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Transcript of Rolls-Royce High Mach Propulsion UTC S. Heister, W. Anderson School of Aeronautics & Astronautics I....
Rolls-Royce High Mach Propulsion UTC
S. Heister, W. AndersonSchool of
Aeronautics & Astronautics
I. Mudawar, P. SojkaSchool of
Mechanical Engineering
Rolls-RoyceUniversity Technology Center
in High Mach Propulsion – Year 1 Review and Status Update
Rolls-Royce High Mach Propulsion UTC
Outline
1. UTC Overview & Year 1 Goals – Heister
2. Fuel/Air HEX Project Status – Mudawar
3. Supercritical Fuel Injection Project Status – Sojka
4. Afterburner Cooling Project Status – Anderson
5. Summary & Year 2 Plans - Heister
Rolls-Royce High Mach Propulsion UTC
Senior UTC Personnel• Dr. Steve Heister, UTC Lead, propulsion, two-phase flows,
engine cycles• Dr. Bill Anderson, combustors, fuel stability• Dr. Issam Mudawar, high heat-flux heat transfer• Dr. Paul Sojka, supercritical “atomizer” design & spray
characterization• Dr. Jay Gore, IR spectroscopy• Mr. Scott Meyer, Senior Engineer, facilities &
instrumentation• Ms. Melanie Thom (Baere Aerospace Consulting): over 15
years experience in fuel systems
Rolls-Royce High Mach Propulsion UTC
Collaborators & Students in UTC
• Fuel/air HEX project– Mr. John Tsohas, M.S. student– Mr. Neal Herring, Ph.D. student– Mr. Tim Kibbey, M.S. student and Rolls-Royce Fellowship recipient– Mr. Adam Finney, undergraduate student
• A/B cooling project:– Mr. Tom Martin, M. S. student and Ross Fellowship recipient– Mr. Eric Briggs, M. S. student
• Supercritical fuel injection project:– Mr. Greg Zeaton, M. S. student– Mr. Omar Morales, MARC/AIM program
Rolls-Royce High Mach Propulsion UTC
High Mach Propulsion UTC 5 Year PlanTwo-phase Fuel Injection
Design injector(s) for two-phase fuel mixture flow into combustor
• Test at least two injector designs to develop data base for mass-driven spray formation
• Develop design models to treat mass-transfer driven spray formation
• Predict mean drop size and drop size distribution in terms of atomizer operating conditions, nozzle geometry, and fuel physical properties
• Build on existing effervescent atomizer model development
• Include influence of fuel vaporization/cracking, which can produce liquid/vapor mixture
• Develop design models to treat mass-transfer driven spray evolution
• Predict patternation, cone angle, entrainment of surrounding air, and penetration
• Build on existing effervescent atomizer model development (effervescent Diesel injection)
• Eventually include vapor distribution as well as liquid distribution
Rolls-Royce High Mach Propulsion UTC
Supercritical Fluid (SCF) Injection Experiment
Identify performance limitations for SCF injection and develop design guidelines for future high-Mach engines
A literature review of previous supercritical fluid injection studies suggests fuel superheat, atomizer geometry, and gas/fluid density ratio are the key variables that effect “Spray” cone angle Patternation “Spray” momentum rate distribution
Goal
Rolls-Royce High Mach Propulsion UTC
SCF Injection – Fluid Selection Jet fuel ruled out
for initial experiments
HOQ is engineering approach to decision making
Surrogate “fuel” selected based on human factors and functional performance
Rolls-Royce High Mach Propulsion UTC
CO2 selected as surrogate “fuel” for first experiments Relatively safe, inert, non-toxic Inexpensive, readily available Supercritical thermodynamic and transport properties are already well defined Non-combustible so no need to redesign existing spray apparatus Tc “low” so existing apparatus can be used
SCF Injection – Fluid Selection
Rolls-Royce High Mach Propulsion UTC
SCF Injection – Baseline Pressure Swirl Injector
Pressure swirl atomizer selected as baseline configuration for evaluation Larger cone angles (better distribution of fuel mass in the combustion chamber) than demonstrated in previous experiments using plain orifice injectors with SCF’s Injector geometry is easily modified to obtain desired spray characteristics
Rolls-Royce High Mach Propulsion UTC
SCF Injection - Preliminary flow visualizations
9.2 g/s 9.2 g/s
H2O-in-air (1) and H2O-in-H2O (2) flows demonstrate the
influence of density ratio on spray evolution
A density ratio similar to H2O-in-H2O (near unity) will
be present when SCF experiments are performed
(1) (2)
Rolls-Royce High Mach Propulsion UTC
SCF Injection - Preliminary flow visualization
An overall
decrease in
cone angle with
increased
density ratio
was observed
Rolls-Royce High Mach Propulsion UTC
SCF Injection - Experimental apparatus
Test vessel CO2 supply system
Air supply system DAQ system
Rolls-Royce High Mach Propulsion UTC
SCF Injection – Test vessel
Windowed chamber
Injector
Originally used for
Diesel injection Recently upgraded to
withstand pressures
of 1500 psi (10.3 MPa) Reconfigured for
supercritical CO2
operation (O-rings,
supply lines, etc.)
Rolls-Royce High Mach Propulsion UTC
SCF Injection - Test rig
Air heater
CO2 heater
Test vessel
Gas booster
Opticaltable
PID heatercontrols
Meteringvalve
Rolls-Royce High Mach Propulsion UTC
SCF Injection – Test rig
TC probe
Coriolis flow meter
Co-flow air manifold
Test vessel
Dome regulator
Rolls-Royce High Mach Propulsion UTC
SCF Injection - DAQ & control
SCXI interface
TC panel
Control output panel
Analog input panel
Rolls-Royce High Mach Propulsion UTC
SCF DAQ – optical patternator
Optical patternator
developed at Purdue
0.5
0.6
0.7
0.8
0.9
1
0 6 12 18 24 30 36 42 48 54 60 66 72 78 84 90 96 102
108
114
120
126
Pixel Number
Sp
ray
Pat
tern
(0
Deg
rees
)
0.5
0.6
0.7
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0.9
1
0 6 12 18 24 30 36 42 48 54 60 66 72 78 84 90 96 102
108
114
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126
Pixel Number
Sp
ray
Pat
tern
(0
Deg
rees
)
Rolls-Royce High Mach Propulsion UTC
SCF DAQ – Momentum rate probe
Technique refined at Purdue over the last ten years Characterizes spray penetration via force balance To be installed in test vessel
Rolls-Royce High Mach Propulsion UTC
SCF Injection – Overview of system capabilities
Heat and pressurize CO2 above its critical T and p and inject into ambient environment whose p and T exceed critical CO2 values
Operate at any combination of p and T above CO2 critical values
Obtain shadowgraphs of spray cone angle Uncertainty: +/-5 %
Obtain mass distribution data Uncertainty: +/-0.5%
Obtain momentum rate data for spray penetration Uncertainty: +/-1%
Rolls-Royce High Mach Propulsion UTC
SCF Injection – Status
Facilities near completion waiting on accumulator (to damp
injection pressure pulsations) TRR next week DAQ software optimization Configure optics SCF experiments will begin by the end of
January 2004
Rolls-Royce High Mach Propulsion UTC
Gearing Status• Leveraging of UTC funds is a primary goal• Current Status
– NASA MSFC “Risk Reduction for the ORSC Cycle”• ~ $0.5M w/ ~ 1/3 focused on thermal management
– NASA GRC “Flow Boiling Critical Heat Flux in Reduced Gravity” (~$0.5M)
– RR/AADC Industrial Affiliates Fellowship for Tim Kibbey– Purdue Ross Fellowship for Tom Martin– U/G Honors thesis project Adam Finney– MARC/AIM summer fellowship for Omar Morales– AFOSR MURI in Hypersonic Transition
Rolls-Royce High Mach Propulsion UTC
Summary – High Mach UTC
• Schedule on track to fulfill Year 1 goals– Research team in place– Fuel Thermal Management Lab nearly complete– Facility mods to spray diagnostics lab nearly
complete
• Gearing/leveraging efforts already successful, future efforts to explore projects with AFRL and/or NASA GRC