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Two-dimensional compressible flow in conical mixed-flow compressors

Description: Report presenting a general method of analysis developed for the two-dimensional, steady, compressible flow through mixed-flow compressors in which the center line of the passage generates a right circular cone about the axis of the compressor. The two-dimensional, radial-discharge compressor is a special case in which the cone angle is equal to 180 degrees. The general analysis also applies to inward-flow turbines.
Date: November 1948
Creator: Stanitz, John D.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Performance of exhaust-gas blowdown turbine and various engine systems using a 12-cylinder liquid-cooled engine

Description: Report presenting an experimental investigation of a blowdown turbine installed in the exhaust stream of a 12-cylinder liquid-cooled engine of 1710-cubic-inch displacement. Results regarding turbine performance and performance of complete engine systems are provided.
Date: November 1948
Creator: Desmon, Leland G. & Sams, Eldon W.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A metallurgical investigation of a contour-forged disc of EME alloy

Description: Report presenting a study of the properties of EME alloy in the form of contour-forged discs for the rotors of gas turbines. The investigation was undertaken because the properties of promising alloys are dependent to a considerable extent on the conditions of fabrication and the size and shape of the rotor discs introduced fabrication procedures for which information was not available. Results regarding hardness surveys, short-time tensile properties, rupture test characteristics, time-deforma… more
Date: November 1948
Creator: Reynolds, E. E.; Freeman, J. W. & White, A. E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Determination of Stresses in Gas-turbine Disks Subjected to Plastic Flow and Creep

Description: From Summary: "A finite-difference method previously presented for computing elastic stresses in rotating disks is extended to include the computation of the disk stresses when plastic flow and creep are considered. A finite-difference method is employed to eliminate numerical integration and to permit nontechnical personnel to make the calculations with a minimum of engineering supervision. Illustrative examples are included to facilitated explanation of the procedure by carrying out the compu… more
Date: 1948
Creator: Millenson, M. B. & Manson, S. S.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Efficiency of Radial-Flow Turbine of Turbo Engineering Corporation TTT13-18 Turbosupercharger

Description: Memorandum presenting an investigation of the radial-flow turbine of the Turbo Engineering Corporation TT13-18 turbosupercharger made to evaluate the effects of inlet total pressure, inlet total temperature, and pressure ratio on the adiabatic efficiency. The results are presented by three efficiency parameters. Maximum efficiency obtained, based on total-pressure ratio and corrected for bearing friction, was 0.82 at an inlet total pressure of 50 inches of mercury absolute, an inlet total tempe… more
Date: 1948
Creator: Coulter, Earl E. & Galloway, William R.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Analysis of Performance of Jet Engine From Characteristics of Components 2: Interaction of Components as Determined From Engine Operation

Description: "In order to understand the operation and the interaction of jet-engine components during engine operation and to determine how component characteristics may be used to compute engine performance, a method to analyze and to estimate performance of such engines was devised and applied to the study of the characteristics of a research turbojet engine built for this investigation. An attempt was made to correlate turbine performance obtained from engine experiments with that obtained by the simple… more
Date: June 2, 1948
Creator: Goldstein, Arthur W.; Alpert, Sumner; Beede, William & Kovach, Karl
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Tentative Specification for Waste Heat Steam Boiler

Description: Report discussing specifications for the design of a waste heat steam boiler "for the purpose of generating steam to operate a condensing steam turbine electric generator from the clean hot radioactive air that has cooled the atomic energy reactor of [a] laboratory under a pressure less than atmospheric."
Date: August 1, 1948
Creator: Williams, C.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Cooling of gas turbines 9: cooling effects from use of ceramic coatings on water-cooled turbine blades

Description: From Summary: "The hottest part of a turbine blade is likely to be the trailing portion. When the blades are cooled and when water is used as the coolant, the cooling passages are placed as close as possible to the trailing edge in order to cool this portion. In some cases, however, the trailing portion of the blade is so narrow, for aerodynamic reasons, that water passages cannot be located very near the trailing edge. Because ceramic coatings offer the possibility of protection for the traili… more
Date: October 13, 1948
Creator: Brown, W. Byron & Livingood, John N. B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of a 4000-Pound-Thrust Axial-Flow Turbojet Engine 5 - Analysis of Turbine Performance

Description: "Performance characteristics of the turbine of a 4000-pound-thrust axial-flow turbojet engine was determined in investigations of the complete engine in the NACA Cleveland altitude wind tunnel. Characteristics are presented as functions of the total-pressure ratio across the turbine and of turbine speed and gas flow corrected to sea-level conditions. Three turbine nozzles of different areas were used to determine the area that gave optimum performance" (p. 1).
Date: August 4, 1948
Creator: Krebs, Richard P. & Hensley, Reece V.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Altitude-Wind-Tunnel Investigation of a 3000-Pound-Thrust Axial-Flow Turbojet Engine 1 - Analysis of Turbine Performance

Description: A wind tunnel investigation was conducted to determine the performance of a turbine operating as an integral part of a turbojet engine. Data was obtained while the engine was running over full operable range of speeds at various altitudes and flight mach numbers, and with four nozzles of different outlet areas.A maximum turbine efficiency of 0.875 was obtained at altitude of 15 thousand feet, Mach number 0.53, and corrected turbine speed of 5900 rpm.
Date: August 23, 1948
Creator: Conrad, Earl W.; Dietz, Robert O., Jr. & Golladay, Richard L.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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