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Study of compressor systems for a gas-generator engine

Description: Report presenting various methods of providing compressor-capacity and pressure-ratio control in the gas-generator type of compound engine over a range of altitudes. The analytical results indicated that the best method of control is that in which the first stage of compression is carried out in a variable-speed supercharger driven by a hydraulic slip coupling. Results regarding the constant-pressure-ratio compressor, constant-volume compressor, comparison of piston-type and rotary compressors,… more
Date: April 13, 1949
Creator: Sather, Bernard I. & Tauschek, Max J.
Partner: UNT Libraries Government Documents Department
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Reynolds number effect on axial-flow compressor performance

Description: Investigation conducted in the altitude wind tunnel to study the effect of Reynolds number on the performance of an axial-flow compressor. The compressor was operated as a part of a turbojet engine over a range of pressure altitudes and compressor-inlet Reynolds numbers. Results regarding compressor efficiency, air flow, and a comparison with axial-flow compressors of different design are provided.
Date: September 15, 1949
Creator: Wallner, Lewis E. & Fleming, William A.
Partner: UNT Libraries Government Documents Department
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Design and performance of experimental axial-discharge mixed-flow compressor 2: performance of impeller

Description: Report presenting an analysis of an axial-discharge mixed-flow compressor designed to combine the compactness, reliability, and wide operating range of a mixed-flow compressor with the high flow capacity per unit of frontal area that characterizes the axial-flow compressor. The primary objective of this design was to maximize the flow capacity for a predetermined pressure ratio. Results regarding the flow distribution at the impeller inlet, flow distribution at the impeller outlet, and impeller… more
Date: August 12, 1948
Creator: Wilcox, Ward W.
Partner: UNT Libraries Government Documents Department
open access

Study of compressor systems for a gas-generator engine

Description: Various methods of providing compressor-capacity and pressure-ratio control in the gas-generator type of compound engine over a range of altitudes from sea level to 50,000 feet are presented. The analytical results indicate that the best method of control is that in which the first stage of compression is carried out in a variable-speed supercharger driven by a hydraulic slip coupling. The constant-speed second stage could be either a mixed-flow rotary compressor or a piston-type compressor. A … more
Date: October 16, 1950
Creator: Sather, Bernard I. & Tauschek, Max J.
Partner: UNT Libraries Government Documents Department
open access

Compressor Performance Characteristics of a Python Turbine-Propeller Engine Investigated in Altitude Wind Tunnel

Description: Report presenting an investigation in the altitude wind tunnel to determine the performance of the Python turbine-propeller engine. Compressor-performance data were obtained for a range of simulated altitudes at a single cowl-inlet ram pressure ratio while the engine was run over its full operable range of engine speeds. Results regarding the deterioration of compressor performance, compressor performance, including efficiency and performance maps, and velocity and static-pressure profiles are … more
Date: May 1, 1951
Creator: Jansen, Emmert T. & McAulay, John E.
Partner: UNT Libraries Government Documents Department
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Effect of inlet-air baffles on rotating-stall and stress characteristics of an axial-flow compressor in a turbojet engine

Description: Report presenting an investigation of the effect of inlet-air baffles on the rotating stall, rotor-blade vibratory stress, and performance characteristics of a compressor in an axial-flow turbojet engine. Two baffles were tested, an inside-diameter baffle extending radially outward from the hub, and an outside-diameter baffle extending radially inward from the outer casing.
Date: January 10, 1955
Creator: Huntley, S. C.; Huppert, Merle C. & Calvert, Howard F.
Partner: UNT Libraries Government Documents Department
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Axial-Flow Compressor Rotating-Stall and Rotor-Blade Vibration Survey

Description: Report presenting a compressor-rotor-blade vibration survey on a production turbojet engine incorporating a 13-stage axial-flow compressor with a pressure ratio of approximately 7 and an air flow of 120 pounds per second. The investigation was conducted due to the major problem that fatigue failures of compressor rotor blades have caused in the development of the axial-flow compressor. Results regarding rotating stall characteristics, rotor-blade vibration, and fourth-stage rotor-blade failure … more
Date: May 23, 1955
Creator: Calvert, Howard F.; Medeiros, Arthur A. & Garrett, Floyd B.
Partner: UNT Libraries Government Documents Department
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Effect of compression-inlet area blockage on performance of an experimental compressor and a hypothetical noise

Description: Report presenting an investigation to determine the effects of inlet-annulus blockage on compressor performance and its corresponding effect on the computed performance of a hypothetical engine. The hypothetical engine performance was calculated from the overall compressor performance and assumed component performance characteristics. Results regarding the compressor performance with no inlet blockage, effect of hub blockage on compressor performance and stall characteristics, effect of sector … more
Date: April 5, 1955
Creator: Filippi, Richard E. & Lucas, James G.
Partner: UNT Libraries Government Documents Department
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Effect of Inlet-Guide-Vane Angle on Performance Characteristics of a 13-Stage Axial-Flow Compressor in a Turbojet Engine

Description: Report presenting the effect of adjusting compressor inlet-guide-vane angle on overall compressor performance, stage performance, engine thrust, and specific fuel consumption in a 7000-pound-thrust turbojet engine. Data was obtained at several angles and demonstrated that increasing the guide-vane angle decreased the weight flow at the higher compressor speeds. It had no effect on stage performance other than at the first stage, where it reduced maximum flow, pressure, and temperature coefficie… more
Date: May 22, 1956
Creator: Medeiros, Arthur A. & Calvert, Howard F.
Partner: UNT Libraries Government Documents Department
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Investigation of X24C-2 10-Stage Axial-Flow Compressor 2: Effect of Inlet-Air Pressure and Temperature of Performance

Description: Effect of inlet-air pressure and temperature on the performance of the X24-2 10-Stage Axial-Flow Compressor from the X24C-2 turbojet engine was evaluated. Speeds of 80, 89, and 100 percent of equivalent design speed with inlet-air pressures of 6 and 12 inches of mercury absolute and inlet-air temperaures of approximately 538 degrees, 459 degrees,and 419 degrees R ( 79 degrees, 0 degrees, and minus 40 degrees F). Results were compared with prior investigations.
Date: August 21, 1947
Creator: Finger, Harold B.; Schum, Harold J. & Buckner, Howard A., Jr.
Partner: UNT Libraries Government Documents Department
open access

Investigation of Reynolds number effect on performance of an eight-stage axial-flow research compressor with long- and medium-chord lengths in the two transonic inlet stages

Description: Report presenting an investigation of the Reynolds number effects on an axial-flow compressor with two of the transonic inlet stages doubled as compared to the original compressor. Results regarding the long-chord-compressor performance, effect of Reynolds number on compressor performance, and a comparison of long- and medium-chord compressor performance are provided.
Date: February 18, 1958
Creator: Sievers, Gilbert K.; Geye, Richard P. & Lucas, James G.
Partner: UNT Libraries Government Documents Department
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Thrust Augmentation of a Turbojet Engine at Simulated Flight Conditions by Introduction of a Water-Alcohol Mixture into the Compressor

Description: From Summary: "An investigation was conducted at simulated high-altitude flight conditions to evaluate the use of compressor evaporative cooling as a means of turbojet-engine thrust augmentation. Comparison of the performance of the engine with water-alcohol injection at the compressor inlet, at the sixth stage of the compressor, and at the sixth and ninth stages was made. From consideration of the thrust increases achieved, the interstage injection of the coolant was considered more desirable … more
Date: August 18, 1952
Creator: Useller, James W.; Auble, Carmon M. & Harvey, Ray W., Sr.
Partner: UNT Libraries Government Documents Department
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Performance of 15-Stage Experimental J71 Axial-Flow Compressor: 2 - Individual Stage Performance Characteristics

Description: The first four stages were found to cause a major part of the poor low-speed efficiency of this compressor. The low design-speed over-all pressure ratio at surge was caused by the first and the twelfth to fifteenth stages. The multiple over-all performance curves in the intermediate-speed range were at least partly the result of double-branched characteristic curves for the third and seventh stages.
Date: October 29, 1954
Creator: Lucas, James G. & Filippi, Richard E.
Partner: UNT Libraries Government Documents Department
open access

Effect of inlet-annulus area blockage on over-all performance and stall characteristics of an experimental 15-stage axial-flow compressor

Description: Report presenting an investigation of an experimental 15-stage axial-flow compressor to determine the effect of inlet-annulus area blockage on disrupting the rotating stall and altering the overall performance and stall characteristics of the compressor. It is part of a general investigation to determine how to alleviate the general problems of blade vibration and poor off-design performance associated with compressor rotating stall.
Date: May 11, 1954
Creator: Lucas, James G.; Finger, Harold B. & Filippi, Richard E.
Partner: UNT Libraries Government Documents Department
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Performance of 15-Stage Experimental J71 Axial-Flow Compressor. 3 - Effects of Inlet-Guide-Vane Adjustment

Description: The stall-limit line at low speeds was improved somewhat by closing the inlet guide vanes 6 deg, while the design-speed maximum flow and pressure ratio were reduced. The first-stage characteristic curve was moved to lower values of both flog coefficient and equivalent pressure ratio. The second-stage pressure ratio was decreased slightly at high speeds, while the later stages were unaffected.
Date: April 20, 1955
Creator: Lucas, James G. & Filippi, Richard E.
Partner: UNT Libraries Government Documents Department
open access

Effect of rotor-and stator-blade modifications on surge performance of an 11-stage axial-flow compressor 1: original production compressor of XJ40-WE-6 engine

Description: Report presenting an investigation to increase the compressor surge-limit pressure ratio of the XJ40-WE-6 turbojet engine at high equivalent speeds. The two compressor modifications investigated included twisting rotor blades to change blade section angles and inserting new stator diaphragms with different blade angles. Results regarding the effect of surge limit on engine performance, performance map of original compressor with mixer, effect of blade modifications on surge line, effect of mixe… more
Date: May 20, 1953
Creator: Finger, Harold B.; Essig, Robert H. & Conrad, E. William
Partner: UNT Libraries Government Documents Department
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Performance of J35-A-23 Compressor 1: Over-All Performance Characteristics at Equivalent Speeds From 20 to 100 Percent of Design

Description: Report presenting an investigation of the overall performance of the J35-A-23 compressor, which is a 16-stage compressor designed to produce a total-pressure ratio of 8.75 at an equivalent flow of 155 pounds per second and an equivalent speed of 6100 rpm. Tests were run at a range of flows and speeds. Notes on installation and characteristics of the compressor are also provided.
Date: October 1, 1951
Creator: Medeiros, Arthur A.; Guentert, Donald C. & Hatch, James E.
Partner: UNT Libraries Government Documents Department
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Utilization of external-compression diffusion principle in design of shock-in-rotor supersonic compressor blading

Description: Report presenting the application of the external-compression principle to a cascade of blades in an attempt to achieve a closer approach to isentropic contraction ratios in supersonic compressor blading. Tests of a rotor designed to incorporate the external-compression principle are provided. Results regarding overall performance, performance at design speed and peak efficiency, off-design performance, and some considerations for future designs are provided.
Date: September 11, 1953
Creator: Creagh, John W. R. & Klapproth, John F.
Partner: UNT Libraries Government Documents Department
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Performance of J33-A-27 Turbojet-Engine Compressor 1: Over-all performance characteristics at equivalent impeller speeds from 6100 to 11,800 rpm

Description: The J33-A-27 compressor was operated at an inlet pressure of 14 inches of mercury absolute and ambient inlet temperature over a range of equivalent impeller speeds from 6100 to 11,800 rpm. At the design equivalent speed of 11,800 rpm, the J33-A-27 compressor had a peak pressure ratio of 4.40 at an equivalent weight flow of 105.7 pounds per second and a peak adiabatic temperature-rise efficiency of 0.745. The maximum equivalent weight flow at design speed was 113.5 pounds per second.
Date: July 11, 1949
Creator: Kovach, Karl & Osborn, Walter M.
Partner: UNT Libraries Government Documents Department
open access

Preliminary Data on the Effects of Inlet Pressure Distortions on the J57-P-1 Turbojet Engine

Description: "An investigation to determine the steady-state and surge characteristics of the J57-P-1 two-spool turbojet engine with various inlet air-flow distortions was conducted in the altitude wind tunnel at the NACA Lewis laboratory. Along with a uniform inlet total-pressure distribution, one circumferential and three radial pressure distortions were investigated. Data were obtained over a complete range of compressor speeds both with and without intercompressor air bleed at a flight Mach number of 0.… more
Date: December 3, 1954
Creator: Wallner, Lewis E.; Lubick, Robert J. & Einstein, Thomas H.
Partner: UNT Libraries Government Documents Department
open access

Performance of a 13-Stage Development Compressor for the J40-WE-24 Engine at Equivalent Speeds from 30 to 112 Percent of Design

Description: The performance of a 13-stage development compressor for the J40-WE-24 engine has been determined at equivalent speeds from 30 to 112 percent of design. The design total-pressure ratio of 6.0 and the design weight flow of 164 pounds per second were not attained, An analysis was conducted to determine the reasons for the poor performance at the design and over-design speed. The analysis indicated that most of the difficulty could be attributed to the fact that the first stage was overcompromised… more
Date: April 9, 1953
Creator: Hatch, James E.; Lucas, James G. & Finger, Harold B.
Partner: UNT Libraries Government Documents Department
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