Address
AFRL/RZ
1950 5th Street
Wright-Patterson AFB, OH 45433-7251
United StatesLaboratory Representative
Tech Transfer Website:
http://www.wpafb.af.mil/library/factsheets/factsheet.asp?id=6026Description
AFRL Aerospace Systems Directorate develops air and space vehicle propulsion and power technologies. Focus areas include turbine and rocket engines, advanced propulsion systems, and fuels and propellants for all propulsion systems. The Wright-Patterson AFB location is focused on the development of air-breathing engines and most forms of power technology. Programs address both future systems and the need to keep current systems competitive, safe, affordable, and effective. The AFRLAerospace Systems Directorate provides one-stop shopping for all forms of propulsion science and technology of interest to the Air (and space) Force turbine and rocket engines, advanced propulsion systems, and the propellants they run on. The directorate is also responsible for most forms of power technology (other than that required for spacecraft), making it one of the nation's leaders in the field of energetics. Program emphasis is on meeting future Air Force needs while keeping current systems competitive and affordable. AFRLAerospace Systems Directorate personnel and research and development, as well as its test and evaluation facilities, offer numerous unique features and opportunities. TheAerospace Systems Directorate develops propulsion and related technologies for the Air Force including: turbine and rocket engines, advanced propulsion systems, fuels, propellants, and lubricants, and aircraft power. The Directorate is headquartered at the Wright Research Site, Wright-Patterson Air Force Base, Ohio, and supplemented by additional personnel and research facilities located at Edwards Research Site, Edwards Air Force Base, Calif.
Mission
To create and transition propulsion and power technology for the military dominance of air and space.
Tech Areas
- Directed energy power and thermal systems analysis
- Electrical modeling and simulation
- Electrical power systems
- Hypersonics
- Integrated high payoff rocket propulsion technology
- Integrated high performance turbine engine technology
- Integrated power unit
- Internal starter/generator
- Laser diode and electronics cooling
- Aerospace power
- Aerothermodynamic and aeromechanic performance
- Airbreathing engines
- Alternate storable propellants
- High power research
- High speed engine concepts
- Fans and compressors
- Fuels
- Cryogenic power systems
- Lithium-ion and environmental battery development
- Long range strike power & thermal systems analysis
- Capacitors
- Combustion
- Electrical technology and plasma physics
- Electrochemistry and thermal sciences
- Engine integration and assessment
- Systems research
- Turbine analysis design development and testing
- Turbine engines
- PEM and solid-oxide fuel cell development
- Plans and analysis
- Plasma physics
- Polynitrogen chemistry
- Power and thermal management initiative development
- Power electronic systems
- Power generation
- Power semiconductor devices
- Propulsion
- Mechanical systems
- Micro-capillary pumped loop
- Rocket-based combined cycle propulsion
- Solid state chemistry research
- Space & missile propulsion
- Structures and controls
- Superconducting coated conductors
- Superconductivity research
- Pulse detonation propulsion
No Available Technologies for this lab
No Funding for this lab
No Programs for this lab
Displaying 1 - 10 of 48
Advanced Instrumentation Lab
Security Clearance : Non Security LabSquare Footage: 0
The Advanced Instrumentation Lab provides inhouse research and development of instrumentation application and installation techniques for structural testing. The primary goals include the crafting of unique instrumentation solutions and maturing sensors using emergent technology and hardware for the challenging requirements involved with aerospace structures testing. Progress in these areas has yielded capabilities in the following areas: · Thermal Requirements: Point measurements up to 3000°F · Mechanical Requirements: Static measurements up to 2% elongation and dynamic loading at 160 dB OASPL ~128µε RMS · Substrate Requirements: Attachments to various high temperature applicable metallic, composite, and ceramic structures Capabilities: · Static strain measurements at elevated temperatures up to 1,600°F · Dynamic strain measurements at elevated temperature up to 1,800°F · Flame and plasma spray free filament sensor installation · High temperature thermocouple attachment for discrete measurement up to 3,500°F on composite structures · Unique modification of ceramic and graphite adhesive to extend adhesive performance to achieve test requirements
Advanced Launch System Complex
Security Clearance : Non Security LabSquare Footage: 0
Description: Area 1-120 consists of three liquid rocket stands, with five firing positions, a control center and various support facilities. Vertical Stand 1A is a single position stand designed for 1,500,000 lbs thrust liquid rocket systems. Vertical Stand 1B is a dual position stand designed for 6,000,000 lbs thrust liquid rocket systems. Stand 2A is a twoposition horizontal stand designed for 750,000 lbs thrust LOX/LH2/Hc component stand. Purpose: Full scale research on launch vehicle liquid rocket engine systems, subsystems, and components. Research includes extended duration testing at ground level. Test firing of sub-systems and components at a 15 degree down angle orientation and complete integrated engine systems in a nozzle down orientation. Products: Testing and development of liquid rocket systems National Launch System (NLS) Program Digital control and data acquisition systems Repair shop for transducers and other electrical equipment Fuel and oxidizer storage vessels Modern high pressure LOX/LH2 facility, designed to test full scale liquid engine components
Aerospace Power Materials and Components (APMC) Laboratory
Security Clearance : Non Security LabSquare Footage: 0
Description: This laboratory provides a safe facility for areas of energy conversion technologies, including superconductors, cryogenic power devices, carbon nanotubes (CNT), thermoelectric and magnetics. Capabilities: Superconductors, Thermoelectrics, CNT: Material development is supported through dry powder and wet chemistry labs. Samples are facilitated by Laser Deposition, Sputter Rigs, and High Temp Furnaces. Measurements are done by a Physical Property Measurement System (PPMS) supporting Vibrating Sample Magnetometer (VSM), Alternating Current Transport (ACT) and Thermal Transport (TTO). A fully automated Power Factor Screening Instrument (PFSI), and an X-Ray diffraction system as well as cryo coolers, in-field magnets, and AC Loss systems are utilized. Magnetics: Synthesis and characterization tools include a high purity glovebox, a superconducting vibrating sample magnetometer, inductively heated hot press and isostatic presses, high frequency and high power hysteresis graphs and a differential scanning calorimeter. Purpose: Research efforts cover the spectrum of basic science and technology development including theory, modeling and simulation, development and science of materials, and devices and system applications. Products: Specific applications for superconductors and cryogenic power devices include MW-class power transmission cables, superconducting magnetic energy storage (SMES), high-power current switches, distributed electric propulsion for more-electric-aircraft, power systems for RPA, low-power electronics and devices, and rotating machine generator and motor technology. Magnetic materials research focuses on developing improved advanced permanent (hard) and electromagnet (soft) materials for use in future Air Force space and aircraft weapon systems. Thermoelectrics material research focuses on producing energy capture devices to improve overall power system efficiencies. CNT research focuses on producing improved heat transfer devices.
Aerospace Structures Test Facility Environmental Test Chambers (ETC)
Security Clearance : Non Security LabSquare Footage: 0
Purpose: The ETCs test the structural integrity of aerospace structures in representative operating temperatures and aerodynamic load distributions. The test article may be tested in an inert atmosphere. The ETCs are utilized to validate design and analysis of advanced structures technology for extreme thermal and mechanical applications such as hypersonic structures and thermal protection systems. Capabilities: The ETCs are four chambers capable of thermally and mechanically loading aerospace structures at representative mission profiles. ETC #1 and #2 are separated by a removable wall, providing the capability of testing larger structures. · 69 discreet PLC controlled electrical power channels · 82 channels of load control using Moog control system · 500+ channels for data acquisition · Instrumentation includes strain, displacement, load, pressure and digital image correlation · Purged oxygen levels down to 100 ppm using nitrogen gas from10,000 gallon liquid nitrogen Dewar with electric and ambient air vaporizers · 15M BTU/hr evaporative water cooling; 3M BTU/hr deionized wate
Combined Environment Acoustic Chamber (CEAC)
Security Clearance : Non Security LabSquare Footage: 0
Purpose: The CEAC imposes combined acoustic, thermal and mechanical loads on aerospace structures. The CEAC is employed to measure structural response and determine acoustic fatigue life of structural components when exposed to simulated aeroacoustic and thermal loads. The CEAC is used to validate advanced technologies for hypersonic, space access, weapons bay, and exhaust-washed vehicle structures. Capabilities: The CEAC is a progressive wave tube that can test specimens up to 4.46 ft x 9 ft. -Up to 170dB overall sound pressure level produced by acoustic modulators with a controllable output range of 44.7-562 Hz by a third octave band computer controller. -Over 700 specially designed 6000 W quartz lamps radiantly impinge up to 72 Btu/ft2 s on specimens with eight control zones. -Real time display and record up to 130 channels of high speed data (up to 208 kHz) from transducers including accelerometers, strain gages and pressure transducers. -Real time display and record at up to 200 samples/sec as much as 128 channels of thermal data from thermocouples, RTDs and flux gages. -Non contacting sensors available, such as 3-D laser vibrometer, infrared thermal imaging, and digital image correlation. -Access to 10,000 gal liquid nitrogen Dewar, 3000 psig facility hydraulic and 100psi pneumatic systems.
Combustion & Laser Diagnostics Research Complex (CLDRC)
Security Clearance : Non Security LabSquare Footage: 0
Description: The Combustion and Laser Diagnostics Research Complex (CLRDC) supports the experimental and computational study of fundamental combustion phenomena to expand the scientific knowledge base; validate combustor-design codes; and improve the performance, reduce the pollutant emissions, and enhance the affordability, maintainability, and reliability of current and future generation propulsion systems for military and commercial aviation. This state-of-the-art complex provides unique laboratory tools for the experimental characterization of combustion through the development, demonstration, and application of advanced laser-based/optical diagnostic techniques. These capabilities are complemented by a suite of specialized modeling and simulation methodologies for assessing and predicting the detailed chemistry and physics of combustion processes. Purpose: Achieve predictive understanding of combustion chemistry and physics. Provide tools for evaluating advanced combustor concepts. Demonstrate optical platforms for on-board sensing and control. Products: The CLDRC features an impressive array of advanced laser technologies, including many one-of-a-kind optical sources and detectors. CLDRC lasers provide broad spectral coverage from the ultraviolet through the visible to the near, mid, and far infrared (terahertz-radiation region) for flow visualization and spectroscopic investigations of complex reacting and non-reacting flowfields. Continuouswave and pulsed (nano-, pico-, and femtosecond) sources are employed in conjunction with various scientific-grade cameras and ultrafast imaging devices to provide tremendous spatial and temporal resolution and dataacquisition bandwidth for critical Air Force applications. A host of linear and nonlinear optical techniques have been developed and applied, including high-speed digital imaging, emission spectroscopy, planar laser-induced fluorescence (PLIF), laser-induced incandescence (LII), planar Rayleigh scattering (PRS), reactive Mie scattering (RMS), laser Doppler velocimetry (LDV), particle-image velocimetry (PIV), thin-filament pyrometry and velocimetry (TFP, TFV), pressure- and temperature-sensitive paints, spontaneous Raman scattering spectroscopy, coherent anti-Stokes Raman scattering (CARS) spectroscopy, transient-grating spectroscopy (TGS), phase Doppler particle analysis (PDPA), femtosecond ballistic imaging, ultrafast pump-probe spectroscopy, laser-induced polarization spectroscopy (LIPS), picosecond time-resolved laser-induced fluorescence (PITLIF), tunable diode-laser absorption spectroscopy (TDLAS), time-division-multiplexed (TDM) hyperspectral absorption spectroscopy, terahertz time-domain spectroscopy (THz-TDS), and advanced techniques for tomographic reconstruction.
Component Research Air Facility (CRAF)Â Â
Security Clearance : Non Security LabSquare Footage: 0
Description: The CRAF is used to provide simulated flight conditions for R&D programs in the turbine engine, advanced propulsion and fuel technology areas. It supports seven research cells in Buildings 18C, 18E and 490 as well as the Compressor Research Facility. It has three reciprocating compressors providing a total of 7.5 lbm/sec of air at 315 psia. It has two Centac compressors providing a total of 30 lbm/sec of air at 750 psia. The air from the reciprocating and Centac compressors can be heated in a process air heater to provide up to 30 lbm/sec of air at temperatures from 250 deg F to 1150 deg F to selected research areas. In addition, the Air Facility has four turbo-exhausters, each with an exhaust capability of 36,000 cfm at a minimum pressure of 11-inches mercury (25,000 ft altitude). The exhausters can be utilized together to obtain flow rates and pressures from 36,000 cfm at 4 inches mercury (46,000 ft altitude) to over 75,000 cfm at 11 inches mercury. The facility utilizes more than 20,000 HP of equipment. Purpose: Provide simulated flight conditions for turbine engine, advanced propulsion and combustion technology programs. This facility also supports the Augmentor Research, Compressor Research and Turbine Aerothermal basic research facilities. Products: Creation of the simulated flight conditions necessary for R&D programs in the turbine engine, advanced propulsion and combustion technology areas. Availability: Available to support U.S. Government agency use, DoD contractors and dual use/defense conversion use in conjunction with operations in the facilities described in the "Purpose."
Compressor Aero Research Lab (CARL)
Security Clearance : Non Security LabSquare Footage: 0
Description: Design concepts are tested and fundamental fluid experiments are performed in two facilities. The first is a 6,000 hp Compressor Facility (CF). The second is a vertical, continuous inflow Annular Cascade Facility (ACF). All instrumentation and measurement systems for both facilities are maintained at levels that produce highly accurate results. Compressor Facility: Speed Range - 4,500-22,500 rpm Air Flow Range - 10-60 lbs/sec Inlet Total Pressure - ambient Steady State Pressure - 256+ channels Steady State Analog - 160+ channels Unsteady Analog - 32 channels (up to 200 kHz) Annular Cascade Facility: Air Flow Range - 10-60 lbs/sec Inlet Total Pressure - ambient Steady State Pressure - 256+ channels Steady State Temperature - 32 channels Unsteady Analog - 32 channels (up to 200 kHz) The CF has three transonic vehicles available for research: (1) a single-stage fan rig with 10 different transonic rotor, (2) a two-stage high-load compressor, (3) a single-stage fan or core configuration with upstream wake generating capability. The ACF has a stateof-the-art serpentine diffuser on which to conduct research. Purpose: The CARL mission: (1) enhance the understanding of complex internal flow physics within fans and compressors through analytical, computational, and experimental methods, (2) develop high payoff fan and compressor design concepts, and (3) transition research findings via development of improved design methods and modeling techniques. Products: High through flow fan technology. Fan leading edge sweep. Shock loss models. Transonic compressor profile loss models. High- and low-fidelity models of fan and compressor vane/blade interaction.
Compressor Research Facility (CRF)
Security Clearance : Non Security LabSquare Footage: 0
Description: The CRF supports exploratory and advanced development efforts in compressor technology, independently evaluating full-scale, multi-stage, one or two-spool three-flow fans and compressors under operating conditions similar to actual flight profiles. It is used to determine the aerodynamic and aeromechanical performance of the most advanced compressors and fans in the world, while enhancing the understanding their complex internal flow physics. Using this research data, design techniques and CFD codes and models are verified and enhanced. It is automated and computer controlled to study steady-state and transient phenomena on full-size research compressors. The facility can handle most compressors from operational engines and is used to update compressor performance maps. The CRF's performance characteristics include: Main Drive: Speed/power - 0 to 16,000 rpm at 30,000 HP; Speed/power - 0 to 30,000 rpm at 15,000 HP Dual Drive: Speed/Power - 0 - 12,500 rpm at 8000 HP Acceleration rate - 10%/second (facility speed) Inlet pressure range - 2 psia to ambient Inlet air flow rate - 0 - 500 lbm/sec Inlet temperature capability, atmospheric to 500o F Core Discharge conditions: Pressure: Ambient to 40 psia; Flow: 0-500 lbm/sec; Temperature: Ambient to 1,490o F Bypass Discharge conditions: Pressure: 2-40 psia; Flow: 0-250 lbm/sec; Temperature: Ambient to 1,200o F 3rd Stream Discharge conditions: Pressure: 2-40 psia; Flow: 0-125 lbm/sec; Temperature: Ambient to 700o F Data Acquisition Channels: Digital (performance) 1150 Digital high-speed channels: 32 @ 1.2 MSPS/channel; 256 @ 0.256 MSPS/channel Purpose: Perform aerodynamic and aeromechanical research on full-scale, multi-stage, oneor two-spool exploratory and advanced development fans and compressors. Products: Multistage forward sweep technology for high performance fans and compressors Advanced optical surface pressure and temperature measurement technology Verification of advanced (national) computational fluid dynamics codes Development of inlet flow field measurement standards for High Cycle Fatigue test and evaluation Unique test data sets of advanced fans and compressors developed under IHPTET
Detonation Engine Research Facility (DERF)
Security Clearance : Non Security LabSquare Footage: 0
Description: This facility is configured to safely conduct experimental pressuregain combustion research. The DERF is capable of supporting up to 60,000 lbf thrust experiments, with integrated remote control and instrumentation systems. Pulsed thrust measurements from 3 to 1,000+ lbf are made with a damped thrust stand mounted on the existing engine thrust stand. A hardened remote-control room is adjacent to the 750,000+ cu.ft. test cell. Control of all detonation engine operations and data acquisition is done via a computer-based interface integrated into a "virtual instrument/control system" with back-up manual shutdown and safety systems. The facility control system is extremely flexible and can control all aspects of detonation engine operation including: lubrication, operating valve drive motor speed, fuel flow, main combustion air flow, purge air flow, timing, ignition delays, and automatic shutdown in the event of a critical system failure. In addition to conventional data acquisition and control systems, the facility is equipped with up to 16 channels of high-frequency data acquisition at up to 5 MHz. Up to 1 Mhz framing rate digital imaging is also available for advanced laser diagnostics and imaging techniques. The PDE research engine was developed and is used for performance validation and as a test-bed for research of detonation initiation, fuel injection (including endothermic/regenerative fuel cooling), valving, controls, materials, heat transfer/thermal management, multi-tube effects, nozzles, ejectors, hybrid turbine engines, acoustics, power extraction, emissions, and diagnostics. Up to 6 pps of airflow is available continuously at up to 100 psig and 15,000 pounds of high pressure (up to 2200 psi) air available for shorter durations. Oxygen and nitrous oxide are approved as alternative oxidizers. For self aspirated engines, 200+ pps air intake is available with supporting ambient exhaust (14.3 psia). A small-scale steam ejector system provides vacuum capability to 3 psia for low flow rates. Vapor and liquid fuel systems encompass nearly every fuel utilized for airbreathing propulsion (from hydrogen to advanced bio-fuels) with direct connection to the liquid fuel farm for larger flow rates. The facility drainage is isolated with a fuel segregator, and a three-zone Cardox system provide environmental protection along with gas monitoring for fuels, CO and NOx. Purpose: The primary object of the facility is the research and development of pressure-gain combustion including pulsed detonation engines (PDEs) and rotary (or rotating) detonation engines (RDEs). The in-house PDE program was established in order to make AFRL's unique resources available for the development of this technology. In order to work with pulsed and rotary detonation phenomena, AFRL has set out to develop the facilities, diagnostics, modeling tools, and experience necessary to contribute and provide unique resources for the maturation of pressure-gain combustion technology. Products: PDE and PDE hybrid performance 4-tube research PDE that has been operated with over 20 different fuels and hundreds of detonation tube geometries. Other pressure gain combustion devices include pulsejets, single and multi-tube PDE's, rotary detonation engines, and a 7-tube rotary valved PDE. Component technology products include: aircraft structural/acoustic interaction validation, unsteady ejector/nozzle technology, endothermic/regenerative fuel cooling, detonation initiation and transition technology as well as small-scale internal combustion and turbine engine research.
