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Investigation of Blade Failures in a J34, Eleven-Stage Axial-Flow Compressor

Description: Report presenting a vibrational survey conducted during normal operation of a production eleven-stage axial-flow compressor powered as part of a complete turbojet engine. After serious third-stage vibration was detected, an investigation was conducted to study and eliminate the vibration with several component configurations. The vibrational source was determined to be an aerodynamic phenomenon related to a stall, but a new inlet-guide-vane assembly with a 4-percent increase in inlet area elimi… more
Date: May 18, 1953
Creator: Calvert, Howard F.; Meyer, André J., Jr. & Morse, C. Robert
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of a 10-stage subsonic axial-flow research compressor 3: investigation of rotating stall, blade vibration and surge at low and intermediate compressor speeds

Description: Report presenting an investigation of rotating stall and surge at low and intermediate speeds conducted on a 10-stage subsonic axial-flow research compressor. Fluctuations of rotating stall and surge were detected by hot-wire anemometers and pressure transducers. Results regarding overall performance and rotating stall, rotating stall and blade vibration, surge, and discussion of surge are provided.
Date: May 18, 1953
Creator: Huppert, Merle C.; Costilow, Eleanor L. & Budinger, Ray E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Investigation of Turbines for Driving Supersonic Compressors 4: Design and Performance of Second Configuration Including Study of Three-Dimensional Flow Effects

Description: Report presenting the design and experimental performance of a turbine configuration designed to drive a high-speed, high specific-weight-flow supersonic compressor. Results regarding two configurations and their work output, design weight flow, and blade loading are provided.
Date: May 18, 1953
Creator: Whitney, Warren J.; Stewart, Warner L. & Schum, Harold J.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

A wind-tunnel investigation of the aerodynamic characteristics of a full-scale supersonic-type three-blade propeller at Mach numbers to 0.96

Description: From Summary: "An investigation of the characteristics of a full-scale supersonic-type propeller has been made in the Langley 16-foot transonic tunnel with the 6000-horsepower propeller dynamometer. The tests covered a range of blade angles from 20.2 degrees to 60.2 degrees at forward Mach numbers up to 0.96. The results showed that envelope efficiency at an advance ratio of 2.8 decreased from 86 percent to 72 percent when the forward Mach number was increased from 0.70 to 0.96."
Date: May 18, 1953
Creator: Evans, Albert J. & Liner, George
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Time-History Data of Maneuvers Performed by a Republic F84G Airplane During Squadron Operational Training

Description: Preliminary results of one phase of a control-motion study program involving several jet fighter-type airplanes are presented in time-history form and are summarized as maximum measured quantities plotted against indicated airspeed. The results pertain to approximately 1,000 maneuvers performed by a Republic F-84G jet-fighter airplane during squadron operational training. The data include most tactical maneuvers of which the F-84G airplane is capable. Maneuvers were performed at pressure altitu… more
Date: May 18, 1953
Creator: Hamer, Harold A. & Mayo, Alton P.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
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