Relevant bibliographies by topics / Air Force Research Laboratory (Wright-Patterson Air Force Base, Ohio)

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  2. Books
  3. Book chapters
  4. Conference papers
  5. Reports

Academic literature on the topic 'Air Force Research Laboratory (Wright-Patterson Air Force Base, Ohio)'

Author: Grafiati
Published: 4 June 2021
Last updated: 1 February 2022

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Journal articles on the topic "Air Force Research Laboratory (Wright-Patterson Air Force Base, Ohio)"

1

Piazza, Luann, William R. Ragland, Katie E. G. Thorp, and Marc C. Martin. "The Tech Trek - Mobile Research Laboratory Enhances Educational Outreach Efforts at Wright-Patterson Air Force Base, Ohio." Microscopy and Microanalysis 6, S2 (August 2000): 1158–59. http://dx.doi.org/10.1017/s1431927600038289.

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Wright-Patterson Air Force Base (near Dayton, OH) continues to expand their local community educational outreach programs with the new mobile science research laboratory, Tech Trek - Mobile Research Laboratory. Tech Trek serves surrounding communities using a 40-foot customized Blue Bird bus equipped with an R.J. Lee Instruments Limited portable scanning electron microscope (SEM). The microscope is on loan from the Materials and Manufacturing Directorate of the Air Force Research Laboratory (AFRL) at Wright-Patterson Air Force Base.The purpose of the Tech Trek program is to stimulate school science programs by making state-of-the-art, usually cost-prohibitive scientific equipment and experienced support staff accessible to schools. The program is focussed on providing opportunities for students currently in the grades six through twelve, our future scientists and engineers, to interact with role models in science and technology while being engaged in interesting scientific research. Using this mobile format combination classroom and laboratory,
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2

Piazza, Luann, William R. Ragland, Katie E. G. Thorp, and Marc C. Martin. "The Scanning Electron Microscopy Educators Program - A Unique Educational Outreach Program at Wright-Patterson Air Force Base, Ohio." Microscopy and Microanalysis 6, S2 (August 2000): 1154–55. http://dx.doi.org/10.1017/s1431927600038265.

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Wright-Patterson Air Force Base (near Dayton, OH) continues to offer a unique educational outreach program, Scanning Electron Microscopy EDucatorS (SEMEDS; pronounced sem-eds). This ten year old motivational science program provides an opportunity for students and educators to visit the Materials and Manufacturing Directorate's research laboratories, where scanning electron microscopes (SEMs) are used by scientists and engineers working in diverse areas of materials research.As a favorite motivational science program, SEMEDS serves surrounding communities by bringing students and educators on-site to Wright-Patterson Air Force Base's Air Force Research Laboratory (AFRL) to operate state-of-the-art SEMs in a real life research laboratory setting. The special features of this program include: exposure to a world-class facility, introductions to the elite researchers who work there, and an opportunity for students to operate the same equipment used by the facility researchers.SEMEDS is an after school program intended for middle school and high school students.
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3

Vaughan, Diane E., Sheldon H. Jacobson, and Derek E. Armstrong. "A New Neighborhood Function for Discrete Manufacturing Process Design Optimization Using Generalized Hill Climbing Algorithms." Journal of Mechanical Design 122, no. 2 (March 1, 2000): 164–71. http://dx.doi.org/10.1115/1.533566.

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Discrete manufacturing process design optimization can be difficult, due to the large number of manufacturing process design sequences and associated input parameter setting combinations that exist. Generalized hill climbing algorithms have been introduced to address such manufacturing design problems. Initial results with generalized hill climbing algorithms required the manufacturing process design sequence to be fixed, with the generalized hill climbing algorithm used to identify optimal input parameter settings. This paper introduces a new neighborhood function that allows generalized hill climbing algorithms to be used to also identify the optimal discrete manufacturing process design sequence among a set of valid design sequences. The neighborhood function uses a switch function for all the input parameters, hence allows the generalized hill climbing algorithm to simultaneously optimize over both the design sequences and the inputs parameters. Computational results are reported with an integrated blade rotor discrete manufacturing process design problem under study at the Materials Process Design Branch of the Air Force Research Laboratory, Wright Patterson Air Force Base (Dayton, Ohio, USA). [S1050-0472(00)01002-3]
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Hettinger, Lawrence J., Bart J. Brickman, Merry M. Roe, W. Todd Nelson, and Michael W. Haas. "Effects of Virtually-Augmented Fighter Cockpit Displays on Pilot Performance, Workload, and Situation Awareness." Proceedings of the Human Factors and Ergonomics Society Annual Meeting 40, no. 2 (October 1996): 30–33. http://dx.doi.org/10.1177/154193129604000205.

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Virtually-augmented display concepts are being developed at the US Air Force Armstrong Laboratory's Synthesized Immersion Research Environment (SIRE) Facility at Wright-Patterson Air Force Base, Ohio, for use in future USAF crew stations. These displays incorporate aspects of virtual environment technology to provide users with intuitive, multisensory representations of operationally relevant information. This paper describes an evaluation that was recently conducted to contrast the effects of conventional, F-15 types of cockpit displays and virtually-augmented, multisensory cockpit displays on pilot-aircraft system performance, workload, and situation awareness in a simulated air combat task. Eighteen military pilots from the United States, France, and Great Britain served as test pilots. The results indicate a statistically significant advantage for the virtually-augmented cockpit configuration across all three classes of measures investigated. The results are discussed in terms of their relevance for the continuing evolution of advanced crew station design.
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Fingers, R. T., and C. S. Rubertus. "Air Force Application of Advanced Magnetic Materials." MRS Proceedings 577 (1999). http://dx.doi.org/10.1557/proc-577-481.

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ABSTRACTA national initiative is underway to develop and test a more electric aircraft (MEA) and is being led by the U.S. Air Force Research Laboratory at Wright-Patterson Air Force Base, Ohio. The MEA concept is based on utilizing electric power to drive aircraft subsystems which are currently driven by a combination of hydraulic, pneumatic, electric and mechanical power transfer systems. A major objective of this effort is to increase military aircraft reliability, maintainability and supportability and to drastically reduce the need for ground support equipment. These improvements will be realized through the further advancement of key MEA technologies, including magnetic bearings, aircraft integrated power units (IPU), and starter/generators (IS/G) internal to an aircraft main propulsion engine. These advanced developments, as well as weapon and space power applications, are the driving force for the new emphasis on high temperature and high strength magnetic materials for power applications. In determining the best magnetic material for an application it is typically necessary to conduct an engineering trade-off analysis which takes into consideration mechanical behavior, electrical loss, and magnetic properties under the conditions of actual usage. New materials solutions are required to meet these challenges, as designers often find the magnetic material performance to be the technological limitation.
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6

Anthony, Richard J., John Finnegan, and John Clark. "PHANTOM COOLING EFFECTS ON ROTOR BLADE SURFACE HEAT FLUX IN A TRANSONIC FULL SCALE 1+1/2 STAGE ROTATING TURBINE." Journal of Turbomachinery, May 20, 2021, 1–13. http://dx.doi.org/10.1115/1.4051245.

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Abstract An experimental and numerical investigation of phantom cooling effects on cooled and uncooled rotating high pressure turbine blades in a full scale 1+1/2 stage turbine test is carried out. Objectives set to capture, separate, and quantify the effects of upstream vane film-cooling and leakage flows on the downstream rotor blade surface heat flux. Multiple series of tests were carried out in the Air Force Research Laboratory, Turbine Research Facility, at Wright-Patterson Air Force Base, Ohio. A non-proprietary research turbine test article is uniquely instrumented with high frequency double-sided thin film heat flux gauges custom made at AFRL. High bandwidth, time resolved surface heat flux is measured on multiple film-cooled and non-film-cooled HPT rotor blades downstream of both film-cooled and non-film-cooled vane sectors. Upstream wake passing and heat flux is characterized on both rotor pressure and suction side surfaces, along with quantifying rotor phantom cooling effects from non-uniform 1st stage vane film cooling and leakage flows. Fast response heat flux measurements quantify how rotor phantom cooling impacts the blade pressure side greatest; increasing along the pressure side towards the trailing edge. It is discovered upstream vane film-cooling alone can account for 50% of the rotor blade cooling effect, and even outweigh the rotor blade film cooling effect far from the blade showerhead holes. Added unsteady numerical simulation demonstrates how variations in inlet total temperature and incidence angle can also contribute to circumferentially non-uniform rotor heat flux.
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7

Klingshirn, C. D., M. DeWitt, R. Striebich, D. Anneken, L. Shafer, E. Corporan, M. Wagner, and D. Brigalli. "Hydroprocessed Renewable Jet Fuel Evaluation, Performance, and Emissions in a T63 Turbine Engine." Journal of Engineering for Gas Turbines and Power 134, no. 5 (March 6, 2012). http://dx.doi.org/10.1115/1.4004841.

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Due to potential beneficial environmental impacts and increased supply availability, alternative fuels derived from renewable resources are evolving on the forefront as unconventional substitutes for fossil fuel. Focus is being given to the evaluation and certification of Hydroprocessed Renewable Jet (HRJ), a fuel produced from animal fat and/or plant oils (triglycerides) by hydroprocessing, as the next potential synthetic aviation fuel. Extensive efforts have recently been performed at the Air Force Research Laboratory (AFRL) at Wright Patterson Air Force Base (WPAFB) to evaluate the potential of two HRJ fuels produced from camelina and tallow feedstocks. These have included characterization of the fuel chemical, physical fuel characteristics and Fit-for-Purpose properties (FFP). The present effort describes general combustion performance and the emission propensity of a T63-A-700 Allison turbine engine operated on the HRJs and 50/50 (by volume) HRJ/JP-8 fuel blends relative to a specification JP-8. In addition, engine and emission testing with a blend of the tallow-derived HRJ and 16% bio-derived aromatic components was completed. Fundamental engine performance characterization allows for determination of the suitability of potential synthetic fuels while quantitation of gaseous and particulate matter emissions provides an assessment of the potential environmental impact compared to current petroleum-derived fuels. In addition, an extended 150 h endurance test was performed using a 50/50 blend of tallow-derived HRJ with JP-8 to evaluate the long-term operation of the engine with the synthetic fuel blend. This paper discusses the laboratory testing performed to characterize HRJs and results from the basic engine operability and emissions studies of the alternative fuel blends.
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Books on the topic "Air Force Research Laboratory (Wright-Patterson Air Force Base, Ohio)"

1

Air Force Research Laboratory (Wright-Patterson Air Force Base, Ohio). Air Vehicles Directorate. Air Vehicles Directorate. Wright-Patterson Air Force Base, Ohio: Air Force Research Laboratory, Air Vehicles Directorate, 2004.

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Air Force Research Laboratory (Wright-Patterson Air Force Base, Ohio). Air Vehicles Directorate. Air Vehicles Directorate. Wright-Patterson Air Force Base, Ohio: Air Force Research Laboratory, Air Vehicles Directorate, 2004.

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3

Aeronautical Systems Center (U.S.). History Office., ed. Organizing for technology leadership: The historical evolution of the Wright Laboratory and the coming of AFRL, 1917-1997. Wright-Patterson AFB, Ohio: History Office, Aeronautical Systems Center, Air Force Materiel Command, 2005.

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4

Center, Lewis Research. Rotordynamic instability problems in high-performance turbomachinery 1988: Proceedings of a workshop sponsored by the Texas A&M University, College Station, Texas, the U.S. Army Research Office, Durham, North Carolina, the Aeropropulsion Laboratory, Wright-Patterson Air Force Base, Ohio, and the NASA Lewis Research Center, Cleveland, Ohio and held at Texas A&M University College Station, Texas, May 16-18, 1988. Cleveland, Ohio: Lewis Research Center, 1989.

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United States. National Aeronautics and Space Administration. Rotordynamic instability problems in high-performance turbomachinery 1986: Proceedings of a workshop sponsored by Texas A & M University, College Station, Texas, the U.S. Army Research Office, Durham, North Carolina, and the Aeropropulsion Laboratory, Wright-Patterson Air Force Base, Ohio, and held at Texas A & M University, College Station Texas, June 2-4, 1986. Washington, D.C: NASA, 1986.

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International Congress on Instrumentation in Aerospace Simulation Facilities (16th 1995 Wright-Patterson AFB, Ohio). ICIASF '95 record: International Congress on Instrumentation in Aerospace Simulation Facilities, United States Air Force, Wright Laboratory, Flight Dynamics Directorate, Wright-Patterson AFB, Ohio, USA, July 18-21, 1995. [New York, N.Y.]: Institute of Electrical and Electronics Engineers, 1995.

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Wright, Robert L. NASA/DOD control/structures interaction technology, 1989: Proceedings of a conference sponsored by NASA Langley Research Center, Hampton, Virginia, and Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, Ohio, and held in San Diego, California, January 29-February 2, 1989. Washington, D.C: National Aeronautics and Space Administration, Scientific and Technical Information Branch, 1989.

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Newsom, Jerry R. NASA/DOD controls-structures interaction technology 1989: Proceedings of a conference cosponsored by NASA Langley Research Center, Hampton, Virginia, and Wright Research Development Center, Wright-Patterson Air Force Base, Ohio, and held in San Diego, California, January 29 - February 2, 1989. Hampton, Va: Langley Research Center, 1989.

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Research and Technology Organization. Human Factors and Medicine Panel. Meting. Models for aircrew safety assessment: Uses, limitations and requirements = la modelisation des conditions de securite des equipages : applications, limitations et cahiers des charges : papers presented at the Specialists'Meeting of the Research and Technology Organization Human Factors and Medicine Panel held at Wright-Patterson Air Force Base, Ohio, USA, 26-28 October 1998. Neuilly-sur-Seine: Research and Technology Organization, 1999.

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Science and Technology: The Making of the Air Force Research Laboratory. Air Univ Pr, 2002.

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Book chapters on the topic "Air Force Research Laboratory (Wright-Patterson Air Force Base, Ohio)"

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Clarke, Edmund M., Orna Grumberg, Hiromi Hiraishi, Somesh Jha, David E. Long, Kenneth L. McMillan, and Linda A. Ness. "Verification of the Futurebus+ Cache Coherence Protocol**This research was sponsored in part by the Avionics Laboratory, Wright Research and Development Center, Aeronautical Systems Division (AFSC), U.S. Air Force, Wright-Patterson AFB, Ohio 45433-6543 under Contract F33615-90-C-1465, ARPA Order No. 7597 and in part by the National Science Foundation under Grant no. CCR-9005992 and in part by the Semiconductor Research Corporation under Contract 92-DJ-294 and in part by the U.S.-Israeli Binational Science Foundation and in part by a Japan-U.S. cooperative research grant from the Japanese Society for the Promotion of Scientific Research and in part by U.S.-Japan cooperative research grant number INT-90-16694 from the National Science Foundation.The views and conclusions contained in this document are those of the authors and should not be interpreted as representing the official policies, either expressed or implied, of the U.S. government." In Computer Hardware Description Languages and their Applications, 15–30. Elsevier, 1993. http://dx.doi.org/10.1016/b978-0-444-81641-2.50007-1.

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Conference papers on the topic "Air Force Research Laboratory (Wright-Patterson Air Force Base, Ohio)"

1

Datko, J. T., and J. A. O’Hara. "The Aeromechanical Response of an Advanced Transonic Compressor to Inlet Distortion." In ASME 1987 International Gas Turbine Conference and Exhibition. American Society of Mechanical Engineers, 1987. http://dx.doi.org/10.1115/87-gt-189.

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An advanced transonic compressor was tested in the Compressor Research Facility at the Aero Propulsion Laboratory, Wright-Patterson Air Force Base, Ohio. This compressor was designed, built, and instrumented by the General Electric Company under Air Force contract. During this test, the compressor was operated with seven different total pressure distortion screens located at the inlet, along with baseline testing of two “clean” inlet configurations. Of particular interest was the forced vibratory response of the compressor first stage integrally bladed disk (blisk) to the various distortions. This paper presents a summary of the blisk vibratory responses to each of the distortion screens. Effects of instrumentation on the dynamic response of the blisk are illustrated. In addition, the measured steady total pressure inlet distortion profiles for each screen are shown with a summary of the instrumentation used to make the various steady and dynamic measurements.
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2

Kumar, G. N., R. M. Jenkins, and U. Sahu. "Regionally Averaged Endwall Heat Transfer Correlations for a Linear Vane Cascade." In ASME 1985 International Gas Turbine Conference and Exhibit. American Society of Mechanical Engineers, 1985. http://dx.doi.org/10.1115/85-gt-19.

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This paper presents an analysis of endwall heat transfer correlations for a linear vane cascade. The data base used for the present correlations was developed originally by Detroit Diesel Allison (now Allison Gas Turbine Division, General Motors) under a contract sponsored jointly by the Air Force Aero Propulsion Laboratory, Wright-Patterson AFB, Ohio, and NASA-Lewis Research Center, Cleveland, Ohio. Correlations are made for overall averaged, regionally averaged, and locally averaged values of Stanton number. Emphasis, however, has been placed on regional averages; regions of particular interest are the cascade leading edge (pressure side) and the cascade trailing edge wake. Independent parameters used in the correlations are exit Reynolds number, exit Mach number, inlet turbulence intensity, and average wall-to-gas temperature ratio. Typical inferences to be drawn from the correlations include a minimal dependency on Mach number and a greater than expected dependency on wall-to-gas temperature ratio.
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3

Anthony, Richard J., John Finnegan, and John P. Clark. "Phantom Cooling Effects on Rotor Blade Surface Heat Flux in a Transonic Full Scale 1+1/2 Stage Rotating Turbine." In ASME Turbo Expo 2020: Turbomachinery Technical Conference and Exposition. American Society of Mechanical Engineers, 2020. http://dx.doi.org/10.1115/gt2020-15836.

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Abstract An experimental and numerical investigation of phantom cooling effects on cooled and uncooled rotating high pressure turbine blades in a full scale 1+1/2 stage turbine test is carried out. Objectives set to capture, separate, and quantify the effects of upstream vane film-cooling and leakage flows on the downstream rotor blade surface heat flux. Multiple series of 1+1/2 stage rotating high pressure turbine tests were carried out in the Air Force Research Laboratory, Turbine Research Facility, at Wright-Patterson Air Force Base, Ohio. A non-proprietary research turbine test article is uniquely instrumented with high frequency double-sided thin film heat flux gauges custom made at AFRL. High bandwidth, time resolved surface heat flux is measured on multiple film-cooled and non-film-cooled HPT rotor blades downstream of both film-cooled and non-film-cooled vane sectors. Upstream wake passing and heat flux is characterized on both rotor pressure and suction side surfaces, along with quantifying rotor phantom cooling effects from nonuniform 1st stage vane film cooling and leakage flows. Fast response heat flux measurements quantify how rotor phantom cooling impacts the blade pressure side greatest; increasing along the pressure side towards the trailing edge. It is discovered upstream vane film-cooling alone can account for 50% of the rotor blade cooling effect, and even outweigh the rotor blade film cooling effect far from the blade showerhead holes. Added unsteady aero numerical simulation demonstrate how variations in inlet total temperature and incidence angle can also contribute to circumferentially non-uniform rotor heat flux. Better understanding from this investigation aids modelling and design efforts in optimizing film cooling performance in real high pressure turbine flow fields. Understanding the behavior of such non-uniform circumferential rotor phantom cooling effects can be critical to optimize the efficiency, fuel consumption, range, and durability of advanced turbomachines.
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4

Stringham, G. D., B. N. Cassem, T. C. Prince, and P. F. Yeung. "Design and Development of a Nine Stage Axial Flow Compressor for Industrial Gas Turbines." In ASME 1998 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1998. http://dx.doi.org/10.1115/98-gt-140.

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A nine stage industrial axial flow compressor with a pressure ratio of 9.1:1 was designed, built and rig tested. The modern technology and design tools developed by government/aircraft engine compressor technologists were used for an industrial gas turbine application. The compressor was designed with “arbitrary” airfoil blading including CFD analysis in all blade rows. Flowpath contouring in the hub region of the rotors was used to decrease losses. The compressor rig was tested at the Compressor Research Facility at Wright Patterson Air Force Base in Dayton, Ohio. Extensive testing included determining the impact of stator leading edge instrumentation on performance. The compressor demonstrated excellent efficiency and stall margin in its first build. This paper describes the aerodynamic design, test instrumentation and test results.
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Keith, Brian D., Dipan K. Basu, and Charles Stevens. "Aerodynamic Test Results of Controlled Pressure Ratio Engine (COPE) Dual Spool Air Turbine Rotating Rig." In ASME Turbo Expo 2000: Power for Land, Sea, and Air. American Society of Mechanical Engineers, 2000. http://dx.doi.org/10.1115/2000-gt-0632.

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The Controlled Pressure Ratio Engine (COPE) is a fourth generation variable cycle engine combining the attributes of a high temperature turbojet (high dry specific thrust and low Max power SFC) with those of a turbofan (low specific thrust and low part power SFC). Variation in turbine flow function is achieved by the Controlled Area Turbine (CAT) Nozzle concept, which utilizes an innovative cam driven scheme to achieve desired flow function changes while minimizing loss in aerodynamic performance. The single stage high pressure turbine is coupled with a two stage vaneless counter-rotating low pressure turbine. The COPE Turbine System Aero/Heat Transfer Design Validation Program, jointly conducted by GE Aircraft Engines and Allison Advanced Development Company under the direction of the Air Force Research Laboratory at Wright-Patterson Air Force Base, has succeeded in demonstrating advanced turbine technologies that will be utilized on the XTE76, XTE77, and Joint Strike Fighter engines. The various phases of this program evaluated variable area nozzle performance, high pressure turbine performance under the influence of varying flow function, and dual spool testing of the vaneless, counter-rotating low pressure turbine. Evaluation of the three phases demonstrated the aerodynamic capability of these turbine technologies, meeting pre-test predictions in overall and component efficiencies.
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Poondru, Shirdish, Urmila Ghia, and Karman Ghia. "Large-Eddy Simulation of Transitional Flow Through a Low-Pressure Turbine Cascade." In ASME 2006 2nd Joint U.S.-European Fluids Engineering Summer Meeting Collocated With the 14th International Conference on Nuclear Engineering. ASMEDC, 2006. http://dx.doi.org/10.1115/fedsm2006-98317.

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Subsonic, transitional flow through a low-pressure turbine (LPT) cascade is investigated using high-order compact difference scheme in conjunction with large-eddy simulation (LES). Three-dimensional simulations are performed at chord inlet Reynolds numbers (Re) of 25,000 and 50,000. The inlet Mach number is approximately 0.06. An MPI-based higher-order accurate, Chimera version of the FDL3DI flow solver developed by the Air Force Research Laboratory at Wright Patterson Air Force base, is extended for the present turbomachinery application. The implicit solver is based on an approximate factored time-integration method of Beam and Warming. Fourth-order compact-difference formulations are used for discretizing spatial derivatives in conjunction with sixth-order non-dispersive filtering. Solutions are obtained both with and without a sub-grid scale (SGS) model. A dual topology, 16-block, structured grid generated using GridPro is utilized for all simulations. The flow features are examined, and the results for both LES approaches are compared to each other, and with experimental data.
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7

Klingshirn, Christopher D., Matthew J. DeWitt, Rich Striebich, David Anneken, Linda Shafer, Edwin Corporan, Matt Wagner, and Dean Brigalli. "Hydroprocessed Renewable Jet Fuel Evaluation, Performance, and Emissions in a T-63 Turbine Engine." In ASME 2011 Turbo Expo: Turbine Technical Conference and Exposition. ASMEDC, 2011. http://dx.doi.org/10.1115/gt2011-46572.

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Due to potential beneficial environmental impacts and increased supply availability, alternative fuels derived from renewable resources are evolving on the forefront as unconventional substitutes for fossil fuel. Focus is being given to the evaluation and certification of Hydroprocessed Renewable Jet (HRJ), a fuel produced from animal fat and/or plant oils (triglycerides) by hydroprocessing, as the next potential synthetic aviation fuel. Extensive efforts have recently been performed at the Air Force Research Laboratory (AFRL) at Wright Patterson Air Force Base (WPAFB) to evaluate the potential of two HRJ fuels produced from camelina and tallow feedstocks. These have included characterization of the fuel chemical and physical fuel characteristics, and Fit-for-Purpose properties (FFP). The present effort describes general combustion performance and emission propensity of a T63-A-700 Allison turbine engine operated on the HRJs and 50/50 (by volume) HRJ/JP-8 fuel blends relative to a specification JP-8. In addition, engine and emission testing with a blend of the tallow-derived HRJ and 16% bio-derived aromatic components was completed. Fundamental engine performance characterization allows for determination of the suitability of potential synthetic fuels while quantitation of gaseous and particulate matter emissions provides an assessment of the potential environmental impact compared to current petroleum-derived fuels. In addition, an extended 150 hour endurance test was performed using a 50/50 blend of tallow-derived HRJ with JP-8 to evaluate the long-term operation of the engine with the synthetic fuel blend. This paper discusses the laboratory testing performed to characterize HRJs and results from the basic engine operability and emissions studies of the alternative fuel blends.
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8

Mawid, M. A., C. A. Arana, and B. Sekar. "Application of a Thermal-Hydraulic Management Model to Gas Turbine Combustors and Fuel Systems." In ASME 1999 International Gas Turbine and Aeroengine Congress and Exhibition. American Society of Mechanical Engineers, 1999. http://dx.doi.org/10.1115/99-gt-054.

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An advanced thermal management analysis tool, named Advanced Thermal Hydraulic Energy Network Analyzer (ATHENA), has been used to simulate a fuel system for gas turbine engines. The ATHENA tool was modified to account for JP-8/dodecane fuel properties. The JP-8/dodecane fuel thermodynamic properties were obtained from the SUPERTRAP property program. A series of tests of a fuel system simulator located at the Air Force Research Laboratory (AFRL)/Wright Patterson Air Force Base were conducted to characterize the steady state and dynamic behavior of the fuel system. Temperature, pressures and fuel flows for various fuel pump speeds, pressure rise and flow control valve stem positions (orifice areas), heat loads and engine fuel flows were measured. The predicted results were compared to the measured data and found to be in excellent agreement. This demonstrates the capability of the ATHENA tool to reproduce the experimental data and, consequently, its validity as an analysis tool that can be used to carry out analysis and design of fuel systems for advanced gas turbine engines. However, some key components in the fuel system simulator such as control components, which regulate the engine fuel flow based on predetermined parameters such as fan speed, compressor inlet and exit pressures and temperatures, combustor pressure, turbine temperature and power demand, were not simulated in the present investigation due to their complex interactions with other components functions. Efforts are currently underway to simulate the operation of the fuel system components with control as the engine fuel flow and power demands are varied.
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Kiser, J. Douglas, Narottam P. Bansal, James Szelagowski, Jagdish (Jack) Sokhey, Tab Heffernan, Joseph Clegg, Anthony Pierluissi, et al. "Oxide/Oxide Ceramic Matrix Composite (CMC) Exhaust Mixer Development in the NASA Environmentally Responsible Aviation (ERA) Project." In ASME Turbo Expo 2015: Turbine Technical Conference and Exposition. American Society of Mechanical Engineers, 2015. http://dx.doi.org/10.1115/gt2015-43593.

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LibertyWorks®, a subsidiary of Rolls-Royce Corporation, first studied CMC (ceramic matrix composite) exhaust mixers for potential weight benefits in 2008. Oxide CMC potentially offered weight reduction, higher temperature capability, and the ability to fabricate complex-shapes for increased mixing and noise suppression. In 2010, NASA was pursuing the reduction of NOx emissions, fuel burn, and noise from turbine engines in Phase I of the Environmentally Responsible Aviation (ERA) Project (within the Integrated Systems Research Program). ERA subtasks, including those focused on CMC components, were being formulated with the goal of maturing technology from Proof of Concept Validation (Technology Readiness Level 3 (TRL 3)) to System/Subsystem or Prototype Demonstration in a Relevant Environment (TRL 6). In April 2010, the NASA Glenn Research Center (GRC) and Rolls-Royce (RR) jointly initiated a CMC Exhaust System Validation Program within the ERA Project, teaming on CMC exhaust mixers for subsonic jet engines. The initial objective was to fabricate and characterize the performance of a 0.25 scale low bypass exhaust system that was based on a RR advanced design, with a 16-lobe oxide/oxide CMC mixer and tail cone (center body). Support Services, LLC (Allendale, MI) and COI Ceramics, Inc. (COIC) supported the design of a mixer assembly that consisted of the following oxide/oxide CMC components mounted on separate metallic attachment flanges: a) a lobed mixer and outer fan shrouds, and b) a tail cone. TRL 4 (Component/Subscale Component Validation in a Laboratory Environment) was achieved in a cost-effective manner through subscale rig validation of the aerodynamic and acoustic performance via testing at ASE FluiDyne (Plymouth, MN) and at NASA GRC, respectively. This encouraged the NASA/ RR/COIC team to move to the next phase of component development; full scale CMC mixer design for a RR AE3007 engine. COIC fabricated the full scale CMC mixer, which was vibration tested at GRC under conditions simulating the structural and dynamic environment of a mixer. Air Force Research Laboratory (AFRL, Wright-Patterson Air Force Base (WPAFB)) provided test support by assisting with instrumentation and performing 3D laser vibrometry to identify the mixer mode shapes and modal frequencies over the engine operating range. Successful vibration testing demonstrated COIC’s new process for fabricating full scale CMC mixers and the durability of the Oxide CMC component at both room and elevated temperatures. A TRL≈5 (Component Validation in a Relevant Environment) was attained and the CMC mixer was cleared for ground testing on a Rolls-Royce AE3007 engine for performance evaluation to achieve TRL 6.
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Poondru, Shirdish, Urmila Ghia, and Karman Ghia. "Active Flow Control on Low-Pressure Turbine Blades Using Synthetic Jets." In ASME 2006 2nd Joint U.S.-European Fluids Engineering Summer Meeting Collocated With the 14th International Conference on Nuclear Engineering. ASMEDC, 2006. http://dx.doi.org/10.1115/fedsm2006-98321.

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Abstract:
The operating Reynolds numbers (Re) for a low-pressure turbine (LPT) in an aircraft engine can drop below 25,000 during high-altitude cruise conditions. At these low Reynolds numbers, the boundary layer on the LPT blade is largely laminar, and is susceptible to separation on the aft portion of the blade suction surface. This separation is detrimental and causes a significant loss in the engine efficiency. The objective of the current research is to control this separation, and minimize the associated losses by numerically implementing an active flow control strategy. Unlike passive flow control techniques, active flow control (AFC) techniques can be turned on and off depending on the requirement for flow control. In the present paper, we numerically investigate the flow through an LPT cascade at a chord inlet Reynolds number of 25,000 with active separation control using synthetic jets and synthetic vortex-generator jets (VGJ’s). Synthetic jets hold an advantage over steady or pulsed jets in that they require no net mass flow, i.e., synthetic jets are formed entirely from the working fluid of the flow system in which they are deployed and, thus, can transfer linear momentum to the flow system without net mass injection across the flow boundary. In the LPT environment, this means that no compressor bleed air is required. While LPT separation control using steady and pulsed VGJs has been numerically investigated before, AFC on an LPT blade by synthetic jets and synthetic VGJs has not yet been numerically investigated. The geometrical difference between a synthetic jet and synthetic VGJ is the angle at which the jet enters the main flow. A synthetic jet enters the main flow normal to the surface, and on the other hand, a synthetic VGJ enters at a certain angle to the wall (pitch angle) and at a certain angle to the main flow (skew angle). For the present case, the VGJs are oriented at 30° to the surface and 90° to the main flow. In addition to the angle at which these two jets enter the main flow, these flow control mechanisms differ in the way they delay or avoid separation. Synthetic jets generate turbulent spots which energize the flow, whereas synthetic VGJ’s generate streamwise vortices which enhance mixing. The relative magnitudes of the effects of turbulence and streamwise vortices in enhancing mixing are being investigated. The results for both control mechanisms will be compared to each other, and with experimental data. An MPI-based higher-order accurate, Chimera version of the FDL3DI flow solver developed by the Air Force Research Laboratory at Wright Patterson Air Force Base, is extended for the present turbomachinery application.
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Reports on the topic "Air Force Research Laboratory (Wright-Patterson Air Force Base, Ohio)"

1

Still, Kenneth R. 2000 Command History for Naval Health Research Center Detachment (Toxicology), Wright-Patterson Air Force Base, Ohio. Fort Belvoir, VA: Defense Technical Information Center, March 2000. http://dx.doi.org/10.21236/ada414746.

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2

Still, Kenneth R., and William K. Alexander. 1999 Command History for Naval Health Research Center Detachment (Toxicology) Wright-Patterson Air Force Base, Ohio. Fort Belvoir, VA: Defense Technical Information Center, March 2000. http://dx.doi.org/10.21236/ada376598.

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