European Workshop on New Aero Engine Concepts Munich, 30 June – 1 July 2010 NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme (2002-2006) under Thematic Priority 4 Aeronautics and Space. 08 June 2010 1
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European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
08 June 2010 1
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
WP2.3.3: Innovative combustion – F Giuliani, TU Graz )
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
F. Giuliani, A. Lang, Graz University of Technology, AustriaT. Grönstedt, M. Irannezhad, Chalmers University, Sweden
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Contents
• Pulse detonation
• Literature survey – statistics
• Hybrid engine concept
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
• Hybrid engine concept
• Intermittent flow analysis
• Conclusions and recommendations
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Contents
• Pulse detonation
• Literature survey – statistics
• Hybrid engine concept
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
• Hybrid engine concept
• Intermittent flow analysis
• Conclusions and recommendations
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Pulse detonation
What pulse detonation is
a) The detonation is initiated at the closed end of the tube
b) The detonation propagates towards the open end
c) The detonation diffracts outside as a decaying shock, in meantime a reflected expansion wave propagates back to
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
meantime a reflected expansion wave propagates back to the closed end, starting the blow-down process
d) At the end of the blowdown process, the tube contains burned products at rest
d) The purging/filling process is triggered by the opening of the valve, sending a shock wave in the burned gases, followed by the air/product surface
e) A slug of air is injected before the reactants for purging
g) The purging air is pushed out of the tube by the reactants
h) The reactants eventually fill the tube completely and the valve is closed
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Pulse detonation
IDEA: replace the conventional combustor with a pulse detonation combustor
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Pulse detonation
Why ?
– Higher predicted thermal efficiency
– Pressure gain: lower
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
– Pressure gain: lower compressor PR required at similar thrust for a hybrid PDE concept
– Reduced TSFC at similar thrust
– Potential for reducing and simplifying the engine core
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Pulse detonation
Why ?
– Higher predicted thermal efficiency
– Pressure gain: lower
Knowing that :
– Low TRL technology
– Non-conventional fuel so far
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
– Pressure gain: lower compressor PR required at similar thrust for a hybrid PDE concept
– Reduced TSFC at similar thrust
– Potential for reducing and simplifying the engine core
– Flow intermittency
– Stoichiometry + peak T >> 2000 K -> NOx
– Pressure gain -> need of compressing the cooling air
– Complexity of cycle control
– Noise
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Contents
• Pulse detonation
• Literature survey – statistics
• Hybrid engine concept
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
• Hybrid engine concept
• Intermittent flow analysis
• Conclusions and recommendations
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Literature survey - Statistics
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Contents
• Pulse detonation
• Literature survey – statistics
• Hybrid engine concept
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
• Hybrid engine concept
• Intermittent flow analysis
• Conclusions and recommendations
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Hybrid engine concept
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Hybrid engine concept
Reference test case
1200
1400
1600
1800
2000Entropy - Temperature Diagram (Reference)
Tem
pera
ture
[K]
Engine Net Thrust: 122.53 [kN]Equivalence Ratio (φ): 0.33 [-]Thrust Specific Fuel Consumption (TSFC): 13.23 [mg/(N*s)]
p5=32.97 [bar]
p =9.02 [bar]
5
6
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
0 500 1000 15000
200
400
600
800
1000
1200
Entropy [J/(kg*K)]
Tem
pera
ture
[K]
pamb=1.01 [bar]
p1=1.06 [bar]
p3=2.35 [bar]
p4=34.7 [bar]
p6=9.02 [bar]
p7=3.63 [bar]
p8c=1.94 [bar]
018bp23
4
6
7
8c
p2=1.53 [bar]
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Hybrid engine concept
Option 1: Same TSFC, „lighter frame“
1200
1400
1600
1800
2000Entropy - Temperature Diagram (PDE - Case 1)
Tem
pera
ture
[K]
Engine Net Thrust: 122.53 [kN]Equivalence Ratio (φ): 0.33 [-]Thrust Specific Fuel Consumption (TSFC): 13.2 [mg/(N*s)]
Nondimensional heat added (q): 5.07 [-]
pamb=1.01 [bar]p5=27.91 [bar]
p =9.74 [bar]
5
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
0 500 1000 15000
200
400
600
800
1000
1200
Entropy [J/(kg*K)]
Tem
pera
ture
[K]
Temperature ratio of compression (ψ): 2.36 [-]
Peak Pressure after the Rayleigh Heat Addition: 132.36 [bar]Peak Temperature after the Rayleigh Heat Addition: 2584 [K]Pressure ratio of the PDE: 1.6 [-]
p1=1.06 [bar]
p2=1.53 [bar]p3=2.35 [bar]
p4=17.35 [bar]
p6=9.74 [bar]
p7=3.82 [bar]
p8c=2.07 [bar]
018bp23
4
6
7
8c
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Hybrid engine concept
Option 2: Lower TSFC, „heavier frame“
1200
1400
1600
1800
2000Entropy - Temperature Diagram (PDE- Case 2)
Tem
pera
ture
[K]
Engine Net Thrust: 122.53 [kN]Equivalence Ratio (φ): 0.32 [-]Thrust Specific Fuel Consumption (TSFC): 12.51 [mg/(N*s)]
pamb=1.01 [bar]
p5=46.13 [bar]
p6=10.77 [bar]
5
6
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
0 500 1000 15000
200
400
600
800
1000
Entropy [J/(kg*K)]T
empe
ratu
re [K
]
Nondimensional heat added (q): 4.06 [-]
Temperature ratio of compression (ψ): 2.87 [-]
Peak Pressure after the Rayleigh Heat Addition: 193.42 [bar]Peak Temperature after the Rayleigh Heat Addition: 2421 [K]
Pressure ratio of the PDE: 1.3 [-]p
1=1.06 [bar]
p2=1.53 [bar]
p3=2.35 [bar]
p4=34.7 [bar]
p7=4.11 [bar]
p8c
=2.22 [bar]
018bp23
47
8c
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Hybrid engine concept
ASSESSMENTS
„Lighter frame“ „Less TSFC“
TSFC same -5,4%
NOx +85,2% +97,1%
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
Mass -6,5% +12,7%
Length* -10% +1,2%
HPC casing
Injection modules (one per
tube)
40 PDE’s
PDC collector and relaxation chamber
* Provided the assumption of bended tubes is valid
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Contents
• Pulse detonation
• Literature survey – statistics
• Hybrid engine concept
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
• Hybrid engine concept
• Intermittent flow analysis
• Conclusions and recommendations
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
• G2D Unsteady RANS Solver developed at Chalmers University
• Used for 2D simulation of detonation tubes
Intermittent flow analysis
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 18
Time sequence per detonation cycle (here operation at 62.5Hz)
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Intermittent flow analysis
Study @ TU Graz• Focus on the PDC operation as a
function of the ignition sequence• Geometry: from Aarnio et al. 1996,
for validation purpose
Study @ Chalmers• Focus on the interaction of the
intermittent flow on the turbine• Geometry: PDC + guide vanes
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 19
• Mixture: air + hydrogen at Phi=1• Split mixture air 50% / buffer air
50% (Phi global = 0.5)• Operation at ambient conditions• 50 Hz cycles
• Mixture : air + kerosene at Phi=1, split 50%-50% (phi global 0.5)
• Inlet conditions P=32 bar, T=850K• 62.5 Hz cycles
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Intermittent flow analysis
Effect of a controlled phase-shift on the outlet conditions of a PDC
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Intermittent flow analysis
Pulse Detonation Combustor - turbine interaction
• Turbine rotor loss modeled after Kacker and Okapuu (1982)
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
(1982)
• -> 3.85% HPT efficiency loss
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Contents
• Pulse detonation
• Literature survey – statistics
• Hybrid engine concept
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
• Hybrid engine concept
• Intermittent flow analysis
• Conclusions and recommendations
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Conclusions
• Design and simulation tools for a hybrid engine concept were developed and validated at TU Graz and Chalmers
• Two global arrangements using as many standard components as possible were proposed. A TSFC reduction of 5.4% was computed. Further
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 23
were proposed. A TSFC reduction of 5.4% was computed. Further optimisation and combination with other technologies (larger BPR, Geared TF) could push this point further.
• PDC is still low TRL. There is a strong drawback in terms of pollutant emissions. There is a strong effort to be done in terms of R&D.
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Conclusions II
• The effect of a phase shift of the firing tubes was performed to reduce the intermittency of the outlet flow and make it more acceptable for gas turbine operation. It sounds promising while peak transients are reduced and mixing is enhanced. However the complexity in terms of measurements and controls is larger.
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 24
• The impact in terms of loss of turbine efficiency because of the flow intermittency remains bounded: less than 4%.
• Proposal: more research on pulse detonation
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
More research on pulse detonation. Why?
• There is at European level a need to catch-up with this technology. NEWAC gave a good kick in that direction. TU Graz and Chalmers gathered know-how and momentum. Let us make good use of it. Let us do experiments.
• The PDC concept opens the door towards an extremely refined combustion control (number of tubes active, air split, frequency, firing sequence). What
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 25
• Less Nox is possible, probably at the cost of a degradation of thermal efficiency
• For the researcher: towards a better understanding of combustion processes. For the engineer: towards beautiful machines.
control (number of tubes active, air split, frequency, firing sequence). What is learned there can also be a benefit to conventional cycles
mfuel
mair
Eignition
Qheat
Low-Nox PDE concept proposed by TU Graz, usinga partial recirculation of burnt gases with depleted
oxygen in the tube inlet
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Reports and articles on WP2.3.3
Lang, A., Giuliani, F., Lei, X., and Grönstedt, T. (2008). WP2.3 - 2.3.3. Basic configuration for innovative combustion. Technical Report TUG-DEL-2.3.3.A, EU IP NEWAC - FP6-030876.
Giuliani, F. and Lang, A. (2010). WP2.3 - 2.3.3. Final Assessments for Innovative Combustion. Technical Report TUG-DEL-2.3.3.B, EU IP NEWAC -FP6-030876.
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 26
FP6-030876.
Giuliani, F., Lang, A., Irannezhad, M., and Grönstedt, T. (2009). Effect of a controlled phase-shift on the outlet conditions of a set of pulse detonators. In 19th ISABE Conference, Montreal, Canada. ISABE-2009-1315.
Giuliani, F. and Lang, A. et al. (2010). Pulse detonation as an option for future innovative gas turbine combustion technologies: a concept assessment. In 27th Congress of the International Council of the Aeronautical Sciences -ICAS. Ongoing.
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Thank you for your attention
Your Combustion Department at the Institute for Thermal Turbomachinery and Machine Dynamics, TU Graz
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
COUVERTURE
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8. Juni 2010Andreas LANG - TU Graz 28
COUVERTURE
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Engine Scheme
Fan LPC LPTHPC HPT
CC
ConventionalAero Engine
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 29
Larger BPR
Smaller HPC
Split Main/Cooling
air
Further compressed cooling air
PDC HybridAero Engine
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Temperature-Entropy-Diagram of a Hybrid Engine
Entropy(s-s
0)/c
p
Te
mp
era
ture
T/T
0
SHOCK WAVE
RAYLEIGH HEAT ADDITION
HPT
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
partial expansion,mixing and cooling
Tem
pera
ture
T/T
_0
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 30
Entropy(s-s
0)/c
p
Te
mp
era
ture
T/T
0
INLET
FAN
IPC
HPC
HPT
LPT
EXHAUST NOZZLE
cooling
Tem
pera
ture
T/T
_0
Entropy (s-s_0)/cp
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Split of the air mass flow inside the core
• Mass flow of the core– 80% for the PDE tubes
– 20% cooling air for diluting the PDE gases
• Mass flow of the PDE tubes (80%)
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 31
• Mass flow of the PDE tubes (80%)– 40% reacting air mass flow
– 40% buffer air
mco
re
mpd
e
mcoolingmbypas
sm0
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
• Reference Aarnio et al. 1996
• 1 Tube
• Tube length 1.2m
G2D validation case I
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 32
• Tube diameter 0.05m
Air inlet
H2 inlet Pulse Detonation Tube Straight diffuser
Controlled valves
Ignition
Ref. measurement probe
Probes
0.08m 1.05m 1.55m
Ambient
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
• Diffuser angle 0 deg
• Mixture: Air + H2, at stochiometric conditions
• Inlet conditions: 1bar, 300K
G2D validation case II
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
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8. Juni 2010Andreas LANG - TU Graz 33
• Frequency 5 Hz
Air inlet
H2 inlet Pulse Detonation Tube Straight diffuser
Controlled valves
Ignition
Ref. measurement probe
Probes
0.08m 1.05m 1.55m
Ambient
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Conditions of the simulation at TU Graz
Parameter Dimension
Ref. Aarnio et al (1996) This study
Tube number [-] 1 1 to 4
Phase shifts between tubes [radians] - 0, 2π/2, 2π/3,2π/4
Tube length [m] 1.200
Tube diameter [m] 0.050
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Diffuser length [m] 0.300
Diffuser angle [degrees] 0 5
Mixture Air + H2, at stoichiometric mixture conditions
Inlet conditions Ambient air pressure and temperature (10^5 Pa, 300 K)
Frequency [Hz] 5 50
Ratio mixing/puffer air No data, assumed to be 1/1
Probes [-] 7 4
Inlet velocity [m/s] No data, assumed 40 m/s
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
• Peak pressure: 17 bar reported, 18 bar simulated
• Peak decay specific times: 0.2 s
• Resonant effects reproduced
G2D validation case III
20
25
Pre
ssu
re [b
ar]
Probe No 2 at x=1.05m
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 35
• Peak velocities differ fromapproximately 10%
2 2.1 2.2 2.3 2.4 2.5 2.6 2.7 2.80
5
10
15
Time (s)P
ress
ure
[ba
r]
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
• Simulation results compared with the expected Chapman-Jouguet Conditions
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 36
Peak temperature [K] 2956 3127 5,78%Peak pressure [bar] 15,1 15,7 3,97%Mach number [-] 1 0,95 -5,00%
Air inlet
H2 inlet Pulse Detonation Tube Straight diffuser
Controlled valves
Ignition
Ref. measurement probe
Probes
0.08m 1.05m 1.55m
Ambient
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Pulse Detonation Combustor - turbine interaction
Static Temperature Static Pressure
•2-D CFD combustor & stator•Turbine rotor loss modeled with a re-calibrated Kacker and Okapuu correlation
•Combustor pressure ratio 1.45 •Turbine efficiency reduced 3.85%
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
373737
2 MPa 12 MPa1000K 4000K
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
• Hot (detonated) gases and cold (buffer) air are mixed at constant volume(through the detonation tube and diffuser)
• Exhaust and cooling air are mixed at constant pressure(inside the settling chamber)
Assumptions and Assessments I
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
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8. Juni 2010Andreas LANG - TU Graz 38
• PM suggests an HPC pressure ratio of 6
• Maximum number of tubes 40
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
• PDE tube size– Length 1 m
– Diameter 0.05 m
• Core air split
Assumptions and Assessments II
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 39
• Core air split– 20% cooling
– 80% PDE40% reacting air | 40% buffer air
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
• Reacting mixture: H2 + Air
• Equivalence ratio φ=1
• Process frequency up to 60 Hz
Assumptions and Assessments III
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 40
• Inlet Mach number 0.3– 80% of the tube can be filled with fresh reactants
– Fill-time below 10 ms (self ignition time)
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
• Single PDE design in analogy with Aarnio et al. except a conical diffuser(surface ratio 5.5)
• Bluff-Body at the diffuser-outlet is introduced• Enhanced turbulence level
Pulse Detonation Combustor Mesh I
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
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8. Juni 2010Andreas LANG - TU Graz 41
• Allow wall cooling in further work
• Single sector tube consists of 35,000 nodes
• Largest cell dimension is 2.5 mm
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
• Mesh pattern is mirrored for multi-tube configuration
• Lateral boundary conditions along the ambient domain are periodic(force symmetry)
Pulse Detonation Combustor Mesh II
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 42
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Effects of a variable phase-shift on the conditions in the far field
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 43
the conditions in the far field
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Setup
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
• Tube dimensions as described before
• Detonation rate 50 Hz
• Sequence phase shift– 0 π
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 44
– 0 π
– 2π/2
– 2π/3
– 2π/4
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Phase shift 0 π
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 45
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Phase shift 2 π/2
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 46
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Phase shift 2 π/3
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 47
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Phase shift 2 π/4
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 48
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Conclusion
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 49
Conclusion
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Institute for ThermalTurbomachinery andMachine Dynamics
Acknowledgments
This study realised at TU Graz in cooperation with Chalmers was supported by
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 50
This study realised at TU Graz in cooperation with Chalmers was supported by the
European Commission as part of the Integrated Project
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
Phase shift 0 π
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 51
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Phase shift 2 π/2
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 52
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Phase shift 2 π/3
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.
8. Juni 2010Andreas LANG - TU Graz 53
European Workshop on New Aero Engine ConceptsMunich, 30 June – 1 July 2010
Phase shift 2 π/4
• Introduction •••• Hybrid PDE Sizing
•••• Hybrid Engine Concept •••• Effects of a variable phase-shift on the conditions in the far field
•••• Simulation Tools •••• Conclusion
NEWAC is an Integrated Project Co-funded by the European Commission within the Sixth Framework Programme(2002-2006) under Thematic Priority 4 Aeronautics and Space.