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Compressor Instability with Integral Methods

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en Limba Engleză Hardback – 08 Aug 2007
"Compressor Instability with Integral Methods" is a book, to bring together the quick integral approaches and advances in the field for the prediction of stall and surge problem in compressor. This 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 be served as a self-study material to those who keen to acquire this knowledge.
In brief, this book focuses on the numerical/computational analysis for the effect of distorted inlet flow propagation on the rotating stall and surge in axial compressors. It gains insight into the basic phenomena controlling these flow instabilities, and reveals the influence of inlet parameters on rotating stall and surge. The book starts from the confirmation and application of Kim et al's integral method and then follows by a development to this method through the proposing and applying a critical distortion line. This line is applied successfully on the stall prediction of in-flight compressor due to flamming of refueling leakage near inlet, a typical real and interesting example of compressor stall and surge operation. Further, after a parametric study on the integral method and the distorted flow field of compressor using Taguchi method, a novel integral method is formulated using more appropriate and practical airfoil characteristics, with a less assumptions needed for derivation. Finally, as an extended work, the famous Greitzer's instability flow model, the well-known B-parameter model applied for analyzing the stall and surge characteristics, is studied parametrically using Taguchi method.
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Specificații

ISBN-13: 9783540724117
ISBN-10: 3540724117
Pagini: 160
Ilustrații: XXIV, 134 p. 67 illus.
Dimensiuni: 155 x 235 x 17 mm
Greutate: 0.45 kg
Ediția: 2007
Editura: Springer Berlin, Heidelberg
Colecția Springer
Locul publicării: Berlin, Heidelberg, Germany

Public țintă

Research

Cuprins

Study on the Propagation of Inlet Flow Distortion in Axial Compressor Using an Integral Method.- Stall Prediction of In-flight Compressor due to Flaming of Refueling Leakage near Inlet.- Parametric Study of Inlet Distortion Propagation in Compressor with Integral Approach and Taguchi Method.- A Development of Novel Integral Method for Prediction of Distorted Inlet Flow Propagation in Axial Compressor.- Parametric Study of Greitzer’s Instability Flow Model Through Compressor System Using Taguchi Method.

Recenzii

"This book is intended to be a reference material mainly for aeronautical engineering senior students, graduate-level students and practitioners in the aerospace industry with the essential background of college-level physics and integral calculus.
With the level of mathematics and aerodynamics involved in this book, this practical book, with its corresponding FORTRAN source codes to test associate examples and problem sets (both a novice and ranging from basic to complex), is ideal for upper-level undergraduate and graduate students in engineering to provide an opportunity for essential practice. It focuses on the improved integral methods applied to the distorted flow analysis. Throughout the text, numerous in-flight examples from both the commercial and military compressors show readers how the concepts and effective calculations are applied to real-life operations. The unique book also serves as a reference for design engineers who want a set of simple and fast methods to predict the performance of axial compressor."
Prof. Sadanari Mochizuki, Ph.D.
Editor-in-Chief, The International Journal of Rotating Machinery
Department of Mechanical Systems Engineering, College of Engineering,
Tokyo University of Agriculture and Technology
 
"This book presents a mathematical treatment of axial compressor response to inlet distortion. Computational results show the requirements for stable operation and the consequences of unstable operation in terms of growth of the distorted region through the compressor, the reduction of mass flow and the change in compressor performance. The analysis shows that the compressor response depends on the magnitude of the inlet distortion, the inlet flow angle and the ratio of lift/drag coefficients of the blade. This analysis helps to understand the details of downstream response to inlet distortion in terms of mass flow reduction and changes in the level of distortion through the blade-rows of a multistage axial compressor.
The mathematical approach uses the continuity equation and the equations of motion in two dimensions. These equations are expressed in terms of differential distortion parameters which are integrated and substituted into the differential equations of motion. Numerical integration is performed by the fourth order Runge-Kutta technique, and solutions are presented for various levels of distortion. In Chapter 2, results of sample calculations shown in Figs. 2.4, 2.5 and 2.6 illustrate the capability of the analysis toward providing a good understanding of the details and causes of instability. Figures 2.7 and 2.8 are good illustrations of the ability of the method to replicate the compressor characteristics in stall. This is very good."
The book could be a valuable reference toward understanding axial compressor response to inlet distortion through its mathematical and analytical treatments."
Professor Dr. Ronald C. Pampreen, Ph.D.
Professional Development Programme, Concepts ETI, Inc.
Concepts NREC, Massachussetts, USA
 
"This book manages to cover an analysis for the effect of distorted inlet flow propagation on the rotating stall and surge in axial compressors in a relatively compact way and could form a useful introductory text. It provides an insight into the basic phenomena controlling the compressor flow instabilities, and to reveal the influence of inlet parameters on rotating stall and surge. These useful technical details are interesting. The authors frequently illustrate the formulae they provide with specific numerical examples which helps to put them in context. In all, this is a book written with much time, effort and consideration. It is a one of a kind advance engineer book written by Singaporean for the local engineers in mind."
Dr. Chen Chuck, Ph.D.
Principal Scientist, 
The Boeing Company, 
Seattle, WA, USA
"This book gives basic guidance on a much broader range of compressor stall and surge topics than is usually seen in books aimed at non-engineers. It can be used as a specialized topic of senior undergraduate or graduate study in the flow instabilities analysis, design and testing the influence of inlet parameters of axial compressor. The corresponding FORTRAN source codes to test associate examples and problem sets (both a novice and ranging from basic to complex), provides additional good material and is ideal for graduate engineering students to allow an opportunity for essential practice"
Prof. Dr. J.C. Misra, Ph.D., D.Sc.
President, Mathematical Sciences, Indian Science Congress
Editor-in-Chief, Mathematical Sciences Series
Former Head, Department of Mathematics
Former Head, School of Medical Science & Technology
Centre for Theoretical Studies, Indian Institute of Technology, Kharagpur, INDIA
 
"I particularly like the way the 5 chapters (albeit a concise book) and all the subheadings have been clearly listed in the Contents so that the reader should have little trouble in discovering where to look for the topic of interest. The section on ' in-flight example for fighter jet compressor’ is one of the better written sections as it provided practical points in showing readers how the concepts and effective computations are applied to real-life operations' ... The authors are to be warmly congratulated for having written a very useful book. I strongly recommend this textbook to professionals in industrial power and propulsion groups."
Emeritus Professor Wen-Jei Yang, Ph.D., P.E.
Department of Mechanical Engineering and of Biomedical Engineering
University of Michigan, Michigan, U.S.A.
Fellow, ASME
Founding President: The Pacific Center of Thermal-Fluids Engineering
"Based on Kim and Marble’s integral method, this book further develops this method through the proposing and applying a critical distortion line. This line is applied successfully on the stall prediction of in-flight compressor due to flamming of refueling leakage near inlet. It provides a typical real and interesting example of compressor stall and surge operation. An excellent, concise and practical guide for engineers in all the rotating machinery professions."
Professor WG Park, PhD
School of Mechanical Engineering,
Pusan National University, Korea
"This book provides an insight into the basic phenomena controlling the compressor flow instabilities, revealing the influence of inlet parameters on rotating stall and surge.  Based on its purpose, each chapter is constructed.  In other words, an extended Greitzer's instability flow model, the well-known B-parameter model applied for analyzing the stall and surge characteristics parametrically using Taguchi method are included. Thus researchers and gradient students can get much information through the
book."
Professor Shuichi TORII, PhD
Department of Mechanical System Engineering,
Kumamoto University, JAPAN
"This book packs a big punch for its size. Each chapter is written concisely and ends with a list of sources of additional information for those who are interested where appropriate. The book is understandable and useful to the engineering community."
Dr. Akira GOTO, PhD
Director and Board Member, Ebara Research Co., Ltd 
Deputy Division Executive,
Fluid Machinery Development Division
Fluid Machinery and Systems Company
Ebara Corporation, Tokyo, Japan 
"The book is well worth the price and should be useful reading for rotating machinery professionals ... This book's title accurately reflects its contents and it has excellent chapters as to make it very worthwhile reading."
Dr. J.T. Kshirsagar, Ph.D.
Head of R & D Technology, Kirloskar Brothers Limited, Pune, India
Distinguished Visiting Professor at I.I.T. Madras, I.I.T. Roorkee, I.I.T. Bombay, India
"Flow instability, stall and surge are inter-related, and hence together constitute an intriguing phenomenon that governs axial compressor performance. This fascinating and wonderful book is unique in addressing the inlet flow distortion features and their unsteady propagation characteristics of compression process. The flow governing formulations of the various chapters are not only sufficiently rigorous to be instructive for aeronautics courses, but are also practically oriented."

Prof. Dr. Mohd. Zamri, Yusoff, Ph.D.
Dean, College of Engineering,
Universiti Tenaga Nasional, Malaysia
"This is an outstanding and interesting book ... cuts through the mystery and complexity of a subject that haunts many compressor designers and allows new integral approach to the flow instability prediction. It is a must read for both engineers and turbomachinery professions."
Dr. K.C. Ng, Ph.D.
Department of Research & Applications,
O.Y.L. R & D Center, Selangor, Malaysia.

Textul de pe ultima copertă

"Compressor Instability with Integral Methods" is a book, to bring together the quick integral approaches and advances in the field for the prediction of stall and surge problem in compressor. This 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 be served as a self-study material to those who keen to acquire this knowledge.
In brief, this book focuses on the numerical/computational analysis for the effect of distorted inlet flow propagation on the rotating stall and surge in axial compressors. It gains insight into the basic phenomena controlling these flow instabilities, and reveals the influence of inlet parameters on rotating stall and surge. The book starts from the confirmation and application of Kim et al's integral method and then follows by a development to this method through the proposing and applying a critical distortion line. This line is applied successfully on the stall prediction of in-flight compressor due to flamming of refueling leakage near inlet, a typical real and interesting example of compressor stall and surge operation. Further, after a parametric study on the integral method and the distorted flow field of compressor using Taguchi method, a novel integral method is formulated using more appropriate and practical airfoil characteristics, with a less assumptions needed for derivation. Finally, as an extended work, the famous Greitzer's instability flow model, the well-known B-parameter model applied for analyzing the stall and surge characteristics, is studied parametrically using Taguchi method.

Caracteristici

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