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Author : Allen Dean Williams
Publisher :
ISBN 13 :
Total Pages : 118 pages
Book Rating : 4.:/5 (437 download)
Download or read book The Effect of Tip Clearance Flows on Performance of Axial Flow Compressors written by Allen Dean Williams and published by . This book was released on 1960 with total page 118 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Peter Alexander Seitz
Publisher :
ISBN 13 :
Total Pages : 428 pages
Book Rating : 4.:/5 (123 download)
Download or read book The Effect of Tip Clearance Change on a Casing Treated Axial Flow Compressor written by Peter Alexander Seitz and published by . This book was released on 1993 with total page 428 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 : Ian N. Moyle
Publisher :
ISBN 13 :
Total Pages : 227 pages
Book Rating : 4.:/5 (221 download)
Download or read book An Experimental and Analytical Study of Tip Clearance Effects in Axial Flow Compressors written by Ian N. Moyle and published by . This book was released on 1991 with total page 227 pages. Available in PDF, EPUB and Kindle. Book excerpt: An analytical and experimental study of the performance changes and flow effects of rotor tip clearance variation in axial flow compressors is presented. The analyses demonstrate that previously unrecognized loss characteristics and flow behavior trends can be identified in a wide range of published tests of clearance effects. The performance and flow data are correlated at constant power conditions or nondimensionally in terms of the test compressor's geometry and wall flow conditions to observe the trends. Flow field changes caused by increasing the tip seal clearance of a low speed, large scale axial compressor having a symmetric velocity diagram were examined experimentally. The measurements were made at several clearances for one rotational speed. Synchronized blade-to-blade measurements of case wall static pressure and skin friction under the rotor tip of the second stage were collected.
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 : Dean A. Rains
Publisher :
ISBN 13 :
Total Pages : 1 pages
Book Rating : 4.:/5 (227 download)
Download or read book Tip Clearance Flows in Axial Flow Compressors and Pumps written by Dean A. Rains and published by . This book was released on 1954 with total page 1 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : M. J. P. Schmidt
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (593 download)
Download or read book Blade Tip Clearance Effects on an Axial Flow Compressor Rotor written by M. J. P. Schmidt and published by . This book was released on 1985 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : J. L. Jefferson
Publisher :
ISBN 13 :
Total Pages : 284 pages
Book Rating : 4.:/5 (15 download)
Download or read book Some Shrouding and Tip Clearance Effects in Axial Flow Compressors written by J. L. Jefferson and published by . This book was released on 1958 with total page 284 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Andrew Steven Koff
Publisher :
ISBN 13 :
Total Pages : 245 pages
Book Rating : 4.:/5 (986 download)
Download or read book Tip Clearance Effects on Multistage Axial Compressor Performance and Flow Structure for Small Core Application written by Andrew Steven Koff and published by . This book was released on 2017 with total page 245 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis describes the effect of increasing multistage axial compressor rotor blade tip clearance on embedded stage performance and flow structure for clearance-to-span ratios ranging from 1.4% to 5.6% using steady and unsteady three-dimensional viscous flow multistage computations. Embedded stage efficiency displays decreased sensitivity as rotor tip clearance increases with two flow regimes. For clearance-to-span ratios less than 3.6%, a nearly linear decrease in stage efficiency of 1.6 points per 1% increase in clearance-to-span is identified, in agreement with published literature. For clearance-to-span ratios greater than 3.6%, the computed stage efficiency decreases at a rate of 0.5 points per 1% increase in clearance-to-span. A parameter is developed that correlates with rotor tip section loss generation over a range of rotor tip clearance-to-span ratios and flow coefficients. The blade row relative streamwise tip section blockage increases in both rotor and stator passages and follows trends in rotor and stator tip section loss generation with rotor tip clearance. The tip section velocity deficit into the stator increases with tip clearance resulting in stator suction side corner flow separation, creating a challenge to design a high efficiency stage with larger tip clearance.
Author : John Kirtland Welch
Publisher :
ISBN 13 :
Total Pages : 135 pages
Book Rating : 4.:/5 (227 download)
Download or read book Experimental Investigation of the Effects of Tip Clearance and End Losses on Axial Compressor Performance written by John Kirtland Welch and published by . This book was released on 1973 with total page 135 pages. Available in PDF, EPUB and Kindle. Book excerpt: The objective of the study was to determine by experimental means the rotor efficiencies at different radii between hub and tip of a single stage axial compressor at its design point, to show the influence of tip clearance and end losses. Procedures for calibration and application of pressure probes to survey the flow in the compressor were established and programs were written to analyze the measured data. Recommendations are made for improvements of the data reduction method, which should precede experiments involving controlled changes in the blade tip clearances. (Author).
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 : S. Can Gülen
Publisher : Cambridge University Press
ISBN 13 : 1108416659
Total Pages : 735 pages
Book Rating : 4.1/5 (84 download)
Download or read book Gas Turbines for Electric Power Generation written by S. Can Gülen and published by Cambridge University Press. This book was released on 2019-02-14 with total page 735 pages. Available in PDF, EPUB and Kindle. Book excerpt: Everything you wanted to know about industrial gas turbines for electric power generation in one source with hard-to-find, hands-on technical information.
Author : John T. Sinnette (Jr.)
Publisher :
ISBN 13 :
Total Pages : 66 pages
Book Rating : 4.3/5 (91 download)
Download or read book Some Methods of Analyzing the Effect of Basic Design Variables on Axial-flow-compressor Performance written by John T. Sinnette (Jr.) and published by . This book was released on 1947 with total page 66 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author : Melvyn Savage
Publisher :
ISBN 13 :
Total Pages : 40 pages
Book Rating : 4.3/5 (91 download)
Download or read book Analysis of the Effects of Design Pressure Ratio Per Stage and Off-design Efficiency on the Operating Range of Multistage Axial-flow Compressors written by Melvyn Savage and published by . This book was released on 1950 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt: Multistage compressors composed of high-pressure-ratio stages have higher over-all off-design efficiencies and a wider operating range than those made up of low-pressure-ratio stages if the blade-row efficiency curves for the two cases are assumed to be somewhat similar.
Author : Rodrick V. Chima
Publisher :
ISBN 13 :
Total Pages : 16 pages
Book Rating : 4.:/5 (317 download)
Download or read book Calculation of Tip Clearance Effects in a Transonic Compressor Rotor written by Rodrick V. Chima and published by . This book was released on 1996 with total page 16 pages. Available in PDF, EPUB and Kindle. Book excerpt: The flow through the tip clearance region of a transonic compressor rotor (NASA rotor 37) was computed and compared to aerodynamic probe and laser anemometer data. Tip clearance effects were modeled both by gridding the clearance gap and by using a simple periodicity model across the ungridded gap. The simple model was run with both the full gap height, and with half the gap height to simulate a vena-contracta effect. Comparisons between computed and measured performance maps and downstream profiles were used to validate the models and to assess the effects of gap height on the simple clearance model. Recommendations were made concerning the use of the simple clearance model. Detailed comparisons were made between the gridded clearance gap solution and the laser anemometer data near the tip at two operating points. The computer results agreed fairly well with the data but overpredicted the extent of the casing separation and underpredicted the wake decay rate. The computations were then used to describe the interaction of the tip vortex, the passage shock, and the casing boundary layer.
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 : Richard James Williams
Publisher :
ISBN 13 :
Total Pages : pages
Book Rating : 4.:/5 (757 download)
Download or read book Large Tip Clearance Flows in High Pressure Stages of Axial Compressors written by Richard James Williams and published by . This book was released on 2009 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis investigates over tip leakage where the tip clearance is large. In the high pressure stages of axial compressors the tip clearance can be typically 6% of span and the total blockage due to tip clearance can consume in excess of forty percent of the annulus height. Experimental and computational investigations of large tip clearance in a linear cascade have been used to investigate this phenomenon. Two cascade builds have been used the first (Build A) consisted of a controlled diffusion aerofoil of low stagger and thirty degrees flow turning. The second cascade (Build B) consisted of an engine representative design with high stagger and around ten degrees of flow turning. The diffusion factor of both cascades was around 0.3. The major findings are that: Large tip clearances have a smaller detrimental influence on single row performance than the previous research would have suggested, for Build B the loss at 10% tip clearance was the same as the 0% tip clearance loss, though the overall flow turning was much reduced. An increase in blade loading towards the tip was observed with both builds. Both these phenomenon were attributed to the small amount of movement of the over tip leakage vortex. An engine representative level of inlet skew was implemented using upstream injection so to assess its influence. This was found to have a remarkably small influence on the performance of a single row with the tip clearance and geometry of the blading having a much greater influence. Finally a circumferential grooved casing treatment was applied in the linear cascade but this was found not to be an appropriate tool for such an investigation.
