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Author : Toshiyuki Arima
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (136 download)
Download or read book The Flow Field in the Tip Clearance Region of an Axial Compressor Rotor written by Toshiyuki Arima and published by . This book was released on 1999 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Toshiyuki Arima
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (137 download)
Download or read book The flow field in the tip clearance region of an axial compressor rotor, ASME 99-GT-340 written by Toshiyuki Arima and published by . This book was released on 1999 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Indianapolis, Indiana, Jun 7-Jun 10, 1999.
Author :
Publisher :
ISBN 13 :
Total Pages : 321 pages
Book Rating : 4.:/5 (946 download)
Download or read book Stepped Tip Gap Effects on a Transonic Axial-Flow Compressor Rotor written by and published by . This book was released on 1997 with total page 321 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of stepped tip gaps and clearance levels on the performance, flowfield, and stall characteristics of a transonic axial-flow compressor rotor were experimentally and numerically determined. A theory and mechanism for relocation of blockage in the rotor tip region was developed. A two-stage compressor with no inlet guide vanes was tested in the Wright Laboratories Compressor Research Facility located at Wright-Patterson Air Force Base, Ohio. The first-stage rotor was unswept and was tested for an optimum tip clearance with variations in stepped gaps machined into the casing near the aft tip region of the rotor. Nine casing geometries were investigated consisting of three step profiles at each of three clearance levels. For small and intermediate clearances, stepped tip gaps were found to improve pressure ratio, efficiency, and flow range for most operating conditions. At 100% design rotor speed, stepped tip gaps produced a doubling of mass flow range with as much as a 2.0% increase in mass flow and a 1.5% improvement in efficiency The flowfield characteristics associated with performance improvements were experimentally and numerically analyzed. Stepped tip gaps were found to have no significant effect on the stall characteristics of the rotor; the stability characteristics attributable to tip geometry were determined by the clearance over the forward portion of the rotor blade. This study provides guidelines for engineers to improve compressor performance for an existing design by applying an optimum casing profile.
Author : Donald W. Thompson
Publisher :
ISBN 13 : 9781423572473
Total Pages : 321 pages
Book Rating : 4.5/5 (724 download)
Download or read book Stepped Tip Gap Effects on a Transonic Axial-Flow Compressor Rotor written by Donald W. Thompson and published by . This book was released on 1997-06-01 with total page 321 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of stepped tip gaps and clearance levels on the performance, flowfield, and stall characteristics of a transonic axial-flow compressor rotor were experimentally and numerically determined. A theory and mechanism for relocation of blockage in the rotor tip region was developed. A two-stage compressor with no inlet guide vanes was tested in the Wright Laboratories Compressor Research Facility located at Wright-Patterson Air Force Base, Ohio. The first-stage rotor was unswept and was tested for an optimum tip clearance with variations in stepped gaps machined into the casing near the aft tip region of the rotor. Nine casing geometries were investigated consisting of three step profiles at each of three clearance levels. For small and intermediate clearances, stepped tip gaps were found to improve pressure ratio, efficiency, and flow range for most operating conditions. At 100% design rotor speed, stepped tip gaps produced a doubling of mass flow range with as much as a 2.0% increase in mass flow and a 1.5% improvement in efficiency The flowfield characteristics associated with performance improvements were experimentally and numerically analyzed. Stepped tip gaps were found to have no significant effect on the stall characteristics of the rotor; the stability characteristics attributable to tip geometry were determined by the clearance over the forward portion of the rotor blade. This study provides guidelines for engineers to improve compressor performance for an existing design by applying an optimum casing profile.
Author :
Publisher :
ISBN 13 :
Total Pages : 310 pages
Book Rating : 4.0/5 ( download)
Download or read book Tip Clearance Effects in Axial Turbomachines written by and published by . This book was released on 1986 with total page 310 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : C. Sieverding
Publisher :
ISBN 13 :
Total Pages : 522 pages
Book Rating : 4.:/5 (318 download)
Download or read book Tip Clearance Effects in Axial Turbomachines written by C. Sieverding and published by . This book was released on 1985 with total page 522 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :
Publisher :
ISBN 13 :
Total Pages : 28 pages
Book Rating : 4.:/5 (317 download)
Download or read book Recommendations for Achieving Accurate Numerical Simulation of Tip Clearance Flows in Transonic Compressor Rotors written by and published by . This book was released on 2000 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Stephanie April Weichert
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (86 download)
Download or read book Tip Clearance Flows in Axial Compressors written by Stephanie April Weichert and published by . This book was released on 2012 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The flow in the rotor tip clearance gap in an axial compressor influences the loss levels and the stall onset point. The role of tip clearance flows in the stall inception process is still debated, though. The aim of this thesis is to improve the fundamental understanding of the tip clearance flow field and its role in the stall inception process. The knowledge gained is used to develop a new casing treatment for an aero-engine core compressor. Detailed static pressure, total pressure, and velocity measurements were made in the rotor tip clearance gap at design and near stall flow conditions. The resulting overtip flow maps showed the flow field in more detail than previously possible. Flow variations around the annulus and among blade passages were analyzed and found to increase as stall is approached. This increase was not uniform around the annulus or among passages; instead, some blade passages exhibited unique behaviour compared to all the other passages. The flow variations in the unique passages were linked to small physical irregularities in compressor blading. Detailed overtip measurements were also made at stall inception to investigate the formation of the spike disturbance. These measurements, the first of their kind, showed that the disturbance which initiates the formation of the spike destabilizes the boundary between the reversed flow and incoming flow. After destabilization, reversed flow increasingly dominates the passage until the neighbouring passage is affected. The spike was found to originate most often from those regions in the compressor where the flow variations are highest and was not, as suggested by some research, associated with the forward movement of the tip leakage vortex. A new casing treatment for axial compressors was proposed and tested. The casing treatment extracts air from over the rotor blade tips and re-injects it upstream of the rotor blade leading edges into the tip region through discrete re-circulation loops. The overtip location of air extraction is unique and enables self-regulation of the amount of flow re-circulated: a minimum amount of air is re-circulated at compressor design conditions (thus minimizing any loss of efficiency) and a maximum amount of air is re-circulated near the stability limit (thus maximizing stall margin). Modest stall margin improvements (2%) were achieved without any loss of compressor efficiency at design conditions.
Author : American Society of Mechanical Engineers. Fluids Engineering Division
Publisher :
ISBN 13 :
Total Pages : 1092 pages
Book Rating : 4.E/5 ( download)
Download or read book Proceedings of the ASME Fluids Engineering Division Summer Conference, 2006: Forums written by American Society of Mechanical Engineers. Fluids Engineering Division and published by . This book was released on 2006 with total page 1092 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : A. Pandya
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (137 download)
Download or read book Investigation of the Tip-clearance Flow Inside and at the Exit of a Compressor Rotor Passage.Part I: Mean Velocity Field written by A. Pandya and published by . This book was released on 1982 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Michael Casey
Publisher : Cambridge University Press
ISBN 13 : 1108416675
Total Pages : 789 pages
Book Rating : 4.1/5 (84 download)
Download or read book Radial Flow Turbocompressors written by Michael Casey and published by Cambridge University Press. This book was released on 2021-06-10 with total page 789 pages. Available in PDF, EPUB and Kindle. Book excerpt: An introduction to the theory and engineering practice that underpins the component design and analysis of radial flow turbocompressors. Drawing upon an extensive theoretical background and years of practical experience, the authors provide descriptions of applications, concepts, component design, analysis tools, performance maps, flow stability, and structural integrity, with illustrative examples. Features wide coverage of all types of radial compressor over many applications unified by the consistent use of dimensional analysis. Discusses the methods needed to analyse the performance, flow, and mechanical integrity that underpin the design of efficient centrifugal compressors with good flow range and stability. Includes explanation of the design of all radial compressor components, including inlet guide vanes, impellers, diffusers, volutes, return channels, de-swirl vanes and side-streams. Suitable as a reference for advanced students of turbomachinery, and a perfect tool for practising mechanical and aerospace engineers already within the field and those just entering it.
Author :
Publisher :
ISBN 13 :
Total Pages : 400 pages
Book Rating : 4.3/5 (243 download)
Download or read book Applied mechanics reviews written by and published by . This book was released on 1948 with total page 400 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Siegfried Wagner
Publisher : Springer Science & Business Media
ISBN 13 : 3540454667
Total Pages : 431 pages
Book Rating : 4.5/5 (44 download)
Download or read book New Results in Numerical and Experimental Fluid Mechanics III written by Siegfried Wagner and published by Springer Science & Business Media. This book was released on 2012-09-07 with total page 431 pages. Available in PDF, EPUB and Kindle. Book excerpt: This volume contains the papers of a German symposium dealing with research and project work in numerical and experimental aerodynamics and fluidmechanics for aerospace and other applications. It gives a broad overview over the ongoing work in this field in Germany.
Author : Robert O. Bullock
Publisher :
ISBN 13 :
Total Pages : 552 pages
Book Rating : 4.:/5 (317 download)
Download or read book Aerodynamic Design of Axial Flow Compressors written by Robert O. Bullock and published by . This book was released on 1965 with total page 552 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : B. Lakshimarayana
Publisher :
ISBN 13 :
Total Pages : 0 pages
Book Rating : 4.:/5 (137 download)
Download or read book Three-dimensional Flow Field in the Tip Region of a Compressor Rotor Passage.Part I: Mean Velocity Profiles and Annulus Wall Boundary Layer written by B. Lakshimarayana and published by . This book was released on 1982 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : National Aeronautics and Space Adm Nasa
Publisher : Independently Published
ISBN 13 : 9781793919175
Total Pages : 26 pages
Book Rating : 4.9/5 (191 download)
Download or read book Large Eddy Simulation of Transonic Flow Field in NASA Rotor 37 written by National Aeronautics and Space Adm Nasa and published by Independently Published. This book was released on 2019-01-14 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt: The current paper reports on numerical investigations on the flow characteristics in a transonic axial compressor, NASA Rotor 37. The flow field was used previously as a CFD blind test case conducted by American Society of Mechanical Engineers in 1994. Since the CFD blind-test exercise, many numerical studies on the flow field in the NASA Rotor 37 have been reported. Although steady improvements have been reported in both numerical procedure and turbulence closure, it is believed that all the important aspects of the flow field have not been fully explained with numerical studies based on the Reynolds Averaged Navier-Stokes (RANS) solution. Experimental data show large dip in total pressure distribution near the hub at downstream of the rotor at 100% rotor speed. Most original numerical solutions from the blind test exercise did not predict this total pressure deficit correctly. This total pressure deficit at the rotor exit was attributed to a hub corner flow separation by the author. Several subsequent numerical studies with different turbulence closure model also calculated this dip in total pressure rise. Also, several studies attributed this total pressure deficit to a small leakage flow coming from the hub in the test article. As the experimental study cannot be repeated, either explanation cannot be validated. The primary purpose of the current investigation is to investigate the transonic flow field with both RANS and a Large Eddy Simulation (LES). The RANS approach gives similar results presented at the original blind test exercise. Although the RANS calculates higher overall total pressure rise, the total pressure deficit near the hub is calculated correctly. The numerical solution shows that the total pressure deficit is due to a hub corner flow separation. The calculated pressure rise from the LES agrees better with the measured total pressure rise especially near the casing area where the passage shock interacts with the tip clearance vortex and flow bec
Author : Jinrong Zhu
Publisher : CRC Press
ISBN 13 : 0203829859
Total Pages : 210 pages
Book Rating : 4.2/5 (38 download)
Download or read book Modelling and Computation in Engineering written by Jinrong Zhu and published by CRC Press. This book was released on 2010-10-06 with total page 210 pages. Available in PDF, EPUB and Kindle. Book excerpt: In recent years the theory and technology of modelling and computation in engineering has expanded rapidly, and has been widely applied in various kinds of engineering projects. Modelling and Computation in Engineering is a collection of 37 contributions, which cover the state-of-the-art on a broad range of topics, including:- Tunnelling- Seismic r
