBN 978-953-307-473-3. 2011
A.Starikovskiy, N.Aleksandrov
Plasma-Assisted Ignition and Combustion
http://www.intechopen.com/books/show/title/aeronautics-and-astronautics
http://www.intechopen.com/books/show/title/aeronautics-and-astronauticshttp://www.intechopen.com/books/show/title/aeronautics-and-astronauticshttp://www.intechopen.com/books/show/title/aeronautics-and-astronauticshttp://www.intechopen.com/books/show/title/aeronautics-and-astronauticshttp://www.intechopen.com/books/show/title/aeronautics-and-astronauticshttp://www.intechopen.com/books/show/title/aeronautics-and-astronauticshttp://www.intechopen.com/books/show/title/aeronautics-and-astronautics
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PUBLICATIONS - 2012 A.Starikovskiy, N.Aleksandrov. Plasma-assisted ignition and combustion. Progress in Energy and Combustion Science (2012), doi:10.1016/j.pecs.2012.05.003 N.L.Aleksandrov, E.M.Anokhin, S.V.Kindysheva, A.A.Kirpichnikov, I.N.Kosarev, M.M.Nudnova, S.M.Starikovskaia and A.Yu.Starikovskii. Plasma decay in air and O2 after a high-voltage nanosecond discharge. J. Phys. D: Appl. Phys. 45 (2012) 255202 (10pp) A.Starikovskiy, N.Aleksandrov, A.Rakitin. Plasma-Assisted Ignition and Deflagration-to-Detonation Transition. 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee, Jan. 9-12, 2012. AIAA-2012-829 A.Starikovskiy, A.Rakitin, G.Correale, A.Nikipelov, T.Urushihara, T.Shiraishi. Ignition of hydrocarbon-air mixtures with non-equilibrium plasma at elevated pressures. 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee, Jan. 9-12, 2012. AIAA-2012-828 A.Yu. Starikovskiy, S.V.Pancheshnyi, A.E.Rakitin. Periodic Pulse Discharge Self-focusing and Streamer-to-Spark Transition in Under-critical Electric Field. 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee, Jan. 9-12, 2012. AIAA-2012-665 N.Aleksandrov, E.Anokhin, S.Kindusheva, A.Kirpichnikov, I.Kosarev, M.Nudnova, S.Satikovskaia, and A.Starikovskiy. Plasma Decay in Air Excited by High-Voltage Nanosecond Discharge. 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee, Jan. 9-12, 2012. AIAA-2012-511 M.Nudnova, S.Kindusheva, N.Aleksahdrov, A.Starikovskiy. Fast Nonequilibrium Plasma Thermalization in N2-O2 Mixtures at Different Pressures. 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee, Jan. 9-12, 2012. AIAA-2012-510 A.Yu. Starikovskiy, V.P. Zhukov, V.A. Sechenov. Ignition Delay Times of Jet-A/Air Mixtures. 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee, Jan. 9-12, 2012. AIAA-2012-501 M.M.Nudnova, A.Yu.Starikovskiy. Ozone formation in pulsed SDBD at wide pressure range. 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee, Jan. 9-12, 2012, AIAA-2012-407 A. Starikovskiy. Kinetics of Plasma-Assisted Oxidation and Ignition below Self-Ignition Threshold. 50th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition, Nashville, Tennessee, Jan. 9-12, 2012. AIAA-2012-244
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SUMMARY Major Results
1. Rapid Compression Machine is assembled;
2. Plasma Shock Tube is assembled;
3. Shock Tunnel is assembled;
4. Plasma assisted ignition demonstration up to P = 40 atm;
5. DBD discharge development is analyzed
Future Plans
1. High-temperature kinetics of PAC;
2. High-pressure kinetics of PAC;
3. Physics of pulsed discharges – nano- and picosecond scale;
4. Kinetics of nonequilibrium plasma – role of plasma density;
5. Plasma-assisted flame stabilization for GTEs and SCRAMJets.