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Aircraft gas-turbines -- Combustion chambers

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• Aircraft gas-turbines
• Combustion chambers
• Gas-turbines -- Combustion chambers

• Aircraft gas-turbines -- Combustion chambers -- Cooling
• Aircraft gas-turbines -- Combustion chambers -- Design and construction
• Aircraft gas-turbines -- Combustion chambers -- Materials
• Aircraft gas-turbines -- Combustion chambers -- Testing
• Afterburners

• Effect of flame stabilizer design on performance and exhaust pollutants of a two-row swirl-can combustor operated to near-stoichiometric conditions (National Aeronautics and Space Administration ;, 1977), by James A. Biaglow, Arthur M. Trout, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Emissions of nitrogen oxides from an experimental hydrogen-fueled gas turbine combustor (National Aeronautics and Space Administration ;, 1974), by Carl T. Norgren, Robert D. Ingebo, and Lewis Research Center (page images at HathiTrust)
• Optical measurement of static temperature and hydroxyl radical profiles in a hydrogen-fueled supersonic combustor (National Aeronautics and Space Administration ;, 1974), by Raymond E. Gaugler and Lewis Research Center (page images at HathiTrust)
• Spontaneous-ignition temperature limits of Jet A fuel in research-combustor segment (National Aeronautics and Space Administration ;, 1974), by Robert D. Ingebo, Carl T. Norgren, and Lewis Research Center (page images at HathiTrust)
• Effect of oxygen addition on altitude blowout and relight of an experimental combustor segment (National Aeronautics and Space Administration ;, 1974), by Carl T. Norgren, Robert D. Ingebo, and Lewis Research Center (page images at HathiTrust)
• Performance and durability of improved air-atomizing splash-cone fuel nozzles (National Aeronautics and Space Administration ;, 1974), by Robert D. Ingebo, Carl T. Norgren, and Lewis Research Center (page images at HathiTrust)
• Effect of exhaust gas recirculation on emissions from a flame-tube combustor using liquid Jet A Fuel (National Aeronautics and Space Administration ;, 1976), by Cecil J. Marek, Robert R. Tacina, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Exhaust pollutant emissions from swirl-can combustor module arrays at parametric test conditions (National Aeronautics and Space Administration ;, 1975), by Edward J. Mularz, Peter W. Verbulecz, Jerrold D. Wear, U.S. Army Air Mobility Research and Development Laboratory, and Lewis Research Center (page images at HathiTrust)
• Flow characteristics of various swirl-can module designs (National Aeronautics and Space Administration ;, 1975), by Edward J. Mularz, U.S. Army Air Mobility Research and Development Laboratory, and Lewis Research Center (page images at HathiTrust)
• Effect of wall edge suction on the performance of a short annular dump diffuser with exit passage flow resistance (National Aeronautics and Space Administration ;, 1975), by Albert J. Juhasz and Lewis Research Center (page images at HathiTrust)
• Effect of premixing quality on oxides of nitrogen in gas turbine combustors (National Aeronautics and Space Administration ;, 1976), by Gerald Roffe, Antonio Ferri, Lewis Research Center, and Nassau County General Applied Science Laboratories (Westbury (page images at HathiTrust)
• Prevaporization and premixing to obtain low oxides of nitrogen in gas turbine combustors (National Aeronautics and Space Administration ;, 1975), by Gerald Roffe, Antonio Ferri, Lewis Research Center, and Advanced Technology Laboratories (page images at HathiTrust)
• Investigation of hydrogen-air ignition senitized by nitric oxide and by nitrogen dioxide (National Aeronautics and Space Administration ;, 1977), by M. Slack, A. Grillo, Grumman Aerospace Corporation, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Pollutant formation in fuel lean reciruclating flows (National Aeronautics and Space Administration ;, 1976), by Robert W. Schefer, R. F. Sawyer, Berkeley University of California, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effect of design features on performance of a double-annular ram-induction combustor (National Aeronautics and Space Administration ;, 1975), by Donald F. Schultz and Lewis Research Center (page images at HathiTrust)
• Performance of an asymmetric short annular diffuser with a nondiverging inner wall using suction (National Aeronautics and Space Administration ;, 1974), by Albert J. Juhasz and Lewis Research Center (page images at HathiTrust)
• Aerodynamic drag and fuel spreading measurements in a simulated scramjet combustion module (National Aeronautics and Space Administration ;, 1974), by Louis A. Povinelli and Lewis Research Center (page images at HathiTrust)

• Measurements of liner cooling effectiveness within a full-scale double-annular ram-induction combustor (National Aeronautics and Space Administration ;, 1974), by Edward J. Mularz, Donald F. Schultz, and U.S. Army Air Mobility Research and Development Laboratory (page images at HathiTrust)

• Effect of design features on performance of a double-annular ram-induction combustor (National Aeronautics and Space Administration ;, 1975), by Donald F. Schultz and Lewis Research Center (page images at HathiTrust)

• High-temperature durability considerations for HSCT combustor (National Aeronautics and Space Administration, Office of Management, Scientific and Technical Information Program, 1992), by Nathan S. Jacobson and Lewis Research Center (page images at HathiTrust)

• Effect of diffuser bleed on performance of an annular swirl can combustor (National Aeronautics and Space Administration ;, 1974), by Albert J. Juhasz and Lewis Research Center (page images at HathiTrust)
• Modifications that improve performance of a double annular combustor at simulated engine idle conditions (National Aeronautics and Space Administration ;, 1974), by Donald F. Schultz and Lewis Research Center (page images at HathiTrust)
• Variable combustor geometry for improving the altitude relight capability of a double annular combustor (National Aeronautics and Space Administration ;, 1974), by Donald F. Schultz and Lewis Research Center (page images at HathiTrust)
• Exhaust emissions of a double annular combustor : parametric study (National Aeronautics and Space Administration ;, 1975), by Donald F. Schultz and Lewis Research Center (page images at HathiTrust)
• Idle efficiency and pollution results for two-row swirl-can combustors having 72 modules (National Aeronautics and Space Administration ;, 1975), by James A. Biaglow, Arthur M. Trout, and Lewis Research Center (page images at HathiTrust)
• Ground idle performance improvement of a double-annular combustor by using simulated variable combustor geometry (National Aeronautics and Space Administration ;, 1975), by Donald F. Schultz and Lewis Research Center (page images at HathiTrust)
• Performance of a short modular turbojet combustor segment using ASTM-A1 fuel (National Aeronautics and Space Administration ;, 1971), by Richard W. Niedzwiecki, Harry M. Moyer, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• Combustion stability of single swirl-can combustor modules using ASTM-A1 liquid fuel (National Aeronautics and Space Administration ;, 1969), by Richard W. Niedzwiecki, Robert E. Jones, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• Performance of a 48-module swirl-can turbojet combustor segment at high temperatures using ASTM-A1 fuel (National Aeronautics and Space Administration ;, 1969), by Richard W. Niedzwiecki, Harry M. Moyer, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• NASA TN D-6706 (National Aeronautics and Space Administration :, 1972), by Donald F. Schultz, Porter J. Perkins, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)

• Cooling characteristics of a transpiration-cooled afterburner with a porous wall of brazed and rolled wire cloth (NACA, 1954), by William K. Koffel, United States National Advisory Committee for Aeronautics, and Lewis Research Center (page images at HathiTrust)

• NASA TN D-6297 (National Aeronautics and Space Administration:, 1971), by Frank W. Burcham (page images at HathiTrust; US access only)
• Supersonic inlet investigation. Volume I, Summary report (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1971., 1971), by T. W. Tsukahira, Gordon R. Hall, M. Yaamada, W. F. Wong, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Northrop Corporation. Aircraft Division (page images at HathiTrust)
• Supersonic inlet investigation. Volume III, Wind tunnel data report (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1971., 1971), by T. W. Tsukahira, B. G. Franco, W. F. Wong, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Northrop Corporation. Aircraft Division (page images at HathiTrust)
• Supersonic inlet investigation. Volume II, Air induction sysem dynamic simulation model (Wright-Patterson Air Force Base, Ohio : Air Force Flight Dynamics Laboratory, Air Force Systems Command, United States Air Force, 1971., 1971), by Nasim F. Amin, Gordon R. Hall, United States. Air Force. Systems Command, Air Force Flight Dynamics Laboratory (U.S.), and Northrop Corporation. Aircraft Division (page images at HathiTrust)

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

• The Aerothermodynamics of aircraft gas turbine engines (Air Force Aero Propulsion Laboratory, Air Force Wright Aeronautical Laboratories, Air Force Systems Command ;, 1978), by Gordon C. Oates, Air Force Aero Propulsion Laboratory (U.S.), and United States. Air Force. Office of Scientific Research (page images at HathiTrust)
• Turbine design and application (Scientific and Technical Information Office, National Aeronautics and and Space Administration: [For sale by the Supt. of Docs., U.S. Govt. Print. Off.], 1972), by Arthur J. Glassman (page images at HathiTrust; US access only)
• Programmed text : T-53-L-13 gas turbine engine. (U.S. Army Aviation Center, 1985), by U.S. Army Aviation 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)
• Analysis of a topping-cycle, aircraft, gas-turbine-engine system which uses cryogenic fuel (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1984), by George E. Turney, Laurence H. Fishbach, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• FORTRAN program to generate engine inlet flow contour maps and distortion parameters (National Aeronautics and Space Administration ;, 1974), by John H. Dicus and Lewis Research Center (page images at HathiTrust)
• Effect of casing treatment on overall performance of axial-flow transonic fan stage with pressure ratio of 1.75 and tip solidity of 1.5 (National Aeronautics and Space Administration ;, 1977), by Walter M. Osborn, Royce D. Moore, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Effect of swirler-mounted mixing venturi on emissions of flame-tube combustor using Jet A fuel (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1979), by David B. Ercegovic, Propulsion Laboratory (U.S.), and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Emittance and absorptance of NASA ceramic thermal barrier coating system (National Aeronautics and Space Administration, Scientific and Technical Information Office ;, 1978), by Curt H. Liebert and United States. National Aeronautics and Space Administration. Scientific and Technical Information Office (page images at HathiTrust)
• Two-layer thermal barrier coating for turbane airfoils - furnace and burner rig test results (U.S. National Aeronautics and Space Administration ;, 1976), by Stephan Stecura, United States National Aeronautics and Space Administration, and Lewis Research Center (page images at HathiTrust)
• 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)
• Jet array impingement with crossflow - correlation of streamwise resolved flow and heat transfer distributions (National Aeronautics and Space Administration, Scientific and Technical Information Branch ;, 1981), by L. W. Florschuetz, C. R. Truman, Darryl E. Metzger, Lewis Research Center, and United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch (page images at HathiTrust)
• NASA TN D-6702 (National Aeronautics and Space Administration :, 1972), by Arthur J. Glassman, Lewis Research Center, and United States National Aeronautics and Space Administration (page images at HathiTrust)
• Computer program for quasi-one-dimensional compressible flow with area change and friction : application to gas film seals (National Aeronautics and Space Administration ;, 1974), by John Zuk, Patricia J. Smith, and Lewis Research Center (page images at HathiTrust)
• Similarity constraints in testing of cooled engine parts (National Aeronautics and Space Administration ;, 1974), by Raymond S. Colladay, Francis S. Stepka, and Lewis Research Center (page images at HathiTrust)
• Performance and windmilling drag characteristics (National Advisory Committee for Aeronautics, 1948), by William A. Fleming, Robert O. Jr Dietz, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Effect of pressure ratio and inlet pressure on performance of experimental gas turbine at inlet temperature of 800 degrees R (National Advisory Committee for Aeronautics, 1948), by Robert C. Kohl, Robert G. Larkin, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Combustion-chamber performance (National Advisory Committee for Aeronautics, 1948), by Bemrose Boyd, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Analysis of turbine performance of 19B-8 engine (National Advisory Committee for Aeronautics, 1948), by Richard P. Krebs, Frank L. Suozzi, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Analysis of compressor performance (National Advisory Committee for Aeronautics, 1948), by Robert O. Dietz, John K. Kuenzig, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Investigation of a gas turbine with National Bureau of Standards body 4811 ceramic rotor blades (National Advisory Committee for Aeronautics, 1948), by John C. Freche, Bob W. Sheflin, United States National Advisory Committee for Aeronautics, and Lewis Flight Propulsion Laboratory (page images at HathiTrust)
• Evaluation of lightweight material concepts for aircraft turbine engine rotor failure protection (Federal Aviation Administration, Office of Aviation Research ;, 1997), by Dy D. Le, U.S. Army Research Laboratory, Naval Air Warfare Center (U.S.). Aircraft Division, Federal Aviation Administration Technical Center (U.S.), and United States. Office of Aviation Research (page images at HathiTrust)
• Statistics on aircraft gas turbine engine rotor failures that occurred in U.S. commercial aviation during 1986 (Federal Aviation Administration Technical Center ;, 1990), by R. A. DeLucia, B. C. Fenton, J. T. Salvino, Naval Air Propulsion Test Center, and Federal Aviation Administration Technical Center (U.S.) (page images at HathiTrust)
• Statistics on aircraft gas turbine engine rotor failures that occurred in U.S. commercial aviation during 1988 (Federal Aviation Administration Technical Center ;, 1992), by R. A. DeLucia, E. R. Chapdelaine, B. C. Fenton, Naval Air Propulsion Test Center, and Federal Aviation Administration Technical Center (U.S.) (page images at HathiTrust)
• A dynamic performance computer for gas turbine engines (Wright-Patterson Air Force Base, Ohio : Power Plant Laboratory, Wright Air Development Center, Air Research and Development Command, United States Air Force, 1955., 1955), by V. L. Larrowe, M. M. Spencer, Wright Air Development Center, University of Michigan, and United States. Air Force. Air Research and Development Command (page images at HathiTrust)
• A method for estimating gas turbine-jet airplane performance (Wright Field, Dayton, Ohio : War Department, Army Air Forces, Air Technical Service Command, 1945., 1945), by Robert E. Hage and United States. Army Air Forces. Air Matériel Command (page images at HathiTrust)
• Training guide for J73-GE-3, -3A, -3D, turbojet engine (General Electric, Aircraft Gas Turbine Divisions, 1955), by General Electric Company and Aircraft Gas Turbine Training School (page images at HathiTrust; US access only)

More items available under broader and related terms at left.