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Airplanes -- Turbojet engines -- Blades -- Cooling

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• Airplanes -- Turbojet engines -- Blades
• Airplanes -- Turbojet engines -- Cooling

• Airplanes -- Turbojet engines -- Blades -- Cooling -- Congresses
• Airplanes -- Turbojet engines -- Blades -- Cooling -- Materials
• Airplanes -- Turbojet engines -- Blades -- Cooling -- Testing

• NACA Conference on Turbine Cooling : a compilation of the papers presented by NACA staff members, Lewis Flight Propulsion Laboratory, Cleveland, Ohio, November 9, 1949 (NACA, 1949), by Ohio) NACA Conference on Turbine Cooling (1949 : Cleveland, Lewis Flight Propulsion Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

• Potential use of ceramic coating as a thermal insulation on cooled turbine hardware (National Aeronautics and Space Administration ;, 1976), by Curt H. Liebert, Francis S. Stepka, and Lewis Research Center (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)

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

• Improved resistance to engine bird ingestion : final report : prepared for U.S. Dept. of Transportation, Federal Aviation Administration, Systems Research and Development Service (Dept. of Transportation, Federal Aviation Administration, Systems Research and Development Service ;, 1977), by Herbert B. Kaehler, Avco Corporation. Avco Lycming Division, and United States. Federal Aviation Administration. Systems Research and Development Service (page images at HathiTrust)
• Formulation of blade-flutter spectral analyses in stationary reference frame (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by Anatole P. Kurkov and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Effects of tip clearance on overall performance of transonic fan stage with and without casing treatment (National Aeronautics and Space Administration ;, 1977), by Royce D. Moore, Walter Martin Osborn, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Experimental transient turbine vane temperatures in a cascade for gas stream temperature cycling between 922 and 1644 K (1200 ̊and 2500 ̊F) (National Aeronautics and Space Administration ;, 1974), by Daniel J. Gauntner, Albert Kaufman, and Lewis Research Center (page images at HathiTrust)
• Laser anemometer measurements and computations in an annular cascade of high turning core turbine vanes (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Louis J. Goldman, Richard G. Seasholtz, and Lewis Research Center (page images at HathiTrust)
• Performance of a low-pressure fan stage with reverse flow (National Aeronautics and Space Administration ;, 1976), by Royce D. Moore, Edward R. Tysl, George W. Lewis, and Lewis Research Center (page images at HathiTrust)
• Durability of zirconia thermal-barrier ceramic coatings on air-cooled turbine blades in cyclic jet engine operation (National Aeronautics and Space Administration ;, 1976), by Lewis Research Center, Curt H. Liebert, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• An observation on tone cut-off in static test data from jet engine fans (National Aeronautics and Space Administration ;, 1975), by Marcus F. Heidmann and Lewis Research Center (page images at HathiTrust)
• Study of noise sources in a subsonic fan using measured blade pressures and acoustic theory (National Aeronautics and Space Administration ;, 1975), by Donald B. Hanson, Langley Research Center, and United Technologies Corporation. Hamilton Standard Division (page images at HathiTrust)
• Design, fabrication and acoustic tests of a 36 inch (0.914 meter) statorless turbotip fan (National Aeronautics and Space Administration ;, 1975), by E. G. Smith, W. R. Uhl, D. L. Stempert, Ames Research Center, and General Electric Company (page images at HathiTrust)
• Highly loaded multi-stage fan drive turbine : performance of initial seven configurations (National Aeronautics and Space Administration ;, 1974), by G. W. Wolfmeyer, M. W. Thomas, Lewis Research Center, and General Electric Company (page images at HathiTrust)
• Highly loaded multi-stage fan drive turbine : cascade test program (National Aeronautics and Space Administration ;, 1973), by D. G. Cherry, M. W. Thomas, T. K. Staley, Lewis Research Center, and General Electric Company (page images at HathiTrust)
• A new blade element method for calculating the performance of high and intermediate solidity axial flow fans (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Henry V. Borst, Henry V. Borst & Associates, Ames Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Design and development of the spinning mode synthesizer (National Aeronautics and Space Administration ;, 1973), by John M. Seiner, Gerhard Reethof, Langley Research Center, and Pennsylvania State University (page images at HathiTrust)
• An investigation of the flow characteristics in the blade endwall corner region (National Aeronautics and Space Administration, Scientific and Technical Information Office, 1987), by Birinchi K. Hazarika, Rishi Raj, and Lewis Research Center (page images at HathiTrust)
• Aerodynamic performance of 0.5-meter-diameter, 337-meter-per-second tip speed, 1.5-pressure-ratio, single-stage fan designed for low noise aircraft engines (National Aeronautics and Space Administration ;, 1974), by Thomas F. Gelder, George W. Lewis, and Lewis Research Center (page images at HathiTrust)
• Fortran program for computing coordinates of circular arc single and tandem turbomachinery blade sections on a plane (National Aeronautics and Space Administration; [for sale by the Clearinghouse for Federal Scientific and Technical Information, Springfield, Va.], 1970), by William D. McNally and James E. Crouse (page images at HathiTrust)
• Preliminary investigation of the strength and endurance of plastic-impregnated fiberglass compressor blades (National Advisory Committee for Aeronautics, 1955), by Donald F. Johnson, Andre J. Meyer, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Endurance evaluation of shell-supported turbine rotor blades made of timken 17-22A (S) steel (National Advisory Committee for Aeronautics, 1951), by Francis S. Stepka, John L. Clure, H. Robert Bear, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Experimental cooling-air impeller performance and turbine rotor temperatures in modified J33 split-disk rotor up to speeds of 10,000 RPM (National Advisory Committee for Aeronautics, 1952), by Alfred J. Nachtigall, Robert R. Ziemer, Charles F. Zalabak, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Effects of special leading- and trailing-edge modifications on blade temperature (National Advisory Committee for Aeronautics, 1951), by Herman H. Ellerbrock, Gordon T. Smith, Charles F. Zalabak, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Rotor blades with 34 steel tubes in cooling-air passages (National Advisory Committee for Aeronautics, 1950), by Robert O. Hickel, Gordon T. Smith, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Endurance evaluation of several tube-filled rotor blades (National Advisory Committee for Aeronautics, 1952), by Jack B. Esgar, John L. Clure, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Conduction and film cooling of leading and trailing edges of rotor blades (National Advisory Committee for Aeronautics, 1951), by Vernon L. Arne, Jack B. Esgar, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Rotor blades with split trailing edges (National Advisory Committee for Aeronautics, 1951), by Gordon T. Smith, Robert O. Hickel, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Compressor-blade vibration and performance in a J47-23 turbojet engine under conditions of rotating stall (National Advisory Committee for Aeronautics, 1955), by Morgan P. Hanson, Andre J. Meyer, Donald F. Johnson, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• An evaluation of electropolished and nonelectropolished blades of alloys refractaloy 26, M-252, and waspaloy in a J33-9 turbojet engine (National Advisory Committee for Aeronautics, 1955), by Francis Jacob Clauss, J. R. Johnston, R. A. Signorelli, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Investigation of two-stage air-cooled turbine suitable for flight at mach number of 2.5. [Part] I, , Velocity-diagram study (National Advisory Committee for Aeronautics, 1956), by James W. Miser, Warner L. Stewart, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Compressor-blade vibration of a J57-P-1 turbojet engine during exploratory operation with inlet-pressure distortions (National Advisory Committee for Aeronautics, 1955), by Morgan P. Hanson, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Improved resistance to engine bird ingestion (Dept. of Transportation, Federal Aviation Administration, Systems Research and Development Service ;, 1977), by Herbert B. Kaehler, Aviation Manufacturing Corporation. Lycoming Division, and United States. Federal Aviation Administration. Systems Research and Development Service (page images at HathiTrust)
• Study of the engine bird ingestion experience of the Boeing 737 aircraft : October 1986-September 1987 (Federal Aviation Administration Technical Center ;, 1989), by Peter W. Hovey, University of Dayton. Research Institute, and Federal Aviation Administration Technical Center (U.S.) (page images at HathiTrust)
• Study of the engine bird ingestion experience of the Boeing 737 aircraft (October 1986-September 1989) (Federal Aviation Administration Technical Center ;, 1991), by Peter W. Hovey, Joseph J. Wilson, Donald A. Skinn, University of Dayton. Research Institute, and Federal Aviation Administration Technical Center (U.S.) (page images at HathiTrust)
• Engine bird ingestion experience of the Boeing 737 aircraft : expanded data base (October 1986-September 1989) (Federal Aviation Administration Technical Center ;, 1992), by Peter W. Hovey, Joseph J. Wilson, Donald A. Skinn, University of Dayton. Research Institute, and Federal Aviation Administration Technical Center (U.S.) (page images at HathiTrust)
• Study of bird ingestions into small inlet area, aircraft turbine engines : May 1987-April 1988 (Federal Aviation Administration Technical Center ;, 1989), by Joseph P. Martino, Donald A. Skinn, University of Dayton. Research Institute, and Federal Aviation Administration Technical Center (U.S.) (page images at HathiTrust)
• Study of bird ingestions into small inlet area aircraft turbine engines (May 1987-April 1989) (Federal Aviation Administration Technical Center ;, 1991), by Joseph P. Martino, Donald A. Skinn, University of Dayton. Research Institute. Structural Integrity Division, and Federal Aviation Administration Technical Center (U.S.) (page images at HathiTrust)

• Experimental investigation of a 4 1/2-stage turbine with very high stage loading factor (National Aeronautics and Space Administration ;, 1973), by D. C. Evans, Lewis Research Center, and General Electric Company (page images at HathiTrust)
• Highly loaded multi-stage fan drive turbine-tandem blade configuration design (National Aeronautics and Space Administration ;, 1972), by D. C. Evans, G. W. Wolfmeyer, Lewis Research Center, and General Electric Company (page images at HathiTrust)

• Bonding and compatibility of aluminum oxide fibers in nickel alloy composites (National Aeronautics and Space Administration ;, 1976), by Leonard J. Westfall and Lewis Research Center (page images at HathiTrust)

• Fluctuating pressures on fan blades of a turbofan engine : flight test investigation (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1985), by James A. Schoenster and Langley Research Center (page images at HathiTrust)

• Cold-air performance of a 12.766-centimeter-tip-diameter axial-flow cooled turbine : II - effect of air ejection on turbine performance (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1977), by Jeffrey E. Haas, Milton G. Kofskey, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Flow visualization of film cooling with spanwise injection from a small array of holes and compound-angle injection from a large array (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Louis M. Russell and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Heat-transfer characteristics of partially film coded plug nozzle on a J-85 afterburning turbojet engine (U.S. National Aeronautics and Space Administration ;, 1976), by Stanley M. Nosek, David M. Straight, and Lewis Research Center (page images at HathiTrust)
• Endurance evaluation of shell-supported turbine rotor blades made of timken 17-22A (S) steel (National Advisory Committee for Aeronautics, 1951), by Francis S. Stepka, John L. Clure, H. Robert Bear, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Engine design-point performance (National Advisory Committee for Aeronautics, 1954), by James E. Hubbartt, Wilson B. Schramm, R. J. Rossbach, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Experimental cooling-air impeller performance and turbine rotor temperatures in modified J33 split-disk rotor up to speeds of 10,000 RPM (National Advisory Committee for Aeronautics, 1952), by Alfred J. Nachtigall, Robert R. Ziemer, Charles F. Zalabak, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Effects of special leading- and trailing-edge modifications on blade temperature (National Advisory Committee for Aeronautics, 1951), by Herman H. Ellerbrock, Gordon T. Smith, Charles F. Zalabak, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Rotor blades with 34 steel tubes in cooling-air passages (National Advisory Committee for Aeronautics, 1950), by Robert O. Hickel, Gordon T. Smith, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Endurance evaluation of several tube-filled rotor blades (National Advisory Committee for Aeronautics, 1952), by Jack B. Esgar, John L. Clure, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Conduction and film cooling of leading and trailing edges of rotor blades (National Advisory Committee for Aeronautics, 1951), by Vernon L. Arne, Jack B. Esgar, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Rotor blades with split trailing edges (National Advisory Committee for Aeronautics, 1951), by Gordon T. Smith, Robert O. Hickel, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)

More items available under broader and related terms at left.