Numerical Analysis of Transient Combustion Responses to Acoustic Oscillations in Axisymmetric Rocket Motors PDF Download
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Author: Tae-Seong Roh
Publisher:
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Category :
Languages : en
Pages :
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Author: Tae-Seong Roh
Publisher:
ISBN:
Category :
Languages : en
Pages :
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Book Description
Author: Tae-Seong Roh
Publisher:
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Category :
Languages : en
Pages :
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Author: Seung-Wook Baek
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Category :
Languages : en
Pages :
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Category : Aeronautics
Languages : en
Pages : 614
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Author:
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ISBN:
Category : Aeronautics
Languages : en
Pages : 614
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Author: Tae-Seong Roh
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Category :
Languages : en
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Category : Airplanes
Languages : en
Pages : 578
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Author: Zhen-Guo Wang
Publisher: John Wiley & Sons
ISBN: 1118890051
Category : Technology & Engineering
Languages : en
Pages : 509
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Book Description
This book concentrates on modeling and numerical simulations of combustion in liquid rocket engines, covering liquid propellant atomization, evaporation of liquid droplets, turbulent flows, turbulent combustion, heat transfer, and combustion instability. It presents some state of the art models and numerical methodologies in this area. The book can be categorized into two parts. Part 1 describes the modeling for each subtopic of the combustion process in the liquid rocket engines. Part 2 presents detailed numerical methodology and several representative applications in simulations of rocket engine combustion.
Author:
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Category :
Languages : en
Pages : 191
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The present report is part of a two volume set which describes a nonlinear solid rocket motor instability analysis and computer program. The primary objective of the current effort was the development and solution of a nonlinear analytical longitudinal instability model, which would allow all of the various governing phenomena to be accounted for in a coupled manner. The two primary elements of the current instability analysis are a method of characteristics solution of the two phase flow in the combustion chamber of the motor, and a coupled calculation of a transient burning rate. It is based on an extension of the most popular, linear, harmonic combustion response model. The current method allows the calculation of propellant burning response to a pressure disturbance of arbitrary waveform, for all time, including the period immediately following the initiation of the disturbance. The analysis also includes a model for velocity coupled response. The nonlinear effects of velocity coupling on the growth of pressure waves in a combustion chamber can be computed.
Author: T. S. Roh
Publisher:
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Category :
Languages : en
Pages :
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