Document
Joseph J. Dussling NASA Glenn Research Center Data Engineer, 8x6 SWT/9x15 LSWT TFOME Contract, Jacobs Technology
AIAA SciTech, January 2015
National Aeronautics and Space Administration Historical Overview and Recent Improvements at the NASA Glenn Research Center 8x6/9x15 Wind Tunnel Complex www.nasa.gov Overview of NASA GRC 8x6 SWT/9x15 LSWT
HISTORICAL OVERVIEW
National Aeronautics and Space Administration C-2004-567
Cleveland, Ohio
Ground breaking of Aircraft Engine Research Laboratory Name changed to Flight Propulsion Research Laboratory to reflect expanding role in flight propulsion Name changed for Dr. George Lewis; NACA Director of Aeronautical Research, 1942- 1947 NASA established, renamed to NASA Lewis Research Center Renamed to John H. Glenn Research Center at Lewis Field January 1941 (founded under NACA) ¾ April 1947 ¾ September 28, 1948 ¾ October 1958 ¾ March 1999 ¾
• • • • • Brief Timeline of Glenn Research Center
National Aeronautics and Space Administration 0.25 to 2.0 & 8x6 (SWT) Variable 30 lbm/s 30 lbm/s 30 lbm/s 520 to 720 200 to 1340 1000 to 35000 3.6e6 to 4.8e6 0 to 0.1 Supersonic Wind Tunnel 9x15 0 to 72 (LSWT) Variable (Heated) 30 lbm/s 30 lbm/s 30 lbm/s 0 to 0.23 Sea Level 0 to 1.4e6 Ambient to 550 Low Speed Wind Tunnel ) R) ° Filler Say title Supersonic Wind Tunnel (SWT) and Low Speed Wind Tunnel (LSWT)
Specs of tunnels? ¾ ¾
• Capabilities of 8x6/9x15 Wind Tunnels Test section speed (Mach) Simulated Altitude (ft) Test Section Reynolds number / feet Dynamic Pressure (lbf/ft Test Section Total Temperature ( Auxiliary Air Supply At 40 psig At 150 psig At 450 psig Model Exhaust National Aeronautics and Space Administration Sound barrier broken October 14, 1947 Supersonic research facility would allow study of engines, airfoils, and scale models of planes ¾ ¾ NACA decided to concentrate research on aerodynamic and propulsion issues at supersonic speeds (1945) 8x6 SWT History National Aeronautics and Space Administration High speed leg only (air dryer, drive system, 8x6 test section and diffuser) Solid Wall Tunnel; M=1.4 to 2.0 ¾ ¾ Designed: mid 1940s Built: 1946-1949 First Run: April 3, 1949 Original Configuration: Largest supersonic wind tunnel at that time
• • • • •
8x6 SWT History
National Aeronautics and Space Administration C-1950-26414 produced during supersonic testing Construction of Acoustic Housing to dampen noise
bugle aimed at the heart of Cleveland”
C-1945-23277
hp
motors producing 87,000* hp
8x6 SWT History
“87,000
Seven Stage Axial Compressor driven by three National Aeronautics and Space Administration
Acoustic Muffler Turn 2 and acoustic baffles installed
¾ ¾
January 1950: Noise generated by 16-in. ram jet test was objectionable within a 5 mile radius August 1950: Acoustic Modifications completed
Acoustic Problems • •
8x6 SWT History
National Aeronautics and Space Administration 2007-2469 Orion Launch Abort System model Porosity holes clearly visible behind C-1956-42930 Hole Drilling Operation in 8x6 SWT 4700 porosity holes added to test section to “bleed” air through walls Flexwall modified for operation for Mach 1.0 to 1.3 Altitude exhaust installed for test section bleed
¾ ¾ ¾
Converted to a transonic tunnel in 1956
Transonic Operation •
8x6 SWT History
National Aeronautics and Space Administration Aerial view of 8x6/9x15 complex showing return leg Dried air within tunnel could be reused Doors allow easy conversion between running open/closed loop
¾ ¾
Aerodynamic testing in closed
Tunnel loop (back-leg) was completed in 1956 loop Propulsion testing in open loop
Return Leg • • • 8x6 SWT History
National Aeronautics and Space Administration
wall” test section; acoustic boxes added
-
Designed: 1967 Built: 1968-1969 First Run: 1969
¾ ¾ ¾ Built in return leg of 8x6 SWT Originally a “hard
Need for a large low-speed facility for Vertical/Short Takeoff and Landing (V/STOL) aerodynamics research later for noise suppression
• • • 9x15 LSWT History
National Aeronautics and Space Administration 1970-01199 Model showing STOL and v/STOL wings Aerodynamic performance and acoustic testing Nozzles, inlets, and propellers Crossflow conditions, varying angles of attack ¾ ¾ ¾ Originally built for Vertical/Short Takeoff and Landing (V/STOL) testing Capable of testing large-scale hardware in a continuous subsonic airstream (0- 175 mph)
• • 9x15 LSWT History
National Aeronautics and Space Administration 2009-04566 counter-rotating drive rig Open Rotor testing in the 9x15 LSWT using the Provides a 5,000-hp drive rig for testing subscale high bypass ratio fans Provides a 750-hp (per shaft) counter- rotating fan drive rig for open rotor (unducted fan) testing ¾ ¾
Now, used extensively for low air-speed aero-performance and acoustic testing for fan rigs
• 9x15 LSWT History
National Aeronautics and Space Administration Can run the 9x15 up to Mach 0.14 on 1 motor Can run the 8x6 up to Mach 0.5 on 1 motor Minimum speed of 8x6 reduced from Mach 0.36 to Mach 0.25
¾ ¾ ¾
Conceived and successfully demonstrated in 1995 Desire to reduce power consumption at low speed operation for the 9x15 Added benefit of expanding the operability envelope at the low end for the 8x6 SWT
One-Motor Drive Operation • • • 9x15 LSWT History
National Aeronautics and Space Administration 2.0 1.5 1.0 Mach Number 0.5 Wing blower operation 1-Motor operation 3-Motor operation 8x6 SWT Test Section Air Speed Capabilities 0.0 Current Original (1949)
8x6 SWT / 9x15 LSWT History
Transonic (1956) National Aeronautics and Space Administration
Military, civil aviation, space testing Acoustics Sonic Boom
¾ ¾ ¾
Wide range of applications and customers (NASA and external) Basic aerodynamic research Force and moment Propulsion systems Airframe integration V/STOL Space Transportation Transport Cruise Performance Environmental
• • • • • • • • • 8x6 SWT / 9x15 LSWT Areas of Testing
National Aeronautics and Space Administration 1964-72479 Launch Escape System 0.059 Scale Model of Apollo 2007-2471 Orion Capsule and Launch Abort System (LAS) 1970-1385 Wernher von Braun visits the 9x15 LSWT 1983-6425 Space Shuttle in 8x6 SWT 1960-54465
Space Applications
Saturn Model in 8x6 SWT
8x6 SWT / 9x15 LSWT Areas of Testing
National Aeronautics and Space Administration 2010-4864 1983-6428 Inlet Test Space Shuttle Nozzle Test Large Scale Low Boom Propulsion 2013-1171 1959-49977 SST Propulsion Inlet Double Inlet Bell Model 1957-45564 1979-0673
Supersonic Inlets and Nozzles
Technology Inlet Bump with 17-in Inlet
8x6 SWT / 9x15 LSWT Areas of Testing
Spike & Return Bleed Scoop & Highly Maneuverable Aircraft National Aeronautics and Space Administration 1986-3413 1986-4703 F-16 STOVL F-15 Hot Gas Model 1976-2620 1994-4441 Lockheed X-32 Model Quiet Clean STOL Experimental Engine Low Mach Hardwall Inlet 1990-4389 1996-0851
Vertical/Short Takeoff and Landing
STOVL Model STOVL 279-3C Model
8x6 SWT / 9x15 LSWT Areas of Testing
National Aeronautics and Space Administration Model 1996-4524 1994-1827 during Noise Reduction Test Acoustic Barrier Wall installed Universal Propulsion Simulator Fan 1996-3949 2010-3454 Propeller for Farfield Acoustics the High Bypass Ducted Rotating Microphone installed on Open Rotor Propulsion Rig installed
Acoustics
8x6 SWT / 9x15 LSWT Areas of Testing
National Aeronautics and Space Administration Overview of NASA GRC 8x6 SWT/9x15 LSWT
RECENT IMPROVEMENTS Data Systems
National Aeronautics and Space Administration graphical pages OR
nalyze
A
1 sample/sec (up to 10 samples/sec with limitations) 10,000 channels max., sampled and calculated 16 data viewing windows max. Alphanumeric 36 Gigabytes storage Command line interface
ecord, &
ESCORT • • • • • •
R
state” data system in
-
roadcast,
B
graphical on bserve,
O
AND 800 samples per second) ollect,
C Replaces existing ESCORT DAS (1980s)
¾ ¾
Faster, multiple sampling (12 ½, 25, 50, 100,…, Over 25,000 channels, sampled and calculated (upper limit not determined) 32 stations with multiple pages per station Alphanumeric same page Terabytes of storage Graphical User Interfaces
2016; COBRA
COBRA • • • • • •
• Upgrade of facility “steady COBRA
National Aeronautics and Space Administration 1000lb NF, SF 2000lb AF 2000in-lb PM,YM 18000in-lb RM • • • • Capacity Two full sets of gauges Custom Telemetry 8 RTDs 4 pressure transducers Accommodates up to 12 two- wire blade strain gauges • • • • • • 6 Component Rotating Balance Check loading successfully accomplished in May Initial data analysis shows balance behavior much improved when compared with initial results ¾ ¾ Developed in conjunction with several Environmentally Responsible Aviation (ERA) tests in the 9x15 LSWT Metric shell for “B” Balance was modified and balance delivered April 2014 Balance installed in drive rig and testing completed in 9x15 LSWT in May-July 2014 Balance to be used for most future fan testing in 9x15 LSWT
• • • • 6 Component Rotating Balance
National Aeronautics and Space Administration 12 Balance Bridges 12 Dynamic Strain Gauges 4 Kulites 8 RTDs 8 Board Monitors Up to 28 Dynamic Strain Gauges 8 Board Monitors
¾ ¾ ¾ ¾ ¾ ¾ ¾
Custom Designed FPGA based for reconfiguration Default Configuration: Alternate Configuration:
• • • • Telemetry for Rotating Balance
National Aeronautics and Space Administration Oil Temperature Bath Fluke Black Stack RTD Reader Kaye offers higher accuracy over conventional references Thermistors and TCs are read into Escort and compared against each other for overall health checks of system
¾ ¾
Upgrades to 9x15 LSWT temperature measurement system completed 2012 Thermocouples (TCs) now connected to Kaye Uniform Temperature Reference (UTR) Health monitoring of the entire system is achieved using an Oil Temperature Bath Similar upgrades planned for 8x6 SWT in next couple of years
Thermocouple Upgrades
• • • •
National Aeronautics and Space Administration Overview of NASA GRC 8x6 SWT/9x15 LSWT
RECENT IMPROVEMENTS Facility Upgrades
National Aeronautics and Space Administration
Outdated Men only Well maintained Now men’s and women’s
¾ ¾ ¾ ¾
Former Current
¾ ¾
Restrooms
•
Outdated Minimal seating of 5-6 comfortably Single phone Can now seat 10-12 comfortably Internet access Data access from facility servers Projector Multiple phones and conference line Color printer
¾ ¾ ¾ ¾ ¾ ¾ ¾ ¾ ¾
Former Current
Customer Accommodations & Improvements
¾ ¾
Customer Room
National Aeronautics and Space Administration
•
Showing Inlet at “Buzz” condition.
on Large Scale Low Boom Inlet test - Image acquired from 8x6 Schlieren System – Optical Phase Knife 1200x800 at 3250 fps 500,000 fps at reduced resolution – – Replaced the receiving optics with new off-the-shelf SOA optical components Phantom V310 Involved a new seal design and modifying existing window frames Replaced existing antiquated 150W Xenon light source utilizing newer LED technology Investigated & implemented newer knife edge technologies Optical phase knife edges • • • • • Receiving Optics Upgrade: High Speed Digital Imaging Capability: New schlieren windows: Light source: Knife Edge Technologies: Standard “razor” knife edge 1. 2. 3. 4. 5.
Conventional Schlieren Enhancements Conventional Schlieren System Upgrades
National Aeronautics and Space Administration Light Source S x Δ BOS Detector Background Classical Z-type Schlieren BOS is a more recent development of the schlieren and shadowgraph techniques used to non-intrusively visualize density gradients Based on an apparent movement of the background when imaged through a density field onto a detector plane BOS captures the density field but only requires a CCD camera, light source, and a high-contrast background
Background Oriented Schlieren (BOS) • • •
National Aeronautics and Space Administration
Flow
BOS
Flow
B BOS BOS from top and conventional from side First time BOS has been implemented in a GRC wind tunnel Fluorescent background allows lighting to be applied at any angle as opposed to being nearly perpendicular as required by traditional retro-reflective backgrounds ¾ ¾ Technique successfully demonstrated in 8x6 SWT Fluorescent BOS background designed and installed onto tunnel floor BOS and Conventional Schlieren at same condition. Different views:
Background Oriented Schlieren (BOS) • •
National Aeronautics and Space Administration Test section acoustic treatment Turning vanes in Corner 2 Turning vanes in Corner 3 Acoustic baffles Diffuser modification Additionally, no negative impact on flow quality or test capability for 8x6 SWT test section ¾ 1. 2. 3. 4. 5.
Maintain (or improve) current aerodynamic test capabilities in terms of Mach number, temperature, flow quality Five recommended modifications identified: ¾ ¾ Acoustic Study performed with overall goal of developing solutions to reduce background noise of 9x15 LSWT at Mach 0.2 Computational Fluid Dynamics (CFD) model created for baseline geometry and validated with experimental data Available funding will dictate magnitude, duration and schedule of facility improvements
• • • 9x15 Acoustic Test Section Upgrade
National Aeronautics and Space Administration Goal to reduce boundary layer noise by 5-7 dB Acoustic treatment study in progress to test treatment samples to verify noise reduction magnitude ¾ ¾ Currently focusing on the selection of 9x15 test section flow surface acoustic treatment • Design requirement is to have acoustic boxes be more of a “modular” design Specialized work cart will be available for model work while floor is installed to prevent damage to treatment • •
9x15 Acoustic Test Section Upgrade
National Aeronautics and Space Administration
Fahrenheit
㼻
of motion
㼻
Single and double knuckles also available for angles of attack and yaw 360 5000 in-lbs drive torque 3000 lbs axial load 8000 lbs radial load 300,000-400,000 in-lbs pitching moment Operating temperatures up to 250
¾ ¾ ¾ ¾ ¾ ¾ ¾
Desire for roll mechanism for models in 8x6 SWT Model Support Strut can pitch for angle of attack Hydraulically actuated roll mechanism currently being designed with following capabilities:
• • • Roll Mechanism
National Aeronautics and Space Administration – 㼻 kick to allow overall AoA 㼻 range of about -15 to +15 Strut (supersonic) mounted design includes -10 used for attaining appropriate AoA) Sting mounted design (includes knuckle to be Strut (supersonic and transonic) and sting mounted roll mechanisms have been designed Material selection currently ongoing
• • Roll Mechanism
National Aeronautics and Space Administration Assists with balance checkouts, model fit-ups, etc. Glenn accepts offer of model backstop (summer 2013) ¾ ¾ Desire for further capabilities of model buildup in wind tunnel shop NASA LaRC had additional model backstop housed at National Transonic Facility (NTF) Hardware arrived November 2013, temporary location Backstop in final location, April 2014 Currently, updating actuation and control systems
• • • • • Model Backstop
National Aeronautics and Space Administration TBD 2016 2012 2015 2012 2012 2015 2010 2014 2015 2010-2013 Implementation In Use In Use In Use In Use In Use Status Fabrication Refurbishing Development Development Material Selection In Use / Continual Development Project 8x6 SWT / 9x15 LSWT Improvement Summary COBRA DAS 6-Component Rotating Balance Telemetry Thermocouple upgrade Customer Accommodations Schlieren System Upgrades 9x15 Acoustic upgrade Roll Mechanism Check Load Stand Autoloader Model Backstop National Aeronautics and Space Administration Your Title Here National Aeronautics and Space Administration Overview of NASA GRC 8x6 SWT/9x15 LSWT
BACKUP SLIDES
National Aeronautics and Space Administration Portable Check Load Stand 8x6 SWT Check Load Stand 9x15 UHB, 2012 Used for in-situ verification of force measurement systems ¾ Portable stands for application of check loads on test articles in test section or build-up facilities Can be built around test article if required 1000 lbs load capacity each axis 8x6 Favor Test, 2010
• • •
Check Load Stands
National Aeronautics and Space Administration 1000 lbs Autoloader in use in the 8x6/9x15 WT Build up room Can be used to apply loads up to 1000 lbs in 50 lbs increments Designed and fabricated by NASA LaRC and Modern Machine & Tool Co., Inc. Desire for device to automate the process Device should have small footprint for use in test section or build up area ¾ ¾ ¾ ¾
1000 lb. capacity autoloader Loading 1000 lbs manually is very labor intensive
• •
Autoloader
National Aeronautics and Space Administration