Numerical and Experimental Investigation of Instability Inception in a High-speed Axial-flow Compressor Using Chaos Theory PDF Download
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Author: Tsuguji Nakano
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author: Tsuguji Nakano
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Author:
Publisher:
ISBN:
Category : Airplanes
Languages : en
Pages : 636
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Author: Eddie Y.K. Ng
Publisher: Springer Science & Business Media
ISBN: 3540724125
Category : Technology & Engineering
Languages : en
Pages : 154
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Book Description
This book brings together the quick integral approaches and advances in the field for the prediction of stall and surge problems in the compressor. The book is useful for people involved in the flow analysis, design and testing of rotating machinery. For students, it can be used as a specialized topic of senior undergraduate or graduate study. The book can also serve as self-study material.
Author: Gavin J. Hendricks
Publisher:
ISBN:
Category :
Languages : en
Pages : 0
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Book Description
Presented at the International Gas Turbine and Aeroengine Congress & Exhibition Birmingham, UK - June 10-13, 1996.
Author: Kenneth Lee Suder
Publisher:
ISBN:
Category : Aerodynamics, Transonic
Languages : en
Pages : 272
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Author: John R. Erwin
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 56
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Author: Willard R. Westphal
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 66
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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: M. A. Langley
Publisher:
ISBN:
Category :
Languages : en
Pages : 265
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Author: Lewis Research Center
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 542
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Author: Patrick M. Russler
Publisher:
ISBN:
Category : Axial flow compressors
Languages : en
Pages : 330
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