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Experimental Investigation of a Five-Stage Axial-Flow Research Compressor with Transonic Rotors in All Stages 4: Blade-Element Performance

Description: Memorandum presenting the detailed blade-element performance of a five-stage axial-flow compressor for analysis purposes as well as to provide a contribution to the growing body of information necessary for continuing improvement in designing compressors. Results regarding overall and stage performance, blade-element performance, rotor blade-element performance, stator blade-element performance, comparison with design, consideration of boundary-layer blockage effects, and solution of equilibriu… more
Date: May 7, 1957
Creator: Sandercock, Donald M.
Partner: UNT Libraries Government Documents Department
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Compressibility Correction for Turning Angles of Axial-Flow Inlet Guide Vanes

Description: Note presenting a simplified extension of the Prandtl-Glauert compressibility correction for isolated airfoils, which was obtained for airfoils in cascade with axial air inlet by considering the total lift coefficient of a cascade to be composed of the sum of two components. Results regarding theoretical variations, experimental correlation, and design application are provided.
Date: December 1950
Creator: Lieblein, Seymour & Sandercock, Donald M.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of a Five-Stage Axial-Flow Research Compressor With Transonic Rotors in All Stages 2: Compressor Over-All Performance

Description: Memorandum presenting an evaluation of the overall performance of a 20-inch-diameter five-stage compressor as the initial step in an investigation of the potential performance and problems associated with a high-stage-pressure ratio compressor. The overall performance was evaluated over a range of flows at equivalent tip speeds from 40 to 100 percent of design. Results regarding the overall performance, compressor-inlet conditions, compressor-discharge conditions, stagewise variation of static … more
Date: September 8, 1954
Creator: Kovach, Karl & Sandercock, Donald M.
Partner: UNT Libraries Government Documents Department
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Experimental Investigation of a Five-Stage Axial-Flow Research Compressor With Transonic Rotors in All Stages 3: Interstage Data and Individual Stage Performance Characteristics

Description: For use in computing the detailed performance parameters of individual blade rows of a multistage compressor, radial distributions of total pressure, total temperature, static pressure and air-flow angle are tabulated. The data cover a range of air flow from choke to the approximate surge limit for equivalent rotor speeds from 70 to 100 percent of design. Equivalent stage performance curves determined from the radial survey measurements indicate both the individual performance and the matching … more
Date: October 10, 1956
Creator: Sandercock, Donald M. & Kovach, Karl
Partner: UNT Libraries Government Documents Department
open access

Experimental Investigation of a Five-Stage Axial-Flow Research Compressor with Transonic Rotors in All Stages 1: Compressor Design

Description: Memorandum presenting a five-stage axial-flow compressor with all rotor rows operating with transonic relative inlet Mach numbers designed as a research unit to study the potentialities and problems arising from the compounding of transonic stages. The report presents all design values and procedures, blade-row velocity diagrams, and the selection of blade shapes.
Date: September 8, 1954
Creator: Sandercock, Donald M.; Kovach, Karl & Lieblein, Seymour
Partner: UNT Libraries Government Documents Department
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Investigation of Performance of Axial-Flow Compressor of XT-46 Turbine-Propeller Engine 1 - Preliminary Investigation at 50-,70-, and 100-Percent Design Equivalent Speed

Description: From Summary: "An investigation is being conducted to determine the performance of the 12-stage axial-flow compressor of the XT-46 turbine-propeller engine. This compressor was designed to produce a pressure ratio of 9 at an adiabatic efficiency of 0.86. The design pressure ratios per stage were considerably greater than any employed in current aircraft gas-turbine engines using this type of compressor. The compressor performance was evaluated at two stations."
Date: May 22, 1950
Creator: Creagh, John W. R. & Sandercock, Donald M.
Partner: UNT Libraries Government Documents Department
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Experimental investigation of an axial-flow compressor inlet stage operating at transonic relative inlet Mach numbers 4: stage and blade-row performance of stage with axial-discharge stators

Description: Report presenting an investigation to determine the performance characteristics of a transonic stage designed to produce transonic inlet Mach numbers relative to a succeeding stage. Results regarding rotor performance, stator performance, and stage performance are provided.
Date: June 28, 1954
Creator: Sandercock, Donald M.; Lieblein, Seymour & Schwenk, Francis C.
Partner: UNT Libraries Government Documents Department
open access

Experimental investigation of an axial flow compressor inlet stage operating at transonic relative inlet Mach numbers 1: over-all performance of stage with transonic rotor and subsonic stators up to rotor relative inlet Mach number of 1.1

Description: Report presenting the design, construction, and investigation of an axial-flow compressor inlet stage with a maximum rotor relative inlet Mach number of 1.1. The rotor was designed for a high axial inlet velocity, no inlet guide vanes, and a tip speed of 1000 feet per second. Results regarding the overall performance, rotor inlet conditions, and stator exit conditions are provided.
Date: March 10, 1952
Creator: Lieblein, Seymour; Lewis, George W., Jr. & Sandercock, Donald M.
Partner: UNT Libraries Government Documents Department
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