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Turbomachines -- Bearings -- Testing

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• Turbomachines -- Bearings
• Turbomachines -- Testing

• Evaluation of drilled-ball bearings at DN values to three million (National Aeronautics and Space Administration ;, 1972), by P. W. Holmes, Lewis Research Center, and United Aircraft Corporation. Pratt & Whitney Aircraft Division (page images at HathiTrust)
• Experiments on the steady state characteristics of herringbone-grooved air-lubricated journal bearings (National Aeronautics and Space Administration ;, 1969), by Robert E. Cunningham, William J. Anderson, David P. Fleming, and Lewis Research Center (page images at HathiTrust)

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

• 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)

• Steady-state and transient analysis of a squeeze film damper bearing for rotor stability (National Aeronautics and Space Administration ;, 1975), by L. E. Barrett, Edgar J. Gunter, Lewis Research Center, and University of Virginia (page images at HathiTrust)

• Performance of a tandem-rotor/tandem-stator conical-flow compressor designed for a pressure ratio of 3 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Jerry R. Wood, Lawrence F. Schumann, Albert Kimsey Owen, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Analytical and experimental study of flow phenomena in noncavitating rocket pump inducers (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by B. Lakshminarayana, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)

• Effect of inducer inlet and diffuser throat areas on performance of a low pressure ratio sweptback centrifugal compressor (National Aeronautics and Space Administration ;, 1975), by Hugh A. Klassen and Lewis Research Center (page images at HathiTrust)
• Experimental performance of a 16.10-centimeter-tip-diameter sweptback centrifugal compressor designed for a 6:1 pressure ratio (National Aeronautics and Space Administration ;, 1977), by Hugh A. Klassen, Lawrence F. Schumann, Jerry R. Wood, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Performance of a tandem-rotor/tandem-stator conical-flow compressor designed for a pressure ratio of 3 (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1982), by Jerry R. Wood, Lawrence F. Schumann, Albert Kimsey Owen, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Performance of a low-pressure-ratio centrifugal compressor with four diffuser designs (National Aeronautics and Space Administration ;, 1973), by Hugh A. Klassen and Lewis Research Center (page images at HathiTrust)
• Design and tests of a six-stage axial-flow compressor having a tip speed of 550 feet per second and a flat operating characteristic at constant speed (National Advisory Committee for Aeronautics, 1958), by Willard R. Westphal, John W. Maynard, Langley Aeronautical Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Rotating stall investigation of the 0.72 hub-tip ratio single-stage compressor (National Advisory Committee for Aeronautics, 1954), by Robert W. Graham, Vasily D. Prian, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series E. (National Advisory Committee for Aeronautics, 1944), by J. Austin King, Owen W. Regan, Aircraft Engine Research Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

• A computer program for variable-geometry single-stage axial compressor test data analysis (UD0400) (Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command, 1981), by C. Herbert Law and Air Force Wright Aeronautical Laboratories. Aero Propulsion Laboratory (page images at HathiTrust)

• Optimization of compressor vane and bleed settings (Aero Propulsion Laboratory, Wright Aeronautical Laboratories, Air Force Systems Command, 1981), by J. E. Garberoglio, W. L. Bourdreaux, J. O. Song, and Pratt & Whitney Aircraft Group. Government Products Division (page images at HathiTrust)

• NACA Wartime Reports. Series E. (National Advisory Committee for Aeronautics, 1945), by Aircraft Engine Research Laboratory and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

• A comparison of sound power levels from portable air compressors based upon test methodologies adopted by U.S. EPA and the CEC. (U.S. Environmental Protection Agency, Office of Noise Abatement and Control ;, 1980), by Commission of the European Communities. Environment and Consumer Protection Service and United States Office of Noise Abatement and Control (page images at HathiTrust)

• Inspection and test of air and other gas compressors. (Headquarters, Dept. of the Army, 1991), by United States. Department of the Army (page images at HathiTrust)

• Design and performance of a high-pressure-ratio, highly loaded axial-flow transonic compressor space (National Aeronautics and Space Administration ;, 1974), by George W. Lewis, Edward R. Tysl, Lonnie Reid, and Lewis Research Center (page images at HathiTrust)
• Frequency response of an axial-flow compressor exposed to inlet pressure perturbations (National Aeronautics and Space Administration ;, 1974), by Edward J. Milner, Francis J. Paulovich, Leon M. Wenzel, and Lewis Research Center (page images at HathiTrust)
• Performance of a transonic compressor rotor with an aspect ratio of 6.5 (National Aeronautics and Space Administration ;, 1974), by Lonnie Reid, Edward R. Tysl, and Lewis Research Center (page images at HathiTrust)

• Performance of a 1.15-pressure-ratio axial-flow fan stage with a blade tip solidity of 0.5 (National Aeronautics and Space Administration ;, 1974), by Walter Martin Osborn, Ronald J. Steinke, and Lewis Research Center (page images at HathiTrust)

• Investigation of an impulse axial-flow compressor rotor over a range of blade angles (National Advisory Committee for Aeronautics, 1950), by Wallace M. Schulze, Willard R. Westphal, John R. Erwin, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Design, over-all performance and stall characteristics (National Advisory Committee for Aeronautics, 1954), by George W. Lewis, G. K. Serovy, Francis C. Schwenk, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)

• NACA Wartime Reports. Series E. (National Advisory Committee for Aeronautics, 1942), by Herman H. Ellerbrock, Arthur W. Goldstein, Aircraft Engine Research Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

• Static sea-level performance of an axial-flow-compressor turbojet engine with an air-cooled turbine (National Advisory Committee for Aeronautics, 1955), by Reeves P. Cochran, Robert P. Dengler, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Evaluation of a compressor bleed system for rim cooling the turbine wheel of a turbojet engine (National Advisory Committee for Aeronautics, 1954), by C. R. Morse, R. H. Kemp, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

• Off-design correlation for losses due to part-span dampers on transonic rotors. (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by William B. Roberts, Donald M. Sandercock, James E. Crouse, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Overall and blade-element performance of a 1.20-pressure-ratio fan stage at design blade setting angle (National Aeronautics and Space Administration ;, 1974), by George W. Lewis, Edward R. Tysl, and Lewis Research Center (page images at HathiTrust)
• Overall and blade element performance of a 1.20-pressure-ratio fan stage with rotor blades reset -5 ̊ (U.S. National Aeronautics and Space Administration ;, 1976), by George W. Lewis, Royce D. Moore, Walter Martin Osborn, and Lewis Research Center (page images at HathiTrust)
• Overall and blade element performance of a 1.20 pressure ratio fan stage with rotor blades reset -7 ̊ (U.S. National Aeronautics and Space Administration ;, 1976), by George W. Lewis, George Kovich, and Lewis Research Center (page images at HathiTrust)

• Inspection and test of air and other gas compressors. (Headquarters, Dept. of the Army, 1991), by United States. Department of the Army (page images at HathiTrust)

• Calibration procedure for compressor bleed valve test stand, Lycoming, model LTCT421. (Headquarters, Dept. of the Army, 1984), by United States. Department of the Army (page images at HathiTrust)

• Damage of mechanical pump impellers ... (NASA, 1965), by R. S. Kulp, United Aircraft Corporation. Pratt & Whitney Aircraft Division, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Performance evaluation of a two-stage axial-flow turbine for two values of tip clearance (National Aeronautics and Space Administration ;, 1968), by Milton G. Kofskey, William J. Nusbaum, and Lewis Research Center (page images at HathiTrust)
• Investigation of the general stress distribution in impeller wheels (Wright-Patterson Air Force Base, Ohio : Directorate of Materials and Processes, Aeronautical Systems Division, Air Force Systems Command, [1963], 1963), by W. Dettmering, Wilhelm Soetebeer, Rheinisch-Westfälische Technische Hochschule Aachen, and United States. Air Force. Systems Command. Aeronautical Systems Division (page images at HathiTrust)

• NASA TN D-4392 (National Aeronautics and Space Administration ;, 1968), by Roy G. Stabe, John F. Kline, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)

• Performance of two-stage fan having low-aspect-ratio, first-stage rotor blading (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1979), by Donald C. Urasek, Walter S. Cunnan, William T. Gorrell, Propulsion Laboratory (U.S.), and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)

• 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)