The Design and Test of a Two Stage Transonic Axial Flow Compressor PDF Download
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Author: R. G. Wells (Writer on turbomachines)
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 0
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Author: R. G. Wells (Writer on turbomachines)
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 0
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Author: Willard R. Westphal
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 66
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Book Description
A six-stage axial-flow compressor with a tip speed of 550 feet per second and a flat operating characteristics at constant speed has been designed and tested. It was designed for a constant power input per pound of flow in expectation that this would result in a wider mass-flow operating range at a given stagnation-presssure ratio. The design specific weight flow was 21.3 pounds per second per square foot of frontal area at atmospheric discharge with a stagnation-pressure ratio of 3.25 and an inlet hub-tip radius ratio of 0.7. Several configurations consisting of various blade setting angles and solidities were tested. Tests showed that the design flow, pressure ratio, and flat operating characteristic were obtained over a range of 10 percent of design flow at a peak efficiency of 82 percent for design conditions. The compressor had a possible immediate application for air removal from a large slotted-throat transonic wind tunnel, but the design theory could apply to any low-speed industrial compressor or second spool of a turbojet engine.
Author: William D. Reid
Publisher:
ISBN:
Category :
Languages : en
Pages : 102
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Test runs of the transonic axial compressor test rig at the Naval Postgraduate School, Turbopropulsion Laboratory, were conducted in preparation for the installation of a new stage design. Modifications in the cooling air supply to the high speed bearings, and to the design of the torque measuring system were completed during subsequent overhaul. A case study of the design of the new transonic stage was initiated. This consisted of a review of the procedure used in the design, as well as a design comparison. The comparison examined the differences between the blades designed for the new stage, which was primarily accomplished using a full, three- dimensional, Computational Fluid Dynamics code, and blades designed using two-dimensional streamline curvature methods. The axi-symmetric through-flow code, used in the design case study was modified to run on workstations at the Naval Postgraduate School, Department of Aeronautics and Astronautics, providing students and faculty with a design tool for single or multiple stage axial flow compressors.
Author: Katsushi Nagai
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Presented at the International Gas Turbine and Aeroengine Congress &Exhibition Birmingham, UK - June 10-13, 1996.
Author: I. M. Davidson
Publisher:
ISBN:
Category :
Languages : en
Pages : 24
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Author: Royce D. Moore
Publisher:
ISBN:
Category :
Languages : en
Pages : 108
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Author:
Publisher:
ISBN:
Category :
Languages : en
Pages : 113
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Book Description
Test runs of the transonic axial compressor test rig at the Naval Postgraduate School, Turbopropulsion Laboratory, were conducted in preparation for the installation of a new stage design. Modifications in the cooling air supply to the high speed bearings, and to the design of the torque measuring system were completed during subsequent overhaul. A case study of the design of the new transonic stage was initiated. This consisted of a review of the procedure used in the design, as well as a design comparison. The comparison examined the differences between the blades designed for the new stage, which was primarily accomplished using a full, three- dimensional, Computational Fluid Dynamics code, and blades designed using two-dimensional streamline curvature methods. The axi-symmetric through-flow code, used in the design case study was modified to run on workstations at the Naval Postgraduate School, Department of Aeronautics and Astronautics, providing students and faculty with a design tool for single or multiple stage axial flow compressors.
Author: Fang-Yuan Zhu
Publisher:
ISBN:
Category :
Languages : en
Pages : 21
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Author: Bart L. Grossman
Publisher:
ISBN: 9781423564577
Category :
Languages : en
Pages : 119
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Book Description
A test program to evaluate a new transonic axial compressor stage was conducted. The stage was designed (by Nelson Sanger of NASA Lewis) relying heavily on CFD techniques while minimizing conventional empirical design methods. The stage was installed in the NPS Transonic Compressor Test Rig and instrumented with fixed temperature and pressure probes. A new PC-based data acquisition system was commissioned and programmed for stage performance measurements. These were obtained at 50, 60, 65, 70, and 80% of the design speed before failure of the spinner retaining bolt led to the loss of the stage. The flow through the rotor was analyzed and the rotor performance predicted using a 3-dimensional viscous code (RVC3D). The predicted rotor performance agreed qualitatively and was numerically consistent with the measured stage performance.
Author: Rocco Anthony Petrone
Publisher:
ISBN:
Category :
Languages : en
Pages :
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