Turbomachine unsteady aerodynamics (Record no. 315817)
[ view plain ]
| 000 -LEADER | |
|---|---|
| fixed length control field | 01857pam a2200205a 44500 |
| 003 - CONTROL NUMBER IDENTIFIER | |
| control field | OSt |
| 008 - FIXED-LENGTH DATA ELEMENTS--GENERAL INFORMATION | |
| fixed length control field | 160408bc1994 xxu||||| |||| 00| 0 eng d |
| 020 ## - INTERNATIONAL STANDARD BOOK NUMBER | |
| ISBN | 812240653X |
| 040 ## - CATALOGING SOURCE | |
| Transcribing agency | IIT Kanpur |
| 041 ## - LANGUAGE CODE | |
| Language code of text/sound track or separate title | eng |
| 082 ## - DEWEY DECIMAL CLASSIFICATION NUMBER | |
| Classification number | 621.406 |
| Item number | R18tu |
| 100 ## - MAIN ENTRY--AUTHOR NAME | |
| Personal name | Rao, J. S. |
| 245 1# - TITLE STATEMENT | |
| Title | Turbomachine unsteady aerodynamics |
| Statement of responsibility, etc | J. S. Rao |
| 260 ## - PUBLICATION, DISTRIBUTION, ETC. (IMPRINT) | |
| Place of publication | New Delhi |
| Name of publisher | Wiley Eastern |
| Year of publication | 1994 |
| 300 ## - PHYSICAL DESCRIPTION | |
| Number of Pages | xi, 520p |
| 500 ## - GENERAL NOTE | |
| General note | Includes bibliographical references and index |
| 520 ## - SUMMARY, ETC. | |
| Summary, etc | The problem of blade fatigue failures is important in the design of new gas turbines. The most important information required in estimating the blade life is the non-steady force field arising out of the stage flow path interaction. This book is concerned with such information.<br/><br/>The basic principles of inviscid incompressible flows are first presented, with applications to elementary incompressible flows. The airfoil theory using conformal mapping is then given to explain the basic principles of steady aerodynamic lift, followed by two-dimensional thin airfoil theory. The unsteady thin airfoil theory due to transverse and chord-wise gusts in the upstream flow is given in detail, which is then linked to the turbomachine stage flow. The blade lift and moment calculations arising out of potential flow and vortex wakes from the neighboring row are then presented. Next, the principles of compressible flow are introduced with an extension to the turbomachine stage problem. A modified exact hydraulic analogy for isentropic flows is then introduced to study flow path interaction in a gas turbine stage. Finally, viscous flow and boundary layer theory are introduced with applications to the turbomachine blades. Thus, this book enables a designer to determine the blade's steady force field in a turbomachine. |
| 650 ## - SUBJECT ADDED ENTRY--TOPICAL TERM | |
| Topical Term | Turbomachines -- Aerodynamics |
| 942 ## - ADDED ENTRY ELEMENTS (KOHA) | |
| Koha item type | Books |
| Withdrawn status | Lost status | Damaged status | Not for loan | Collection code | Home library | Current library | Date acquired | Full call number | Accession Number | Koha item type |
|---|---|---|---|---|---|---|---|---|---|---|
| General Stacks | PK Kelkar Library, IIT Kanpur | PK Kelkar Library, IIT Kanpur | 12/08/2007 | 621.406 R18tu | A119228 | Books |