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Studies Of End Wall Effects On Rotating Stall Inception In Axial Compressors
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Book Synopsis Studies of End-wall Effects on Rotating Stall Inception in Axial Compressors by : Randy Shek-Ming Chue
Download or read book Studies of End-wall Effects on Rotating Stall Inception in Axial Compressors written by Randy Shek-Ming Chue and published by . This book was released on 1983 with total page 352 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis End-wall Effects on Rotating Stall Inception in Axial Compressors by : Tih-Mei Yuh
Download or read book End-wall Effects on Rotating Stall Inception in Axial Compressors written by Tih-Mei Yuh and published by . This book was released on 1981 with total page 282 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781721981618 Total Pages :354 pages Book Rating :4.9/5 (816 download)
Book Synopsis Task II by : National Aeronautics and Space Administration (NASA)
Download or read book Task II written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-06-27 with total page 354 pages. Available in PDF, EPUB and Kindle. Book excerpt: The effects of two types of flow non-uniformity on stall inception behavior were assessed with linearized stability analyses of two compressor flow models. Response to rotating tip clearance asymmetries induced by a whirling rotor shaft or rotor height variations were investigated with a two-dimensional flow model. A 3-D compressor model was also developed to study the stability of both full-span and part-span rotating stall modes in annular geometries with radial flow variations. The studies focussed on (1) understanding what compressor designs were sensitive to these types of circumferential and spanwise flow non-uniformities, and (2) situations where 2-D stability theories were inadequate because of 3-D flow effects. Rotating tip clearance non-uniformity caused the greatest performance loss for shafts whirling at the rotating stall frequency. A whirling shaft displacement of 1 percent chord caused the stalling mass flow to rise by as much as 10 percent and the peak pressure rise to decrease by 6 percent. These changes were an order of magnitude larger than for equivalent-sized stationary or rotor-locked clearance asymmetries. Spanwise flow non-uniformity always destabilized the compressor, so that 2-D models over-predicted that stall margin compared to 3-D theory. The difference increased for compressors with larger spanwise variations of characteristic slope and reduced characteristic curvature near the peak. Differences between 2-D and 3-D stall point predictions were generally unacceptable (2 - 4 percent of flow coefficient) for single-stage configurations, but were less than 1 percent for multistage compressors. 2-D analyses predicted the wrong stall mode for specific cases of radial inlet flow distortion, mismatching and annulus area contraction, where higher-order radial modes led to stall. The stability behavior of flows with circumferential or radial non-uniformity was unified through a single stability criterion. The stall point for both cases was set by...
Book Synopsis Rotating Waves as a Stall Inception Indication in Axial Compressors by : V. H. Garnier
Download or read book Rotating Waves as a Stall Inception Indication in Axial Compressors written by V. H. Garnier and published by . This book was released on 1990 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Stall inception has been studied in two low-speed compressors (a single-stage and a three-stage) and in a high-speed three-stage compressor, using temporally and spatially resolved measurements. In all three machines, rotating stall was preceded by a period in which small-amplitude waves were observed traveling around the circumference of the machine at a speed slightly less than the fully developed rotating stall cell speed. The waves evolved smoothly into rotating stall without sharp changes in phase or amplitude, implying that, in the machines tested, the prestall waves and the fully developed rotating stall are two stages of the same phenomenon. The growth rate of these disturbances was in accord with that predicted by current analytical models. The prestall waves were observed both with uniform and with distorted inflow, but were most readily discerned with uniform inflow. Engineering uses and limitations of these waves are discussed.
Book Synopsis Blade Passage Flow Structure Effects on Axial Compressor Rotating Stall Inception by : Donald Andrew Hoying
Download or read book Blade Passage Flow Structure Effects on Axial Compressor Rotating Stall Inception written by Donald Andrew Hoying and published by . This book was released on 1996 with total page 230 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research on Rotating Stall in Axial Flow Compressors by : Robert J. Vidal
Download or read book Research on Rotating Stall in Axial Flow Compressors written by Robert J. Vidal and published by . This book was released on 1959 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Three-dimensional Rotating Stall Inception and Effects of Rotating Tip Clearance Asymmetry in Axial Compressors by : Kenneth Andrew Gordon
Download or read book Three-dimensional Rotating Stall Inception and Effects of Rotating Tip Clearance Asymmetry in Axial Compressors written by Kenneth Andrew Gordon and published by . This book was released on 1999 with total page 388 pages. Available in PDF, EPUB and Kindle. Book excerpt: (Cont.) The stability behavior of flows with circumferential or radial nonuniformity was unified through a single stability criterion. The stall point for both cases was set by the integral around the annulus of the pressure rise characteristic slope, weighted by the amplitude of the mode shape. For the case of steady circumferential variations, this criterion reduced to the integrated mean slope (IMS) condition associated with steady inlet distortions. The rotating tip clearance asymmetry model was also used to demonstrate the feasibility of actively controlling the shaft position to suppress rotating stall. In axisymmetric mean flow, this method only stabilized the first harmonic mode, increasing the operating range until surge or higher harmonic modes became unstable.
Book Synopsis A Theory of Rotating Stall of Multistage Axial Compressors by : Franklin K. Moore
Download or read book A Theory of Rotating Stall of Multistage Axial Compressors written by Franklin K. Moore and published by . This book was released on 1983 with total page 96 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Observed Flow Characteristics of Rotating Stall Inception and Its Prevention Using Discrete Tip Injection in the NASA Stage 35 Axial Compressor with New Analysis Methods by : Benjamin P. Johnson
Download or read book Observed Flow Characteristics of Rotating Stall Inception and Its Prevention Using Discrete Tip Injection in the NASA Stage 35 Axial Compressor with New Analysis Methods written by Benjamin P. Johnson and published by . This book was released on 2008 with total page 120 pages. Available in PDF, EPUB and Kindle. Book excerpt: Abstract: In order to further our understanding of the effects of tip injection in preventing rotating stall, a number of computational cases were run which modeled stall inception in the NASA compressor Stage 35. The flow solver TURBO, written and developed by Dr. Jen-Ping Chen, was used and new post-processing analysis methods were implemented in these cases. These include the investigation of three-dimensional disturbance (zero axial velocity) pockets, diffusion factor analyses, angle of attack analyses, and negative axial velocity volume measurements. The utilization of these methods led to a number of observations. The first was that the three-dimensional disturbances were first formed in the mid-span of the rotor passages and then migrated to the tip region. Secondly, in both the stable and unstable cases, the disturbances travelled at 100% rotor speed around the annulus upon their inception. The third observation made was that, in stalling cases, the disturbances would eventually occupy the entire breadth of a rotor passage in the vicinity of the tip. Upon this occurrence, the disturbance would begin to propagate upstream of the leading edge of the rotor blade. It would then migrate around the rotor leading edge, merging with the disturbances in the adjacent passages while slowing to approximately 50% rotor speed. The diffusion factor and angle of attack analyses proved less conclusive than had been hoped in providing a definitive, quantitative indication of the inevitability of stall. The original hope was that one or both of these parameters would prove to be a reliable, definitive indicator of the inevitable onset of stall at a given throttle. The diffusion factor analysis provided a means to indicate qualitative differences between different cases, i.e. indicating whether one case is more likely to stall than another. The angle of attack analysis, for the most part, seemed to accurately reflect the actual flow conditions - high angles of attack were recorded for blades which exhibited leading-edge flow separation. Two cases were chosen to represent a stable and stalling case. The results of the stable case indicate that the tip injectors maintain stability in the compressor by preventing the formation of disturbances which occupy the full breadth of a given rotor passage. As the disturbances migrated toward the tip, the injectors would wash them away. To maintain stable operation, some disturbances required passage through the influence of only one injector, while in other cases passage through multiple injectors was required. The results of the unsteady case indicate that if the amount of injection is insufficient, the subsequent merging and growth of the disturbances blocks a significant portion of the rotor face and prevents sufficient mass flow from getting through, resulting in rotating stall.
Book Synopsis Research on Rotating Stall in Axial Flow Compressors. Part III. Experiments on Laminar Separation from a Moving Wall by : Robert J. Vidal
Download or read book Research on Rotating Stall in Axial Flow Compressors. Part III. Experiments on Laminar Separation from a Moving Wall written by Robert J. Vidal and published by . This book was released on 1959 with total page 26 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research on Rotating Stall in Axial Flow Compressors by : R. A. Hartunian
Download or read book Research on Rotating Stall in Axial Flow Compressors written by R. A. Hartunian and published by . This book was released on 1959 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book ASME 67-FE-16 written by G. L. Mellor and published by . This book was released on 1967 with total page 8 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Active Control of Rotating Stall in a Three-stage Axial Compressor by : Joel M. Haynes
Download or read book Active Control of Rotating Stall in a Three-stage Axial Compressor written by Joel M. Haynes and published by . This book was released on 1993 with total page 217 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Research on Rotating Stall in Axial Flow Compressors by : F. K. Moore
Download or read book Research on Rotating Stall in Axial Flow Compressors written by F. K. Moore and published by . This book was released on 1959 with total page 40 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Effect of Controlled Inlet Distortions on Rotating Stall Inception in a Low Speed Centrifugal Compressor by : Patrick B. Lawless
Download or read book Effect of Controlled Inlet Distortions on Rotating Stall Inception in a Low Speed Centrifugal Compressor written by Patrick B. Lawless and published by . This book was released on 1994 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Basic Studies of Rotating Stall in Axial Flow Compressors by : Gary R. Ludwig
Download or read book Basic Studies of Rotating Stall in Axial Flow Compressors written by Gary R. Ludwig and published by . This book was released on 1979 with total page 266 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the results of a theoretical and experimental program aimed at obtaining a sufficient understanding of the rotating stall phenomena such that its onset and properties can be predicted under a wide set of circumstances. The theoretical research covers the development of two-dimensional stability theories for compressible flows and the progress towards the development of a three-dimensional theory for incompressible flow. The experimental work, performed in an annular cascade facility, studied the effects of rotorstator interference both on the steady-state performance of the blade rows and on rotating stall. The influence of circumferential distortion on the rotating stall boundary for the stage was also determined. Comparisons are made between the experimental results and the predictions of a two-dimensional rotating stall stability theory which had been developed previously for incompressible flows. (Author).
Book Synopsis Compressor Surge and Stall by : R. C. Pampreen
Download or read book Compressor Surge and Stall written by R. C. Pampreen and published by . This book was released on 1993 with total page 532 pages. Available in PDF, EPUB and Kindle. Book excerpt: High efficiency axial and centrifugal compressors are important in fields as diverse as aircraft engines, superchargers and turbochargers, process and refrigeration compressors. Compressors must achieve high efficiency in blade rows in diffusing flow fields. Of equal and sometimes greater importance is the range os stable operation of the compressor. Blade row stall characteristics determine the limit os stable operation. Blading can stall uniformly with symmetric flow breakdown or asymmetrically in rotating stall, wich propagates around the periphery of the blade row. Depending on aerodynamic conditions, surge may occur instead of, in concert with, or subsequent to blade row stall. The transient breakdown and recovery of aerodynamic loading not only limits compressor performance but also leads to mechanical failures caused by the vibrational loads imposed on the blades. There is no need to know what initiates these performance limits so that surge and stall margins can be optimized and control strategies can be planned. the first step toward understanding is to be knowledgeable about he physical processes occurring during surge and stall. This will permit the designer to anticipate variable geometry needs such as variable inlet guide vanes, variable statuors, and bleed port strategies. Theoritical treatment is far from being well established, however, there are many approaches discussed in the literature. This book is a unique reference to the subject matter. Physical descriptions of the phenomena are given, test results are presented, and analytical studies are discussed. There has been much written about the experimental investigations and theoretical treatments related to surge and stall. To assist those who would pursue advancements in furthering ou knowledge of surge and stall, it seemed appropriate to have a resource that contains a compendium of information on this subject. That is the purpose of this book. [Source : d'après la 4e de couverture].