Document
National Aeronautics and Space Administration The NASA Environmentally Responsible Aviation Project/General Electric Open Rotor Test Campaign
Environmentally Responsible Aviation Project !
Dale Van Zante Sub-Project Engineer for Propulsion Additional system analysis provided by the Subsonic Fixed Wing Project 51st AIAA Aerospace Sciences Meeting Grapevine, TX January 8, 2013 www.nasa.gov
Outline "
• Objective
• The Open Rotor Propulsion Rig (ORPR)
• The Test Campaign
• Systems Analysis of an Advanced Single Aisle Aircraft
• The ERA Diagnostics Test at NASA Glenn
• Simplified shielding configurations
• Outlook
• Acknowledgements
The GE/NASA/FAA Collaboration on Open Rotor Testing " • Objective: Explore the design space for lower noise while maintaining the high propulsive efficiency from a counter-rotating open rotor system.
• Approach: A series of low-noise open rotor systems were tested in collaboration with General Electric and CFM International, a 50/50 joint company between Snecma and GE. Candidate technologies for lower noise were investigated. Installation effects such as pylon integration were investigated in partnership with GE and the FAA.
“Can Open Rotors ever by quiet enough to be practical?”
Open Rotor Propulsion Rig (ORPR) "
Three Model Propulsion Simulator (MPS) rigs were fabricated in the 1980s.
MPS SN001- Used at Boeing.
MPS SN002- Used at GE Cell 41.
MPS SN003- Used at NASA Lewis.
MPS SN003 was refurbished and is now called ORPR.
- New digital telemetry system - Updated/upgraded rotating force balances.
NASA C-1985-6030 Chris Hughes of the GRC Acoustics branch oversaw the ORPR rehab.
The Test Campaign "
• The test program characterized the aerodynamic and acoustic performance of Generation-1 and Generation-2 blade sets.
Gen-1 Blade Sets (NASA/GE) Historical Baseline (F31/A31, 1980s best aero) Modern Baseline (2000s CFD+CAA design) 2 GE Advanced Designs 2 SNECMA Designs Historical Baseline Gen-2 Blade Sets (NASA/FAA/GE) Blade Set 6 GE Advanced Designs 12 x 10 blade count Pylon wake mitigation
The Gen-1 test series "
GE/Boeing test.
Apr 5 – 28.
First research run.
Oct 28 Drive rig rehab ERA Diagnostics Test.
and installation Jul 19 – Sep 7 2009 " 2010 " 2011 " Drive rig checkout.
GE/Airbus test.
Sep 24 – Oct 27 Linear array Dec 14 – Feb 12 checkout.
Dec 7-11 Gen-1 designs demonstrated significant noise reduction with high aero efficiency.
Gen-1 8x6 Test Feb 28 – Aug 25
The Gen-2 test series "
Gen-2 8x6 Test Gen-2 9x15 Test Aug 26 – Sep 9 Nov 10 – Jan 19 2011 " 12 " Linear Array development in the 9x15 Jan. 19, 2012 End of Gen-2 Test
Systems Analysis of an Advanced Single Aisle Aircraft "
NASA Study Results – Fuel Burn vs. Noise "
NASA modern airplane: Advanced UHB Turbofan 15% structural weight reduction from composites, etc.
Open rotor version has +2100lbs (953 kg) weight penalty Fuel burn: 27% Noise: 25 dB cum margin to CH4 N+1 Tech UHB TF NASA modern airplane BPR ~14 Open Rotor (modern blade set) 162 pax, 3250nm mission Fuel burn: 36% Cruise M= 0.78, 35kft (FL350) Noise: 13 dB cum margin to CH4 Rear mount Turbofan N+1 Tech Open Rotor BPR >30 Guynn , M., Berton , J., Hendricks, E., Tong, M., Haller, W., & Thurman, D.
(2011). “Initial Assessment of Open Rotor Propulsion Applied to an Advanced Single-Aisle Aircraft,” 10th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference, AIAA-2011-7058. Virginia Beach, VA.
" Guynn , M.; Berton , J.; Haller, W.; Hendricks, E.; and Tong, M.: Performance and Environmental Assessment of an Advanced Aircraft with Open Rotor Propulsion. NASA TM-2012-217772, 2012.
Margin NASA modern airplane 162 pax, 3250nm mission 1998 technology reference vehicle Cruise M= 0.78, 35kft (FL350) Noise 162 pax, 3250nm mission Rear mount Open Rotor % Fuel Burn Benefit " Environmentally Responsible Aviation and Subsonic Fixed Wing Projects
The ERA Diagnostics Test at NASA Glenn "
ERA Diagnostics:
Detailed Historical Baseline flowfield measurements "
Leading edge vortex track High Low The 3D PIV measurements provide a wealth of A canonical shielding information about the blade Fwd Rotor configuration provides code Suction wakes and vortex track.
validation data.
surface The location of peak noise level The Pressure Sensitive in the phased Paint measurements show array map phase locked static changes in the pressure on the surface of presence of the the rotating blade.
CFMI pylon indicating a change in the relative strength of sources.
Test Geometry "
1. Rotor sound should be unaffected by the wall " 2. Should be useful for validation of prediction methods " 3. Useful for estimation of noise reduction in system level studies " Shielding Experiment:
Realistic Source, Simplified Shield "
Simplified Shield Results "
Semi-infinite barrier Finite barrier • Up to 10 dB OASPL peak attenuation with short barrier • Enough to meet noise goals?
• Simplified prediction methods over-predict shielding: advanced methods needed • Source distribution may be complicated Stephens, David and Envia , Edmane , “Acoustic Shielding for a Model Scale Counter-rotation Open Rotor,” AIAA 2011-2940, 17th AIAA/CEAS Aeroacoustics Conference, Portland, Oregon, June 2011.
Berton , Jeffery J., “Empennage Noise Shielding Benefits for an Open Rotor Transport,” AIAA 2011-2764, 17th AIAA/CEAS Aeroacoustics Conference, Portland, Oregon, June 2011.
Summary "
• The test program required a substantial commitment from the research/facilities organizations.
• Double shift operations, 5 days a week since Sept 2009 • 1142 hours of run time on the open rotor rig • A collaboration between all partners (ERA, SFW, FAA and GE) was necessary for the success of the test and ongoing data analysis.
• Low-noise, high-efficiency Open Rotor systems have been demonstrated. The progress in source noise reduction has been remarkable. (10+ EPNdB Cum. in a single generation) • System analysis (TRL 4) has shown promise for substantial acoustic margin for new aircraft designs based on Gen-1 data.
• Gen-2 test series focused on pylon installation effects. System studies with the Gen-2 data are ongoing.
Acknowledgements "
NASA Environmentally Responsible Aviation Project Subsonic Fixed Wing Project Aeronautics Test Program FAA Continuous Lower Energy, Emissions and Noise Program General Electric Co. and CFMI and partners Boeing and Airbus
Open Rotor papers based on the GE/NASA work at
Glenn Research Center. "
Elliott, David M., “Initial Investigation of the Acoustics of a Counter Rotating Open Rotor Model With Historical Baseline Blades in a Low Speed Wind Tunnel,” AIAA 2011-2760, 17th AIAA/CEAS Aeroacoustics Conference, Portland, Oregon, June 2011.
Stephens, David and Envia , Edmane , “Acoustic Shielding for a Model Scale Counter-rotation Open Rotor,” AIAA 2011-2940, 17th AIAA/CEAS Aeroacoustics Conference, Portland, Oregon, June 2011.
Berton , Jeffery J., “Empennage Noise Shielding Benefits for an Open Rotor Transport,” AIAA 2011-2764, 17th AIAA/CEAS Aeroacoustics Conference, Portland, Oregon, June 2011.
Hendricks, Eric, “DEVELOPMENT OF AN OPEN ROTOR CYCLE MODEL IN NPSS USING A MULTI-DESIGN POINT APPROACH,” GT2011-46694, ASME Turbo Expo 2011, Vancouver, BC, June 2011.
Van Zante , Dale, Gazzaniga , John, Eliott , David, and Woodward, Richard, “An Open Rotor Test Case: F31/A31 Historical Baseline Blade Set,” ISABE-2011-1310, Gothenburg, Sweden, September 2011.
Van Zante , Dale E. and Wernet , Mark P., “Tip Vortex and Wake Characteristics of a Counterrotating Open Rotor,” AIAA-2012-4039, 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Atlanta, GA, 29 July – August 1, 2012.
Hendricks, Eric S. and Tong, Michael T., “Performance and Weight Estimates for an Advanced Open Rotor Engine,” AIAA-2012-3911, 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Atlanta, GA, 29 July – August 1, 2012.
Stephens, David B., “ Nearfield Unsteady Pressures at Cruise Mach Numbers for a Model Scale Counter-Rotation Open Rotor,” AIAA-2012-2264, 18th AIAA/CEAS Aeroacoustics Conference, Colorado Springs, CO, June 2012.
Guynn , M., Berton , J., Hendricks, E., Tong, M., Haller, W., & Thurman, D. (2011). Initial Assessment of Open Rotor Propulsion Applied to an Advanced Single-Aisle Aircraft. 10th AIAA Aviation Technology, Integration, and Operations (ATIO) Conference, AIAA-2011-7058. Virginia Beach, VA.
Guynn , M.; Berton , J.; Haller, W.; Hendricks, E.; and Tong, M.: Performance and Environmental Assessment of an Advanced Aircraft with Open Rotor Propulsion. NASA TM-2012-217772, 2012.
Hendricks, E. and Tong, M. "Performance and Weight Estimates for an Advanced Open Rotor Engine." AIAA-2012-3911. NASA/ TM-2012-217710. 48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference, Atlanta, GA, 30 July-1 August 2012.
Envia , Edmane , “Open Rotor Aeroacoustic Modelling ,” presented at the Conference on Modelling Fluid Flow, Budapest, Hungary, Sept. 4-7, 2012.
Abstract "
The Open Rotor is a modern version of the UnDucted Fan (UDF) that was flight tested in the late 1980 ʼ s through a partnership between NASA and General Electric (GE). Tests were conducted in the 9 ʼ x15 ʼ Low Speed Wind Tunnel and the 8 ʼ x6 ʼ Supersonic Wind Tunnel starting in late 2009 and completed in early 2012.
Aerodynamic and acoustic data were obtained for takeoff, approach and cruise simulations. GE was the primary partner, but other organizations were involved such as Boeing and Airbus who provided additional hardware for fuselage simulations. This test campaign provided the acoustic and performance characteristics for modern open rotor blades designs. " NASA and GE conducted joint systems analysis to evaluate how well new blade designs would perform on a B737 class aircraft, and compared the results to an advanced higher bypass ratio turbofan. " Acoustic shielding experiments were performed at NASA GRC and Boeing LSAF facilities to provide data for noise estimates of unconventional aircraft configurations with Open Rotor propulsion systems. " The work was sponsored by NASA ʼ s aeronautics programs, including the Subsonic Fixed Wing (SFW) and the Environmentally Responsible Aviation (ERA) projects. "