Upload
others
View
3
Download
0
Embed Size (px)
Citation preview
Fundamental Mechanisms, Predictive Modeling,
and Novel Aerospace Applications of Plasma Assisted Combustion
AFOSR
MURI Review Meeting
Andrey Starikovskiy Princeton University
November 6, 2012
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
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
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 …….
Plasma Assisted Oxidation P = 1atm; T = 300-800 K
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
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
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.
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)
Forrestal Gas and Plasma Dynamic Lab 9 Months Ago
Forrestal Gas and Plasma Dynamic Lab 4 Months Ago
Forrestal Gas and Plasma Dynamic Lab 0 Months Ago
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)
Rapid Compression Machine: P = 10-70 atm, T = 650-1200 K
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
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
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
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
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
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
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
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].
Rapid Compression Machine: Plasma-Assisted Ignition
Plasma RCM: Electrode Geometries
localized
nanosecond
spark
nanosecond
SDBD
Plasma RCM: Regimes of Discharge Development
PAC at High Pressure: ER = 0.4
T2 = 794 K
P2 = 32.0 bar
Propane
Surface DBD
E < 50mJ
High-Pressure PAC: Lean Conditions
High Pressure PAC: Discharge Before Compression Stroke
T2 = 836 K, P2 = 40 bar. Discharge before compression
High-Pressure PAC: Lean Conditions
Discharge 20 ms before compression
PAC at High Pressure: ER = 1
T2 = 713 K
P2 = 26.5 bar
Propane
Surface DBD
E < 50mJ
High-Pressure PAC: ER = 1
High Pressure PAC: ER = 1 Discharge 20 ms Before Compression
T2 = 672 K, P2 = 20 bar
High Pressure PAC: ER = 1 Discharge 20 ms Before Compression
Comparison of Different Types of Discharges
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
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.
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)
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
PAC Kinetics at High T, Low P
Shock Tube with Discharge Section. U ≤ 500 kV, M ≤ 5 – Princeton
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
Discharge Formation and Flame Stabilization in High Speed Flow - SCRAMJets
Princeton Shock Tube/Shock Tunnel
Operating regimes for Princeton’s combustion-driven Shock Tube/Shock Tunnel in Air
Comparison with others
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)
Physics of Nonequilibrium
Systems Laboratory
DBD Discharges Development
Physics of Nonequilibrium
Systems Laboratory
DBD Discharges: 20 kV, 10kHz, 10th pulse
10 Torr 50 Torr
100 Torr 200 Torr
DBD Discharges: 20kV, 10kHz, 10 Torr Pulse N5
DBD Discharges: 20kV, 10kHz, 100th pulse
100 Torr 200 Torr
10 Torr 20 Torr 50 Torr
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
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)
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
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
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.