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Application of a characteristic blade-to-blade solution to flow in a supersonic rotor with varying stream-filament thickness

Description: From Introduction: "A solution of the type of reference 2 is necessary to give the stream-sheet thickness and curvature for the blade-to-blade (S1 surface) solution considered in this report. The equations for the solution of the S1 surface of revolution are presented in reference 3. The purpose of the subject report is to continue the work of reference 3 by applying the method to a specific problem in order that the practicability of the method and the time involved in computing a solution may be determined."
Date: August 1953
Creator: Costilow, Eleanor L.
Partner: UNT Libraries Government Documents Department

Experimental determination of aerodynamic forces normal to the chord due to rotating stall acting on compressor blading

Description: Report presenting an investigation conducted on an NACA axial-flow single-stage compressor with a 14-inch diameter and a 0.9 hub-tip ratio to determine the magnitude of the blade force variation due to the flow fluctuations caused by rotating stall. Results regarding steady-state blade forces, shapes of steady-state force curves, time variation in weight flow, oscillograms of strain-gage output, and effect of damping are provided.
Date: August 24, 1954
Creator: Johnson, Donald F. & Costilow, Eleanor L.
Partner: UNT Libraries Government Documents Department

A method of solving the direct and inverse problem of supersonic flow along arbitrary stream filaments of revolution in turbomachines

Description: Report presenting an analysis of the supersonic flow in two two-dimensional high-solidity cascades and in a partly supersonic symmetrical nozzle. A method is developed for the determination of the supersonic flow along stream surfaces of revolution in turbomachines. In addition to their use in direct problems, the equations can be used to design blade elements in supersonic flow along an arbitrary stream filament of revolution in turbomachines.
Date: September 1951
Creator: Wu, Chung-Hua & Costilow, Eleanor L.
Partner: UNT Libraries Government Documents Department

Rotating-stall characteristics of a rotor with high hub-tip radius ratio

Description: Report presenting an investigation of the rolling-stall characteristics of a 0.9 hub-tip ratio rotor. Stall patterns consisting of two, three, and one total-span stall zones developed in that order upon reduction of flow coefficient. Results regarding performance and stall characteristics, rotor pressure-rise coefficient, flow fluctuations due to rotating stall, pressure fluctuations due to rotating stall, temperature fluctuations due to rotating stall, and discussion of rotating stall and comparison with theory are provided.
Date: August 1955
Creator: Costilow, Eleanor L. & Huppert, Merle C.
Partner: UNT Libraries Government Documents Department

Some effects of guide-vane turning and stators on the rotating stall characteristics of a high hub-tip ratio single-stage compressor

Description: Report presenting an investigation of the rotating stall characteristics of several guide-vane-rotor and guide-vane-rotor-stator configurations. Guide vanes of 4 different turning angles were tested. Results regarding initial rotating stall point, number of stall zones formed, surge, flow fluctuations due to rotating stall, pressure fluctuations due to rotating stall, and stall propagation rate are provided.
Date: April 1956
Creator: Costilow, Eleanor L. & Huppert, Merle C.
Partner: UNT Libraries Government Documents Department

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.
Partner: UNT Libraries Government Documents Department

Analysis of flow in a subsonic mixed-flow impeller

Description: From Introduction: "A brief description of the method of analysis is presented herein considering the mean stream surface approach advanced in references 2 and 3, and both the incompressible and compressible solutions are given in detail."
Date: August 1952
Creator: Wu, Chung-Hua; Brown, Curtis A. & Costilow, Eleanor L.
Partner: UNT Libraries Government Documents Department

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-dimensional treatment by summarizing the literature on secondary flows and boundary layer effects. Charts for determining the effects of errors in design parameters and experimental measurements on compressor performance are given in Chapters XVI. Chapter XVII reviews existing literature on compressor and turbine matching techniques.
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.
Partner: UNT Libraries Government Documents Department