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Modified tubular combustor as high-temperature gas generators

Description: A pair of combustors and transition liners in a quarter-annular, direct-connect assembly was operated at temperatures up to 2400 degrees F to determine the feasibility of using production-type combustor systems as high-tmeperature gas generators for turbine-cooling studies. Operation at high temperatures for 32 hours was possible when minor liner modifications were made that provided greater cooling-air flow between the turbine casing and interior components.
Date: October 21, 1955
Creator: Friedman, Robert & Zettle, Eugene V.
Partner: UNT Libraries Government Documents Department
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Initial Experiments on the Aerodynamic Cooling Associated With Large-Scale Vortical Motions in Supersonic Flow

Description: Report presenting a theory of reduction of convective heat transfer to a surface in supersonic flow by periodically imposing a large-scale vortical motion on the boundary layer and an experimental investigation of that theory. Results regarding the pulsating flow phenomena, heat-transfer characteristics, and aerodynamic characteristics are provided.
Date: March 8, 1955
Creator: Eggers, A. J., Jr. & Hermach, C. A.
Partner: UNT Libraries Government Documents Department
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Design procedure for transpiration-cooled strut-supported turbine rotor blades

Description: From Summary: "The procedure currently employed by the NACA Lewis Laboratory in the design of transpiration-cooled strut-supported turbine rotor blades is discussed. The strut is the internal blade supporting member and also serves to partition the blade into separate cooling-air passages. Orifices in the blade base, which meter the cooling-air to each internal passage, are used in conjunction with a constant chordwise permeability."
Date: December 19, 1955
Creator: Prasse, Ernst I. & Livingood, John N. B.
Partner: UNT Libraries Government Documents Department
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Analytical comparison of convection-cooled turbine blade cooling-air requirements for several radial gas-temperature profiles

Description: Report presenting an analysis made to permit a comparative evaluation of the turbine rotor cooling-air requirements with convection-cooled blades for four combustor-outlet radial gas-temperature profiles: a uniform profile, a profile representable by a complete cycle of the cosine wave using cooler gas layers near the turbine casing, a profile representable by one-half cycle of the cosine wave using cooler gas layers near the stator inner ring, and an optimum profile resulting in the absolute m… more
Date: September 7, 1955
Creator: Hubbartt, James E. & Slone, Henry O.
Partner: UNT Libraries Government Documents Department
open access

Cascade Investigation of Cooling Characteristics of a Castfinned Air-Cooled Turbine Blade for Use in a Turboprop Engine

Description: Memorandum presenting an experimental investigation of the cooling characteristics of a small air-cooled turbine blade for use in a turboprop engine in a static cascade facility. Three test blades were studiued at three combustion-gas temperatures. Results regarding gas-flow conditions in cascade test section, correlation of temperature data, and application of correlated data to the typical engine are provided.
Date: June 12, 1957
Creator: Stepka, Francis S.; Richards, Hadley T. & Hickel, Robert O.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine 2: Rotor Blades With 15 Fins in Cooling-Air Passages

Description: Report presenting an investigation to experimentally determine the effectiveness of air-cooling several configurations of turbine blades in a turbojet engine. The results of the second blade configuration, which consists of a hollow blade shell with 15 fins inserted, are provided. The factors involved in the design of the blade configuration are also included.
Date: August 1950
Creator: Hickel, Robert O. & Ellerbrock, Herman H., Jr.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine: 1: Rotor Blades With 10 Tubes in Cooling-Air Passages

Description: Report presenting an investigation to experimentally determine the effectiveness of air cooling several turbine-blade configurations in a turbojet engine. The results obtained with the first configuration, which was a hollow blade shell with 10 tube inserts, are presented. A description of factors leading to the design are provided as well as the correlated cooled-blade temperatures, solid-blade temperatures, cooling-air-temperature increase through radial passages, and blade failure are provid… more
Date: July 30, 1950
Creator: Ellerbrock, Herman H., Jr. & Stepka, Francis S.
Partner: UNT Libraries Government Documents Department
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Cooling Characteristics of a Transpiration-Cooled Afterburner With a Porous Wall of Brazed and Rolled Wire Cloth

Description: Memorandum presenting cooling data for a transpiration-cooled afterburner with a porous combustion-chamber wall of brazed and rolled wire cloth for a range of exhaust-gas temperatures, total flow ratio of cooling air to combustion gas, and pressure altitudes. Maximum wall temperatures based on the cooling correlation were determined for a porous wall of uniform permeability at sea-level takeoff and for several flight Mach numbers. Results regarding typical data, cooling correlation, transpirati… more
Date: August 19, 1954
Creator: Koffel, William K.
Partner: UNT Libraries Government Documents Department
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Flight Test of a Solid-Fuel Ramjet With the Internal Surface of the Combustor Air Cooled

Description: Report presenting a flight investigation of a rocket-launched solid-fuel ram-jet engine designed to bypass cooling air around the fuel charge. The internally cooled combustor averted combustor burn-out during the flight test. Results regarding the net thrust coefficient, gross thrust coefficient, time history of the air specific impulse, and total fuel load are provided.
Date: July 3, 1956
Creator: Bartlett, Walter A., Jr.
Partner: UNT Libraries Government Documents Department
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Empirical Cooling Correlation for an Experimental Afterburner With an Annular Cooling Passage

Description: Memorandum presenting an empirical cooling correlation for an experimental high-performance afterburner. The correlation relates the average combustion-chamber wall temperature at a station near the combustion-chamber outlet to the temperatures of the cooling air and combustion gas, and to the mass flows of the cooling air and combustion gas.
Date: June 26, 1952
Creator: Koffel, William K. & Kaufman, Harold R.
Partner: UNT Libraries Government Documents Department
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Internal film cooling experiments in 4-inch duct with gas temperatures to 2000 degrees F

Description: Report presenting an investigation of the cooling effectiveness of water films on the inner surface of a well-insulated, 4-inch-diameter duct with air flowing through the duct at a range of temperature and Reynolds numbers. Results regarding the effect of the gas temperature and mass velocity on liquid-cooled length, effect of coolant flow on liquid-cooled length, and some suggestions for further investigation are provided. Equations for correlation are created from the data.
Date: September 21, 1950
Creator: Kinney, George R. & Sloop, John L.
Partner: UNT Libraries Government Documents Department
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Preliminary analysis of effects of air cooling turbine blades on turbojet-engine performance

Description: The effects of turbine-blade cooling on engine performance were analytically investigated for a turbojet engine in which cooling air is bled from the engine compressor. The analysis was made for a constant turbine-inlet temperature and a range of altitudes to determine the minimum cooling requirements to permit substitution of nonstrategic materials in turbine blading. The results indicate that, for a constant inlet temperature, air cooling of the turbine blades increases the specific fuel cons… more
Date: August 2, 1950
Creator: Schramm, Wilson B.; Nachtigall, Alfred J. & Arne, Vernon L.
Partner: UNT Libraries Government Documents Department
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Investigation of High-Temperature Operation of Liquid-Cooled Gas Turbines 1: Turbine Wheel of Aluminum Alloy, a High-Conductivity Nonstrategic Material

Description: Report presenting an investigation of turbine operating temperatures as affected by liquid cooling, especially if materials of high conductivity are used, at gas temperatures up to 1925 degrees Fahrenheit. Results regarding the statio heat-transfer rig and turbine rig are provided. The investigation showed that nonstrategic material such as aluminum alloy can be used in liquid-cooled turbine wheels at high gas temperatures.
Date: July 22, 1948
Creator: Kottas, Harry & Sheflin, Bob W.
Partner: UNT Libraries Government Documents Department
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Performance investigation of can-type combustor 2: water injection at various stations in combustor

Description: Report presenting an investigation to determine the maximum quantity of water that could be injected either into or ahead of a single can-type combustor without reducing the attainable combustor-outlet temperature below the value required for engine operation and without the appearance of liquid water at the combustor outlet. Water was injected from spray nozzles at four different stations along the combustor.
Date: September 30, 1948
Creator: Cook, William P. & Zettle, Eugene V.
Partner: UNT Libraries Government Documents Department
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Performance of several air ejectors with conical mixing sections and small secondary flow rates

Description: An investigation of several ejector configurations to determine the ability to handle the air required for engine cooling. The results are limited to investigations of conical-type mixing-section ejectors at ratios of mixing-section minimum diameter to primary-jet-nozzle diameter using unheated air. Results regarding experimental data, generalization of experimental data, spacing for maximum weight-flow ratio, ejector thrust, ejector configurations for constant weight-flow ratio, and selection … more
Date: July 19, 1948
Creator: Huddleston, S. C.; Wilsted, H. D. & Ellis, C. W.
Partner: UNT Libraries Government Documents Department
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Preliminary Study of Use of Nonstrategic Metals for and Application of Cooling to Blades of Turbine of J35 Turbojet Engine

Description: Memorandum presenting the modifications to the J35 engine that are necessitated with the use of non-strategic materials. Two proposals for cooling the rotor disk and blades are: finned hollow blades that are air cooled and blades with circular passages for liquid cooling in which the fuel could be used as the coolant.
Date: November 17, 1948
Creator: Turbine Cooling Research Branch
Partner: UNT Libraries Government Documents Department
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Internal-Film Cooling of Rocket Nozzles

Description: Experiments were conducted with 1000-pound-thrust rocket engine to determine feasibility of cooling convergent-divergent nozzle by internal film of water introduced at nozzle entrance. Water flow of 3 percent of propellant flow reduced heat flow into nozzle to 55 percent of uncooled heat flow. Introduction of water by porous ring before nozzle resulted in more uniform coverage of nozzle than water introduced by single arrangement of 36 jets directed along nozzle wall. Water flow through porous … more
Date: June 8, 1948
Creator: Sloop, J. L. & Kinney, George R.
Partner: UNT Libraries Government Documents Department
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Altitude cooling investigation of the R-2800-21 engine in the P-47G airplane 2: investigation of the engine & airplane variables affecting the cylinder temperature distribution

Description: "The data obtained from cooling tests of an R-2800-21 engine installed in a P-47G airplane were studied to determine which engine and airplane operation variables were mainly responsible for the extremely uneven temperature distribution among the 18 engine cylinders obtained at the medium and high engine-power conditions. The tests consisted of flights at altitudes from 5000 to 35,000 feet for the normal range of engine and airplane operation. The results of the study showed that a flow conditi… more
Date: October 9, 1946
Creator: Pesman, Gerard J. & Kaufman, Samuel J.
Partner: UNT Libraries Government Documents Department
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Preliminary air-flow and thrust calibrations of several conical Cooling-air ejectors with a primary to secondary temperature ratio of 1.0 I :diameter ratios of 1.21 and 1.10

Description: Report presenting an investigation of the performance of several conical cooling-air ejectors at primary jet pressure ratios from 1 to 10, secondary shroud pressure ratios from 0.60 to 4.00, and primary to secondary temperature ratio of 1.0. The investigation centered on primary air flow, secondary air flow, primary nozzle thrust, and gross ejector thrust.
Date: July 22, 1952
Creator: Greathouse, W. K. & Hollister, D. P.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of Air-Cooled Turbine Blades in Turbojet Engine 12: Cooling Effectiveness of a Blade With an Insert and With Fins Made of a Continuous Corrugated Sheet

Description: Memorandum presenting an investigation conducted in a modified turbojet engine to determine the cooling effectiveness of an air-cooled turbine-rotor blade employing a corrugated metal sheet brazed to the inner surface of the blade shell to increase the internal heat-transfer area. The corrugated fin blade had a lower integrated average wall temperature at the section investigated than the more promising shell-supported blade types previously investigated. Results regarding the temperature distr… more
Date: August 28, 1952
Creator: Bartoo, Edward R. & Clure, John L.
Partner: UNT Libraries Government Documents Department
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Flight and Test-Stand Investigation of High-Performance Fuels in Pratt & Whitney R-1830-94 Engines 4: Comparison of Cooling Characteristics of Flight and Test-Stand Engines

Description: "The cooling characteristics of three R-1830-94 engines, two of which were mounted in a test stand and the other in a B-24D airplane, were investigated and the results were compared. The flight tests were made at a pressure altitude of 7000 feet; the test-stand runs were made at ground-level atmospheric conditions. Three cooling runs were made for each engine: variable cooling-air pressure drop, variable carburetor-air flow, and variable fuel-air ratio" (p. 1).
Date: October 8, 1946
Creator: Dandois, Marcel & Werner, Milton
Partner: UNT Libraries Government Documents Department
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Effects of internal configuration on afterburner shell temperatures

Description: From Summary: "A brief investigation was conducted in the altitude wind tunnel to determine the extent to which the afterburner shell cooling problem could be alleviated by internal configuration changes. Data were obtained with and without a cooling liner installed and for variations in the radial fuel distribution and in the radial distribution in flame-seat area. Consideration is given to the effects on both shell temperature and afterburner performance."
Date: January 8, 1952
Creator: Conrad, E. William & Jansen, Emmert T.
Partner: UNT Libraries Government Documents Department
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Analytical procedures for rapid selection of coolant passage configurations for air-cooled turbine rotor blades and for evaluation of heat-transfer, strength, and pressure-loss characteristics

Description: Report presenting a method based on geometric factors of the coolant passage was evolved for the rapid selection and evaluation of coolant passage configurations for air-cooled turbine rotor blades. The most promising coolant passage configurations are analyzed to obtain absolute values of the required cooling-air weight flow, pressure loss, and strength characteristics.
Date: September 18, 1952
Creator: Ziemer, Robert R. & Slone, Henry O.
Partner: UNT Libraries Government Documents Department
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