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Experimental investigation of acceleration characteristics of a turbojet engine including regions of surge and stall for control applications

Description: The acceleration characteristics, in the region of maximum acceleration and compressor stall and surge, of an axial-flow turbojet engine with a fixed-area exhaust nozzle were determined by subjecting the engine to fuel flow steps, ramps, and ramps with a sine wave superimposed. From the data obtained, the effectiveness of an optimalizer type of control for this engine was evaluated. At all speeds above 40 percent of rated, a maximum acceleration was not obtained until the engine reached the poi… more
Date: December 20, 1954
Creator: Stiglic, Paul M.; Schmidt, Ross D. & Delio, Gene J.
Item Type: Refine your search to only Report
open access

A Semiempirical Procedure for Estimating Wing Buffet Loads in the Transonic Region

Description: Report presenting wing buffeting data obtained from a flight loads investigation of two jet-propelled swept-wing airplanes to study the effects of Mach number and reduced frequency on the wing buffet loads. Consistent trends were noted between the flight testing and wind-tunnel testing that the results of this particular test were compared with. Results regarding variation with penetration and dynamic pressure, variation with Mach number and reduced frequency, and estimation of wing buffet load… more
Date: September 14, 1956
Creator: Skopinski, T. H. & Huston, Wilber B.
Item Type: Refine your search to only Report
open access

Component performance investigation of J71 experimental turbine 1: Over-all performance with 97-percent-design stator areas

Description: From Summary: "The over-all component performance characteristics of a J71 experimental three-stage turbine with 97 percent design stator areas were determined over a range of speed and pressure ratio at inlet-air conditions of approximately 35 inches of mercury absolute and 700 degrees R. The turbine break internal efficiency at design operating conditions was 0.877; the maximum efficiency of 0.886 occurred at a pressure ratio of 4.0 at 120 percent of design equivalent rotor speed. In general,… more
Date: April 11, 1956
Creator: Schum, Harold J. & Davison, Elmer H.
Item Type: Refine your search to only Report
open access

Temperature in a J47-25 Turbojet-Engine Combustor and Turbine Sections During Steady-State and Transient Operation in a Sea-Level Test Stand

Description: From Summary: "In order to determine the conditions of engine operation causing the most severe thermal stresses in the hot parts of a turbojet engine, a J47-25 engine was instrumented with thermocouples and operated to obtain engine material temperatures under steady-state and transient conditions. Temperatures measured during rated take-off conditions of nozzle guide vanes downstream of a single combustor differed on the order of 400 degrees F depending on the relation of the blades position … more
Date: June 3, 1955
Creator: Morse, C. R. & Johnston, J. R.
Item Type: Refine your search to only Report
open access

Investigation of turbines suitable for use in a turbojet engine with high compressor pressure ratio and low compressor-tip speed 6: experimental performance of two-stage turbine

Description: The brake internal efficiency of the highly loaded two-stage turbine was 0.79 equivalent design work and speed. The maximum brake internal efficiency was 0.84. A radial survey revealed these major defects: (1) the first-rotor throat area was too large, and a large area of underturned flow existed near the tip;(2) considerable underturning existed at the second-stator outlet; and (3) tangential components of velocity at the turbine outlet amounted to 2.5 points in turbine efficiency.
Date: August 20, 1956
Creator: Davison, Elmer H.; Schum, Harold J. & Petrash, Donald A.
Item Type: Refine your search to only Report
open access

Wind-Tunnel Investigation at Mach Numbers From 0.8 to 1.4 of Static Longitudinal and Lateral-Directional Characteristics of an Unswept-Wing Airplane Model

Description: "Results are presented for a wind-tunnel investigation of an airplane model with a 3.4-percent-thick unswept wing of aspect ratio 2.45 at Mach numbers from 0.8 to 1.4 at a Reynolds number of 1.5 million. Longitudinal characteristics are presented for the basic model and for configuration variations involving two types of wing camber, an area-rule fuselage modification, various external-store arrangements, several conventional missile installations and one designed according to the moment-of-are… more
Date: December 13, 1956
Creator: Summers, James L.; Treon, Stuart L. & Graham, Lawrence A.
Item Type: Refine your search to only Report
open access

Aerodynamic design of axial-flow compressors: Volume 3

Description: Chapters XI to XIII concern the unsteady compressor operation arising when compressor blade elements stall. The fields of compressor stall and surge are reviewed in Chapters XI and XII, respectively. The part-speed operating problem in high-pressure-ratio multistage axial-flow compressors is analyzed in Chapter XIII. Chapter XIV summarizes design methods and theories that extend beyond the simplified two-dimensional approach used previously in the report. Chapter XV extends this three-dimension… more
Date: August 1, 1956
Creator: Johnsen, Irving A.; Bullock, Robert O.; Graham, Robert W.; Costilow, Eleanor L.; Huppert, Merle C.; Benser, William A. et al.
Item Type: Refine your search to only Report
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