A -- Turbine Engine Research Center (TERC) Enhancement and Sustainment

Air Force Research Laboratory, (AFRL/PRKB), is hosting a pre-solicitation conference for F33615-02-R-2223 (formerly posted as PRK-01-10, F33615-01-R-2111 in the sources sought synopsis dated 22 Jan 2001). The conference will be held at WPAFB, Area B, on 04 March 2002 from 1300 to 1600. All persons attending the conference will be met in the lobby of the Area B Visitors Center between 12:30 and 12:45. If for some reason the meeting must be postponed, interested parties who respond to this notice will be notified by phone or e-mail. This is an IDIQ five-year effort to support research, development, enhancement & sustainment of the TERC including measurement, data acquisition, analysis, control, & computer systems used for the measurement & analysis of experimental turbine engine components Due to increased security on base, all participants must send the following information to one of the points of contact listed above for each person attending the conference by COB 26 FEB 2002: Company Name, Individual Name, Title, Business and Home Addresses, Business Phone and Fax, Business E-mail, and statement that individual is a U. S. Citizen. A tour of the facility is also planned. Due to limitations of space on the tour, all participants may not be able to go on the tour. The fax number is +1 (555) 000-0000. The procurement is unrestricted (not set-aside). Direct questions to the Contracting point of contact identified in the announcement. A brief background and scope of the program follow. The primary mission of the Turbine Engine Research Center (TERC) is to analyze and evaluate the aerodynamic and aeromechanical performance of advanced turbine engine components. To meet its mission, the TERC conceives, develops, operates and manages technology that: Provides high quality data necessary to document performance; Develops and applies state-of-the-art measurement techniques; Develops, modifies and integrates advanced analytical tools in support of test requirements Acquires, verifies, analyzes, manages and presents acquired data. The objective of this contract is to research, develop and apply techniques, methods, software and hardware for the measurement and analysis of aerodynamic and aeromechanical parameters of experimental turbine engine components and to insure the operational readiness of the TERC measurement, data acquisition, analysis, control, and computer systems. Facilities that are currently part of the TERC are: COMPRESSOR RESEARCH FACILITY (CRF): A compressor under test in the CRF is driven by one of two 30,000 horsepower synchronous electric motors coupled by a gearbox system that can drive the test compressor at rotational speeds of up to 30,000 revolutions per minute (RPM). Computer control and/or monitoring of all systems allows detailed study of the test compressor through immediate data analysis. Drive motor speed, electrical power conditioning, inlet valve positions, discharge valve positions, and variable test compressor geometry (e.g., variable vanes, bleed valves) are all digitally controlled. Test article lubrication, drive motor lubrication, actuator hydraulics, service air, cooling water, and auxiliary air systems are controlled by programmable logic controllers (PLCs). The control system uses CAMAC hardware with 500+ analog input channels sampled at 100Hz per channel, 32 analog output channels, 48 digital input channels and 48 digital output channels. The computer systems are DEC alpha computers using the VMS operating system. The control software is primarily custom FORTRAN with some C code. The primary Test Article data system uses VXI hardware with 1500+ channels of analog input sampled at 60Hz per channel. Data acquisition is handled by an NT system using modified Kinetics Systems Visual Basic and C++ code. The online data reduction, display and data storage is handled by a DEC ALPHA using VMS running custom FORTRAN code. The Aeromechanics data system is a UNIX system running custom C++ code and is used to acquire and process dynamic data (strain gage, high response pressure transducers, etc). The data acquisition and control systems are tied to a common IRIG-B clock. Additional software features allow pre-test development of a Test Article Data Base tailored to a compressor's unique requirements and post-test data playback for data analysis, reduction and display. TURBINE RESEARCH FACILITY (TRF): The TRF is a short duration test apparatus used to conduct aero-thermal investigations of phenomena relating to turbine components (primarily rotor and vane assemblies) The TRF contains all the support hardware, software and instrumentation required to run tests on advanced turbine designs.. The facility consists of a large tank filled with heated, pressurized gas, an evacuated test section, and two large evacuated dump tanks. The test section is comprised of a turbine rotor section, which is spun up to a predetermined speed by an air motor, and then allowed to coast for a few seconds. At the test speed, a valve is opened, allowing the pressurized test gas to flow through the test section that contains the spinning test rotor and on to the dump tanks. The tests have a duration of two-to-five seconds. The turbine rotor's speed during the test is regulated and subsequently brought to rest by an eddy current dynamometer. Facility health data is acquired throughout spin-up, test and spin-down. Performance data, currently derived from 400 temperature, pressure, speed, torque and heat flux sensors, are acquired during the two-to-five seconds of blow-down. Current data system capabilities allow sample rates of up to 1 MHz. Data acquisition is handled by an NT system using modified Kinetics Systems Visual Basic and C++ code. The online data reduction, display and data storage is handled by 2 SUN SOLARIS UNIX Systems running custom LabView and C code. COMPRESSOR AERO RESEARCH LAB (CARL): The CARL is used to investigate turbine engine compressor aerodynamic performance. The test facility is powered by a 2,000 horsepower drive motor. The facility is unique in that it is operated in a closed-loop fashion using state-of-the-art instrumentation and measurement systems that permit on-line precision calibrations of all steady-state pressure and temperature sensors. The facility may be operated over a speed range of 6,000 to 21,500 RPM and a flow range of 15 to 65 lbs/sec. Current standard instrumentation capabilities include: 100 temperature sensors, 160 steady-state pressure sensors, 32 channels of up to 280 kHz direct digital recording, parallel analog recording of up to 26 channels, and 4 active tip-clearance devices. Both fixed and traversing instrumentation capabilities exist. Laser-illuminated flow visualization techniques, Laser Doppler Anemometry (LDV), Particle Image Velocimetry (PIV) also exist. TURBINE ENGINE FATIGUE FACILITY (TEFF): The primary mission of the TEFF is to investigate High Cycle Fatigue phenomena in turbine engine blades and disks. TEFF testing fills a gap between material coupon testing and actual engine system testing. The research focus is on the growth of cracks in actual engine components when subjected to realistic stress scenarios induced by servo-hydraulic test frames and electro-dynamic shakers. Full-scale testing of turbine engine blades and disks using advanced analysis techniques such as Laser Vibrometry and Optical Rotation/De-rotation can also be accomplished. FLOW RESEARCH LABORATORY (FRL). The FRL supports TERC programs. It is used to calibrate inlets, probes and other instrumentation devices and systems used in the CRF, TRF and CARL. This facility is also used to develop and optimize advanced non-intrusive instrumentation techniques, such as laser and hot wire anemometry systems to measure the detailed flow field within turbine engines. TURBINE ENGINE WIND TUNNEL RESEARCH FACILITIES. The two cascade facilities are used to explore boundary layer control on low-pressure turbine blading at simulated Reynolds numbers. The facility can operate at velocities up to 180 ft/sec, and turbulence levels up to 20%, with desired turning angles. The physics of secondary, transitional and separated flows are investigated and boundary layer control techniques are being researched. Key to the effective research performed in these facilities is the rapid prototyping of experimental turbine blades. TURBINE ENGINE FLAT PLATE RESEARCH FACILITY. This facility is used to research the flow physics related to boundary conditions such as turbulence intensity levels and scales along with heat transfer measurements, to evaluate turbulence models and enhance computational fluid dynamics related to turbines. The primary test unit consists of a two-foot by ten-foot flat plate section with electrical heating capability plus a five-foot unheated starting length, with zero pressure gradient. Air is supplied at a maximum of 200 fps by a wall jet with interchangeable nozzles for shaping the flow. The flat plate is equipped to investigate film cooling application techniques. This unit is also used for flow visualization using laser sheet lighting, with and without cooling jet interactions. Two additional low-speed, two-dimensional, high turbulence units are available for leading edge or stagnation area film cooling research. These two additional units are used to research the effects of pressure gradient on film cooling with high turbulence levels. Film cooling effectiveness and heat transfer coefficients are determined by transient liquid crystal or thermographic phosphor techniques. Other advanced instrumentation includes three-component and two-component laser anemometry systems, two color Particle Image Velocimetry (PIV) system for instantaneous 2D velocity measurements, three-component hot wire system, and high accuracy and precise spatial resolution arrays of 80+ thermocouples along the plate sections. AEROSPACE FUELS RESEARCH COMPLEX - This facility provides the theoretical and practical knowledge needed to fuel cutting edge propulsion technology. By combining chemistry, computer skills, and hands on technology, the Fuels Research Complex is creating more powerful, more affordable, and more environmentally friendly fuels for all aircraft and spacecraft needs.