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

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

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). Air Vehicles Directorate"

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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4

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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5

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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Books on the topic "Air Force Research Laboratory (Wright-Patterson Air Force Base, Ohio). Air Vehicles Directorate"

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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2

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

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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5

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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6

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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7

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

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8

Duffner, Robert W. Science and Technology: The Making of the Air Force Research Laboratory. University Press of the Pacific, 2002.

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9

Wright Laboratory (Wright-Patterson Air Force Base, Ohio). Failure Analysis Section, ed. Don't let failures keep you grounded!: Technical guidance specification requirements : failure analysis : research and development quality solutions. Wright-Patterson AFB, OH: Wright Laboratory's Materials Directorate, Failure Analysis Section, 1994.

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10

Vortex Flow Aerodynamics : Volume I: Proceedings of a conference sponsored by the NASA Langley Research Center, Hampton, Virginia, and the Air Force Wright Aeronautical Laboratories, Flight Dynamics Laboratory, Wright-Patterson Air Force Base, Ohio, and held at Langley Research Center, October 8-10, 1985. Washington, D.C: NASA, Scientific and Technical Information Branch, 1986.

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

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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