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Turbomachines -- Diffusers

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• Turbomachines
• Diffusers
• Turbomachines -- Fluid dynamics

• Turbomachines -- Diffusers -- Testing

• Performance of a vortex-controlled diffuser in an annular swirl-can combustor at inlet Mach numbers up to 0.53 (National Aeronautics and Space Administration, Scientific and Technical Information Office, 1979), by John M. Smith (page images at HathiTrust)

Items below (if any) are from related and broader terms.

• Three-component laser anemometer measurement systems (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Division ;, 1991), by Louis J. Goldman and Lewis Research Center (page images at HathiTrust)
• Performance of inlet stage of transonic compressor (National Aeronautics and Space Administration ;, 1976), by Donald C. Urasek, George W. Lewis, Ronald J. Steinke, and Lewis Research Center (page images at HathiTrust)
• Performance of a transonic fan stage designed for a low meridional velocity ratio (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Royce D. Moore, Walter Martin Osborn, George W. Lewis, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Lewis Research Center (page images at HathiTrust)
• Experimental apparatus for investigation of fan aeroelastic instabilities in turbomachinery (National Aeronautics and Space Administration ;, 1977), by William H. Jones and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Straight cylindrical seal for high-performance turbomachines (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1987), by Robert C. Hendricks (page images at HathiTrust)
• Analytic investigation of effect of end-wall contouring on stator performance (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Robert J. Boyle, Louis J. Goldman, Harold E. Rholik, and Lewis Research Center (page images at HathiTrust)
• Detailed flow measurements in casing boundary layer of 427-meter-per-second-tip-speed two-stage fan with casing treatment (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by William T. Gorrell and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Damping seals for turbomachinery (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by George L. Von Pragenau, George C. Marshall Space Flight Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Aerodynamic effect of a honeycomb rotor tip shroud on a 50.8-centimeter-tip-diameter core turbine (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Thomas P. Moffitt, Warren J. Whitney, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Research and development of high-performance axial-flow turbomachinery (National Aeronautics and Space Administration, 1968), by J. T. McCabe, P. W. Curwen, P. Bolan, United States National Aeronautics and Space Administration, Lewis Research Center, and Pratt & Whitney Aircraft Company (page images at HathiTrust)
• Thermal effects on the clearance and stiffness of foil journal bearings for a Brayton cycle turboalternator (National Aeronautics and Space Administration ;, 1972), by A. Eshel, Lewis Research Center, and Ampex Corporation (page images at HathiTrust)
• Design, fabrication, and performance of foil journal bearing for the brayton rotating unit (National Aeronautics and Space Administration ;, 1973), by Lazar Licht, M. Branger, Lewis Research Center, and Ampex Corporation (page images at HathiTrust)
• A FORTRAN program for calculating three-dimensional, inviscid, rotational flows with shock waves in axial compressor blade rows : user's manual (National Aeronautical and Space Administration, Scientific and Technical Information Office ;, 1982), by William T. Thompkins, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, Gas Turbine and Plasma Dynamics Laboratory, and Lewis Research Center (page images at HathiTrust)
• Dynamic electrical characteristics of a 400-Hertz Brayton cycle turboalternator and controls (National Aeronautics and Space Administration ;, 1971), by Martin E. Valgora, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5761 (National Aeronautics and Space Administration :, 1970), by Laurence J. Heidelberg, Carl Weigel, Calvin L. Ball, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust; US access only)
• FORTRAN program for calculating compressible laminar and turbulent boundary layers in arbitrary pressure gradients (National Aeronautics and Space Administration ;, 1970), by William D. McNally (page images at HathiTrust)
• Analytical investigation of some three-dimensional flow problems in turbomachines (National Advisory Committee for Aeronautics, 1952), by Frank E. Marble, Irving Michelson, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• A visualization study of secondary flows in cascades (National Advisory Committee for Aeronautics, 1953), by Arthur G. Hansen, George R. Costello, Howard Z. Herzig, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Erosion study in turbomachinery affected by coal and ash particles : phase 1. (Dept. of Energy ;, 1976), by Cincinnati. University. Dept. of Aerospace Engineering and Applied Mechanics, Widen Tabakoff, and United States. Department of Energy (page images at HathiTrust; US access only)
• ERB Engine Research Building turbomachinery facilities (Aeropropulsion Facilities & Experiments Division,National Aeronautics and Space Administration, Lewis Research Center, 1994), by Lewis Research Center. Aeropropulsion Facilities & Experiments Division (page images at HathiTrust)
• Contractors' meeting in turbulence and rotating flows (Arlington, Virginia : Air Force Office of Scientific Research, Air Research and Development Command, United States Air Force, 1999., 1999), by Thomas Beutner and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• The acoustic characteristics of turbomachinery cavities (National Aeronautics and Space Administration, ;, 1995), by M. J. Lucas, George C. Marshall Space Flight Center, and Wyle Research (Firm) (page images at HathiTrust)
• Conceptual design study of a nuclear Brayton turboalternator-compressor (National Aeronautics and Space Administration ;, 1971), by General Electric Company and Lewis Research Center (page images at HathiTrust)

• Liquid rocket engine turbopump shafts and couplings (National Aeronautics and Space Administration, 1972), by L. K. Severud and C. C. Purdy (page images at HathiTrust; US access only)
• Test-engine and inlet performance of an aircraft used for investigating flight effects on fan noise (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by Robert A. Golub, John S. Preisser, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Effects of diffusion factor, aspect ratio, and solidity on overall performance of 14 compressor middle stages (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Werner R. Britsch, Mark R. Laessig, Walter Martin Osborn, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Aerodynamic performances of three fan stator designs operating with rotor having tip speed of 337 meters per second and pressure ratio of 1.54 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1980), by Thomas F. Gelder, Genevieve M. Esgar, James F. Schmidt, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust; US access only)
• Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ratio of 2.05 (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Royce D. Moore, Lonnie Reid, United States. National Aeronautics and Space Administration. Scientific and Technical Information Office, and Lewis Research Center (page images at HathiTrust)
• High-speed laser anemometer system for intrarotor flow mapping in turbomachinery (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by J. Anthony Powell, Richard G. Seasholtz, Anthony J. Strazisar, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Lewis Research Center (page images at HathiTrust)
• Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.19 and 1.26, respectively, and with design pressure ration of 1.82 (National Aeronautics and Space Administration, Scientific and Technical Information Office, 1978), by Lonnie Reid and Royce D. Moore (page images at HathiTrust)
• Design and performance of a 427-meter-per-second-tip-speed two-stage fan having a 2.40 pressure ratio (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Walter S. Cunnan, William Stevans, Donald C. Urasek, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Aerodynamic performance of a 1.35-pressure-ratio axial-flow fan stage (Natioanl Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Walter Martin Osborn, Ronald J. Steinke, Royce D. Moore, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Aerodynamic performance of a 1.20-pressure-ratio fan stage designed for low noise (National Aeronautics and Space Administration ;, 1976), by George W. Lewis, Royce D. Moore, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• Effect of rotor meridional velocity ratio on response to inlet radial and circumferential distortion (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Nelson L. Sanger, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Aerodynamic performance of 1.38-pressure-ratio, variable-pitch fan stage (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Royce D. Moore, Walter Martin Osborn, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.78, respectively, and with design pressure ratio of 1.82 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Royce D. Moore, Lonnie Reid, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Three-step cylindrical seal for high-performance turbomachines (National Aeronautics and Space Administration, 1987), by Robert C. Hendricks and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Improved method for calculating transonic velocities on blade-to-blade stream surfaces of a turbomachine (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by Jerry R. Wood, United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch, and Lewis Research Center (page images at HathiTrust)
• Performance of single-stage axial-flow transonic compressor with rotor and stator aspect ratios of 1.63 and 1.77, respectively, and with design pressure ratio of 2.05 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Royce D. Moore, Lonnie Reid, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Design and fabrication of a high-performance Brayton cycle radial-flow gas generator (National Aeronautics and Space Administration :, 1967), by AiResearch Manufacturing Company of Arizona (page images at HathiTrust)
• Cascade tests of serrated leading edge blading at high subsonic speeds (National Aeronautics and Space Administration ;, 1974), by E. G. Smith, H. D. Sowers, Ames Research Center, and General Electric Company (page images at HathiTrust)
• Experimental and theoretical investigation of three-dimensional turbulent boundary layers and turbulence characteristics inside an axial flow inducer passage (National Aeronautics and Space Administration ;, 1977), by A. K. Anand, B. Lakshminarayana, Pennsylvania State University, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Development of a multiple-parameter nonlinear perturbation procedure for transonic turbomachinery flows : preliminary application to design/optimization problems (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1983), by Stephen S. Stahara, John R. Spreiter, J. P. Elliott, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• FORTRAN program for quasi-three-dimensional calculation of surface velocities and choking flow for turbomachine blade rows (National Aeronautics and Space Administration ;, 1971), by Theodore Katsanis (page images at HathiTrust)
• FORTRAN program for calculating transonic velocities on a blade-to-blade stream surface of a turbomachine (National Aeronautics and Space Administration ;, 1969), by Theodore Katsanis, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• FORTRAN program for calculating velocities and streamlines on a blade-to-blade stream surface of a tandem blade turbomachine (National Aeronautics and Space Administration ;, 1969), by Theodore Katsanis, William D. McNally, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• NASA TN D-5672 (National Aeronautics and Space Administration ; [For sale for Federal Scientific and Technical Information, Springfield, Virginia 22151], 1970), by James S. Fear, Robert R. Tacina, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Analysis of limitations imposed on one-spool turbojet-engine designs by compressors and turbines at flight Mach numbers of 0, 2.0, and 2.8 (National Advisory Committee for Aeronautics, 1954), by Richard H. Cavicchi, Robert E. English, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Aerodynamic performance of axial-flow fan stage operated at nine inlet guide vane angles (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Royce D. Moore, Lonnie Reid, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)

• Computer-aided design analysis of 57-mm, angular-contact, cryogenic turbopump bearings (National Aeronautics and Space Administration, Scientific and Technical Information Division ;, 1988), by Elizabeth S. Armstrong, Harold H. Coe, and Lewis Research Center (page images at HathiTrust)
• Experimental evaluation of foil-supported resilient-pad gas-lubricated thrust bearing (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by Zolton N. Nemeth and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Evaluation of chromium oxide and molybdenum disulfide coatings in self-acting stops of an air-lubricated Rayleigh step thrust bearing (National Aeronautics and Space Administration ;, 1974), by Zolton N. Nemeth and Lewis Research Center (page images at HathiTrust)
• Evaluation of high-temperature bearing cage materials (National Aeronautics and Space Administration ;, 1967), by Erwin V. Zaretsky, William J. Anderson, and Lewis Research Center (page images at HathiTrust)

More items available under broader and related terms at left.