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Gas-turbines -- Blades

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• Gas-turbines
• Blades
• Turbines -- Blades
• Gas-turbines -- Aerodynamics
• Gas-turbines -- Fluid dynamics

• Gas-turbines -- Blades -- Cooling
• Gas-turbines -- Blades -- Materials
• Aircraft gas-turbines -- Blades

• Low cost FM oscillator for capacitance type of blade tip clearance measurement system (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1987), by John P. Barranger and Lewis Research Center (page images at HathiTrust)
• Cold-air study of the effect on turbine stator blade aerodynamic performance of coolant ejection from various trailing-edge slot geometries (National Aeronautics and Space Administration ;, 1974), by Herman W. Prust, Wayne M. Bartlett, and Lewis Research Center (page images at HathiTrust)
• Review and status of heat-transfer technology for internal passages of air-cooled turbine blades (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by Frederick C. Yeh, Francis S. Stepka, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Hot hardness of nickel-rich nickel-chromium-aluminum alloys (National Aeronautics and Space Administration ;, 1976), by Stanley R. Levine and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Method of predicting radiation heat transfer in turbine-cooling test facilities (National Aeronautics and Space Administration ;, 1975), by Herbert J. Gladden, Curt H. Liebert, and Lewis Research Center (page images at HathiTrust)
• Coolant pressure and airflow distribution in a strut-supported transpiration-cooled vane for a gas turbine engine (National Aeronautics and Space Administration ;, 1972), by Albert Kaufman, Hadley T. Richards, David J. Poferl, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• Effect of a reduction in blade thickness on performance of a single-stage 20.32-centimeter mean-diameter turbine (National Aeronautics and Space Administration ;, 1973), by William J. Nusbaum, Milton G. Kofskey, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• Effect of chord size on weight and cooling characteristics of air-cooled turbine blades (National Advisory Committee for Aeronautics, 1957), by Jack B. Esgar, Arthur N. Curren, Eugene F. Schum, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Analytical investigation of two liquid cooling systems for turbine blades (National Advisory Committee for Aeronautics, 1951), by Thomas W. Jackson, John N. B. Livingood, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Determination of gas-to-blade convection heat-transfer coefficients on a forced-convection, water-cooled single-stage aluminum turbine (National Advisory Committee for Aeronautics, 1951), by John C. Freche, Eugene F. Schum, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Cooling of gas turbines. [Part] 2, Effectiveness of rim cooling of blades (National Advisory Committee for Aeronautics, 1947), by L. Wolfenstein, John S. McCarthy, Gene L. Meyer, and Aircraft Engine Research Laboratory (page images at HathiTrust)
• Cooling of gas turbines. [Part] 4, Calculated temperature distribution in the trailing part of a turbine blade using direct liquid cooling (National Advisory Committee for Aeronautics, 1947), by W. Byron Brown, William R. Monroe, and Aircraft Engine Research Laboratory (page images at HathiTrust)
• Cooling of gas turbines. [Part] 8, Theoretical temperature distributions through gas turbine with special blades and cooling fins on the rim (National Advisory Committee for Aeronautics, 1948), by W. Byron Brown, John N. B. Livingood, and Flight Propulsion Research Laboratory (page images at HathiTrust)
• Cooling of gas turbines. [Part] 5, Effectiveness of air cooling of hollow blades (National Advisory Committee for Aeronautics, 1947), by L. Wolfenstein, John S. McCarthy, Robert L. Maxwell, and Aircraft Engine Research Laboratory (page images at HathiTrust)
• Cooling of gas turbines. [Part] 3, Analysis of rotor and blade temperatures in liquid-cooled gas turbines (National Advisory Committee for Aeronautics, 1947), by W. Byron Brown, John N. B. Livingood, and Aircraft Engine Research Laboratory (page images at HathiTrust)
• Effect of diameter of closed-end coolant passages on natural-convection water cooling of gas-turbine blades (National Advisory Committee for Aeronautics, 1956), by Arthur N. Curren, Charles F. Zalabak, 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 the use of electrical resistance for detecting overtemperatured S-816 turbine blades (National Advisory Committee for Aeronautics, 1957), by Leonard Robins, Lewis A. Rodert, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• A comparison of typical National Gas Turbine Establishment and NACA axial-flow compressor blade sections in cascade at low speed (National Advisory Committee for Aeronautics, 1953), by A. Richard Felix, James C. Emery, Langley Aeronautical Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• NACA Wartime Reports. Series E. (National Advisory Committee for Aeronautics, 1945), by David S. Gabriel, L. Robert Carman, Aircraft Engine Research Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

• NACA Conference on Turbine Materials and Cooling : a compilation of the papers presented, Lewis Flight Propulsion Laboratory, Cleveland, Ohio, March 15, 1951 (NACA, 1951), by Ohio) NACA Conference on Turbine Materials and Cooling (1951 : Cleveland, Lewis Flight Propulsion Laboratory, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

• Flow measurement in base cooling air passages of a rotating turbine blade (National Aeronautics and Space Administration ;, 1974), by Curt H. Liebert, Frank G. Pollack, and Lewis Research Center (page images at HathiTrust)

• Analytical study of flow reduction due to oxidation of wire-form porous sheet for transpiration cooled turbine blades (National Aeronautics and Space Administration ;, 1969), by Albert Kaufman, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)

• Analytical study of flow reduction due to oxidation of wire-form porous sheet for transpiration cooled turbine blades (National Aeronautics and Space Administration ;, 1969), by Albert Kaufman, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)

• Stagnation region gas film cooling : spanwise angled injection from multiple rows of holes (National Aeronautics and Space Administration ;, 1981), by D. W. Luckey, M. R. L'Ecuyer, Lewis Research Center, Purdue University. Thermal Sciences and Propulsion Center, United States National Aeronautics and Space Administration, and United States. Office of Naval Research (page images at HathiTrust)

• Incidence loss for a core turbine rotor blade in a two-dimensional cascade (National Aeronautics and Space Administration ;, 1974), by Roy G. Stabe, John F. Kline, and Lewis Research Center (page images at HathiTrust)
• Cold-air annular-cascade investigation of aerodynamic performance of cooled turbine vanes (National Aeronautics and Space Administration ;, 1974), by Louis J. Goldman, Kerry L. McLallin, and Lewis Research Center (page images at HathiTrust)
• Aerodynamic performance of a ceramic-coated core turbine vane tested with cold air in a two-dimensional cascade (National Aeronautics and Space Administration ;, 1975), by Roy G. Stabe, Curt H. Liebert, and Lewis Research Center (page images at HathiTrust)
• Comparison of cooling effectiveness of turbine vanes with and without film cooling (National Aeronautics and Space Administration ;, 1974), by Frederick C. Yeh and Lewis Research Center (page images at HathiTrust)
• Metal temperatures and coolant flow in a wire-cloth transpiration-cooled turbine vane (National Aeronautics and Space Administration ;, 1975), by Herbert J. Gladden (page images at HathiTrust)
• Turbine vane coolant flow variations and calculated effects on metal temperatures (National Aeronautics and Space Administration ;, 1975), by Frederick C. Yeh, Louis M. Russell, Peter L. Meitner, and Lewis Research Center (page images at HathiTrust)
• Aerodynamic performance of a fully film cooled core turbine vane tested with cold air in a two-dimensional cascade (National Aeronautics and Space Administration ;, 1975), by Roy G. Stabe, John F. Kline, and Lewis Research Center (page images at HathiTrust)
• Effect of blade-tip crossover passages on natural-convection water-cooling of gas-turbine blades (National Advisory Committee for Aeronautics, 1956), by Charles F. Zalabak, Arthur N. Curren, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)

• An analysis of the capabilities and limitations of turbine air cooling methods (National Aeronautics and Space Administration ;, 1970), by Jack B. Esgar, Albert Kaufman, Raymond S. Colladay, and Lewis Research Center (page images at HathiTrust)

• Coatings for High-Temperature Structural Materials: Trends and Opportunities (1996), by National Research Council National Materials Advisory Board (page images with commentary at NAP)

• An evaluation of three oxidation-resistant alloy claddings for IN 100 and WI 52 superalloys (National Aeronautics and Space Administration ;, 1969), by Michael A. Gedwill, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• A nickel-base alloy, NASA WAZ-16, with potential for gas turbine stator vane application (National Aeronautics and Space Administration ;, 1974), by William J. Waters, John C. Freche, and Lewis Research Center (page images at HathiTrust)
• Factors affecting miniature Izod impact strength of tungsten-fiber-metal-matrix composites (National Aeronautics and Space Administration ;, 1973), by Edward A. Winsa, Donald W. Petrasek, and Lewis Research Center (page images at HathiTrust)
• Stress-rupture strength and microstructural stability of tungsten-hafnium-carbon-wire-reinforced superalloy composites (National Aeronautics and Space Administration ;, 1974), by Donald W. Petrasek, Robert A. Sigorelli, and Lewis Research Center (page images at HathiTrust)

• On friction and leakage losses in the working blade-rings of radial flow turbines in helicopter and transport gas-turbine units (National Aeronautics and Space Administration, 1967), by N. F. Galit︠s︡kiĭ (page images at HathiTrust)
• Incidence loss for a core turbine rotor blade in a two-dimensional cascade (National Aeronautics and Space Administration ;, 1974), by Roy G. Stabe, John F. Kline, and Lewis Research Center (page images at HathiTrust)
• Experimental performance and analysis of 15.04-centimeter-tip-diameter, radial-inflow turbine with work factor of 1.126 and thick blading (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1980), by Kerry L. McLallin, Jeffrey E. Haas, Propulsion Laboratory (U.S.), Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• Effect of rotor-to-stator spacing on acoustic performance of a full-scale fan (QF-5) for turbofan engines (National Aeronautics and Space Administration ;, 1974), by Joseph R. Balombin, Edward G. Stakolich, and Lewis Research Center (page images at HathiTrust)
• Thermal stress analysis of ceramic gas-path seal components for aircraft turbines (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by Francis E. Kennedy, Robert C. Bill, Lewis Research Center, Propulsion Laboratory (U.S.), and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Reaction diffusion in the nickel-chromium-aluminum and cobalt-chromium-aluminum systems (National Aeronautics and Space Administration ;, 1977), by Stanley R. Levine and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Procedure for calculating turbine blade temperatures and comparison of calculated with observed values for two stationary air-cooled blades (NACA, 1952), by W. Byron Brown, Hadley T. Richards, Henry O. Slone, United States National Advisory Committee for Aeronautics, and Lewis Research Center (page images at HathiTrust)
• Effect of high rotor pressure-surface diffusion on performance of a transonic turbine (National Advisory Committee for Aeronautics, 1955), by James W. Miser, Daniel E. Monroe, Warner L. Stewart, Lewis Flight Propulsion Laboratory, and United States. National Adviosry Committee for Aeronautics (page images at HathiTrust)
• Effect of a reduction in stator solidity on performance of a transonic turbine (National Advisory Committee for Aeronautics, 1956), by James W. Miser, R. Y. Wong, 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)
• Comparison of results of experimental and theoretical studies of blade-outlet boundary-layer characteristics of stator blade for a high subsonic Mach number turbine (National Advisory Committee for Aeronautics, 1957), by Cavour H. Hauser, William J. Nusbaum, Lewis Flight Propulsion Laboratory, United States. National Adviosry Committee for Aeronautics, and United States National Advisory Committee for Aeronautics (page images at HathiTrust)
• Cascade investigation of cooling characteristics of a corrugated-insert air-cooled turbine blade for use in a turboprop engine (National Aeronautics and Space Administration, 1960), by Hadley T. Richards and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Fiber reinforced structures for small turbine engine fragment containment (Phase II). (Federal Aviation Administration, Office of Aviation Research ;, 1996), by Inc Pepin Associates and United States. Federal Aviation Administration. Office of Aviation Research (page images at HathiTrust)

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