12 Matching Results

Search Results

Advanced search parameters have been applied.
in creator/contributor: "Medeiros, Arthur A."  
Results: 1 - 12
open access

Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 5 - Effect on Over-All Performance Characteristics of a 20-Percent Reduction in Solidity of the Fourteenth Through Sixteenth Stage Rotors

Description: The performance of a 16-stage axial-flow compressor, in which the mean-radius solidity was reduced from 1.28 to 1.02 in the fourteenth through sixteenth stage rotors was determined. The performance of this modification was compared with that of the compressor with original rotors. The reduced solidity resulted in slightly improved performance.
Date: April 21, 1952
Creator: Medeiros, Arthur A. & Hatch, James E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 3 - Effect on Over-All Performance Characteristics on Increasing Stator-Blade Angles in Inlet Stages

Description: The stator-blade angles in the first four stages of a 16-stage axial-flow compressor were increased in order to decrease the angles of attack of these stages, and thereby to improve part-speed performance. The performance of this modified compressor was compared with that of the same compressor with original blade angles.
Date: February 15, 1952
Creator: Medeiros, Arthur A. & Hatch, James E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Various Blade Modifications in Performance of a 16-Stage Axial-flow Compressor. 4 - Effect on Over-all Performance Characteristics of Decreasing Twelfth through Fifteenth Stage Stator-blade Angles 3 deg and Increasing Stator Angles in the Inlet Stages

Description: "The performance of a 16-stage axial-flow compressor, in which two modifications of unloaded inlet stages were combined with loaded exit stages, has been determined. In the first modification the exit stages were loaded by decreasing the twelfth through fifteenth stage stator angles 3 deg. as compared with the blade angles in the original compressor, and the inlet stages were unloaded by increasing the blade angles the following amounts: guide vanes and first-stage stator, 6 deg; second- and th… more
Date: March 17, 1952
Creator: Hatch, James E. & Medeiros, Arthur A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Various Blade Modifications on Performance of a 16-Stage Axial-Flow Compressor 2 - Effect on Over-All Performance Characteristics of Increasing Twelfth through Fifteenth Stage Stator-Blade Angles 3 Degrees

Description: The stator-blade angles in the twelfth through fifteenth stages of a 16-stage axial-flow compressor were increased 3O. The over-all performance of this modified compressor is compared to the performance of the compressor with original blade angles. The matching characteristics of the modified compressor and a two-stage turbine were obtained and compared to those of the compressor with original blade angles and the same turbine.
Date: January 5, 1952
Creator: Hatch, James E. & Medeiros, Arthur A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Inlet-Guide-Vane Angle on Blade Vibration and Rotating Stall of 13-Stage Axial-Flow Compressor in Turbojet Engine

Description: Report presenting a blade-vibration and rotating-stall survey on a modified version of a production turbojet engine with a 13-stage axial-flow compressor with a design pressure ratio of 7 and an air flow of 120 pounds per second. This testing was carried out due to the problems rotating stall can cause with both experimental and production axial-flow compressors. Results regarding the rotating-stall patterns, rotor-blade vibrations, radial and axial strength of rotating stall, and maximum rotat… more
Date: May 22, 1956
Creator: Calvert, Howard F.; Medeiros, Arthur A. & Johnson, Donald F.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Analysis of Off-Design Performance of a 16-Stage Axial-Flow Compressor With Various Blade Modifications

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" (p. 1).
Date: March 5, 1953
Creator: Medeiros, Arthur A.; Benser, William A. & Hatch, James E.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Inlet Temperature on Rotating Stall and Blade Vibrations in a Multistage Axial-Flow Compressor

Description: Report presenting rotating-stall and blade-vibration data for the first three rotor blade rows of a 13-stage axial-flow compressor at several inlet temperatures. Stall patterns of 1 through 5 stall zones were detected at all inlet temperatures in the equivalent compressor speed ranges between 4600 and 6200 rpm.
Date: August 5, 1955
Creator: Medeiros, Arthur A.; Calvert, Howard F. & Fenn, David B.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

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

Rotating-Stall and Rotor-Blade-Vibration Survey of a 13-Stage Axial-Flow Compressor in a Turbojet Engine

Description: Report presenting a blade-vibration and rotating-stall survey on a production turbojet engine with a 13-stage axial-flow compressor with a pressure ratio of 7 and an air flow of 120 pounds per second. Results regarding stall patterns, maximum vibratory stresses, and location of the stall zones are provided.
Date: April 29, 1955
Creator: Calvert, Howard F.; Braithwaite, Willis M. & Medeiros, Arthur A.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
open access

Effect of Various Blade Modifications on Performance of a 16-Stage High-Pressure-Ratio Axial-Flow Compressor 1 - Effect on Over-All Performance Characteristics of Decreasing Twelfth Through Fifteenth State Stator-Blade Angles 3 Degrees

Description: The stator-blade angles in the twelfth to fifteenth stages of a 16-stage high-pressure-ratio axial-flow compressor were decreased 3 deg The over-all performance of this compressor is compared with the performance of the same compressor with standard blade angles. The matching characteristics of the modified compressor and a two-stage turbine were also obtained and compared with those of the compressor with the original blade angles and the same turbine.
Date: January 22, 1952
Creator: Medeiros, Arthur A.; Hatch, James E. & Dugan, James F., Jr.
Item Type: Refine your search to only Report
Partner: UNT Libraries Government Documents Department
Back to Top of Screen