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Partner:
UNT Libraries Government Documents Department
Decade:
1950-1959
Year:
1953
Month:
March
Acceleration of high-pressure-ratio single-spool turbojet engine as determined from component performance characteristics I : effect of air bleed at compressor outlet
Date: March 10, 1953
Creator: Rebeske, John J , Jr
Description: An analytical investigation was made to determine from component performance characteristics the effect of air bleed at the compressor outlet on the acceleration characteristics of a typical high-pressure-ratio single-spool turbojet engine. Consideration of several operating lines on the compressor performance map with two turbine-inlet temperatures showed that for a minimum acceleration time the turbine-inlet temperature should be the maximum allowable, and the operating line on the compressor map should be as close to the surge region as possible throughout the speed range. Operation along such a line would require a continuously varying bleed area. A relatively simple two-step area bleed gives only a small increase in acceleration time over a corresponding variable-area bleed. For the modes of operation considered, over 84 percent of the total acceleration time was required to accelerate through the low-speed range ; therefore, better low-speed compressor performance (higher pressure ratios and efficiencies) would give a significant reduction in acceleration time.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc59518/
Air-flow and thrust characteristics of several cylindrical cooling-air ejectors with a primary to secondary temperature ratio of 1.0
Date: March 6, 1953
Creator: Greathouse, W K
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc59617/
Analysis of off-design performance of a 16-stage axial-flow compressor with various blade modifications
Date: March 5, 1953
Creator: Medeiros, Arthur A
Description: The over-all performance of a 16-stage axial-flow compressor was determined with various stator-blade resettings and a reduction in solidity of the rotor blades in the last three stages. It was shown that little control over the sudden change in slope of the surge-limit line at intermediate speeds was obtained with the blade modifications attempted, except that some change in speed at which the change in slope occurred could be effected by stator-blade resettings. Interstage data indicated that the severe surge limit at intermediate speeds was caused by stall of the inlet stage, which, because of stage interaction effects, resulted in a simultaneous decrease in performance of the following five or six stages. Stage data are presented which indicate the flow and pressure-ratio range over which each stage is required to operate at compressor speeds from 50 to 100 percent of design speed.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc59508/
An analysis of the factors affecting the loss in lift and shift in aerodynamic center produced by the distortion of a swept wing under aerodynamic load
Date: March 1, 1953
Creator: Mathews, Charles W
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc56557/
An application of the method of characteristics to two-dimensional transonic flows with detached shock waves
Date: March 1, 1953
Creator: Harder, Keith C
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc56608/
The asymmetric adjustable supersonic nozzle for wind-tunnel application
Date: March 1, 1953
Creator: Allen, H Julian
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc56650/
Buffeting of a vertical tail on an inclined body at supersonic Mach numbers
Date: March 24, 1953
Creator: Gowen, Forrest E
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc59517/
The calculation of pressure on slender airplanes in subsonic and supersonic flow
Date: March 1, 1953
Creator: Heaslet, Max A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc56550/
Comparison of measured and predicted indicated angles of attack near the fuselages of a triangular-wing wind-tunnel model and a swept-wing fighter airplane in flight
Date: March 11, 1953
Creator: James, Harry A
Description: None
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc59546/
Comparison of theoretically and experimentally determined effects of oxide coatings supplied by fuel additives on uncooled turbine-blade temperature during transient turbojet-engine operation
Date: March 30, 1953
Creator: Schafer, Louis J
Description: An analysis was made to permit the calculation of the effectiveness of oxide coatings in retarding the transient heat flow into turbine blades when the combustion gas temperature of a turbojet engine is suddenly changed. The analysis is checked with experimental data obtained from a turbojet engine whose blades were coated with two different coating materials (silicon dioxide and boric oxide) by adding silicone oil and tributyl borate to the engine fuel. The very thin coatings (approximately 0.001 in.) that formed on the blades produced a negligible effect on the turbine-blade transient temperature response. With the analysis discussed here, it was possible to predict the turbine rotor-blade temperature response with a maximum error of 40 F.
Contributing Partner: UNT Libraries Government Documents Department
Permallink:digital.library.unt.edu/ark:/67531/metadc59578/