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Performance Improvement Of Centrifugal Compressor Stage With Pinched Geometry Or Vaned Diffuser
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Book Synopsis Performance improvement of centrifugal compressor stage with pinched geometry or vaned diffuser by : Ahti Jaatinen
Download or read book Performance improvement of centrifugal compressor stage with pinched geometry or vaned diffuser written by Ahti Jaatinen and published by . This book was released on 2009 with total page 152 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Centrifugal Compressor Stage by : Thomas Barker Ferguson
Download or read book The Centrifugal Compressor Stage written by Thomas Barker Ferguson and published by . This book was released on 1963 with total page 172 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Influence of Diffuser Vane Leading Edge Geometry on the Performance of a Centrifugal Compressor by : W. W. Clements
Download or read book The Influence of Diffuser Vane Leading Edge Geometry on the Performance of a Centrifugal Compressor written by W. W. Clements and published by . This book was released on 1989 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analytical Correlation of Centrifugal Compressor Design Geometry for Maximum Efficiency with Specific Speed by : Michael R. Galvas
Download or read book Analytical Correlation of Centrifugal Compressor Design Geometry for Maximum Efficiency with Specific Speed written by Michael R. Galvas and published by . This book was released on 1972 with total page 44 pages. Available in PDF, EPUB and Kindle. Book excerpt: Centrifugal compressor performance was examined analytically to determine optimum geometry for various applications as characterized by specific speed. Seven specific losses were calculated for various combinations of inlet tip-exit diameter ratio, inlet hub-tip diameter ratio, blade exit backsweep, and inlet-tip absolute tangential velocity for solid body prewhirl. The losses considered were inlet guide vane loss, blade loading loss, skin friction loss, recirculation loss, disk friction loss, vaneless diffuser loss, and vaned diffuser loss. Maximum total efficiencies ranged from 0.497 to 0.868 for a specific speed range of 0.257 to 1.346. Curves of rotor exit absolute flow angle, inlet tip-exit diameter ratio, inlet hub-tip diameter ratio, head coefficient and blade exit backsweep are presented over a range of specific speeds for various inducer tip speeds to permit rapid selection of optimum compressor size and shape for a variety of applications.
Book Synopsis The Influence of Inlet Flow Distortion on the Performance of a Centrifugal Compressor and the Development of an Improved Inlet Using Numerical Simulations by : Yunbae Kim
Download or read book The Influence of Inlet Flow Distortion on the Performance of a Centrifugal Compressor and the Development of an Improved Inlet Using Numerical Simulations written by Yunbae Kim and published by . This book was released on 2001 with total page 404 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Optimisation of Turbocharger Compressor Diffuser Geometry for Real-World Drive Cycles by : Kristaq Hazizi
Download or read book Aerodynamic Optimisation of Turbocharger Compressor Diffuser Geometry for Real-World Drive Cycles written by Kristaq Hazizi and published by GRIN Verlag. This book was released on 2022-11-02 with total page 446 pages. Available in PDF, EPUB and Kindle. Book excerpt: Doctoral Thesis / Dissertation from the year 2022 in the subject Engineering - Automotive Engineering, grade: 8.0, Anglia Ruskin University (FACULTY OF SCIENCE & ENGINEERING), course: Mechanical Engineering, language: English, abstract: The aim of the dissertation is to develop a new numerical optimisation technique for the diffuser geometry of a typical turbocharger compressor, using a non-parametric optimisation method (adjoint). This leads to an increase in power and thermal efficiency in real-world drive cycles for passenger car engines. The geometry and experimental data correspond to the TD025-05T4 compressor from the 1.2-liter Renault Megane passenger car supplied by MTEE. In this study, a set of numerical simulations were conducted along two turbocharger compressor speed lines at 150,000 rpm and 80,000 rpm to analyse and validate the results against experimental data. Three points on each speed line are selected: one point each in regions close to surge and choke and a point in the stable zone of the compressor map. In addition, this study optimises the diffuser geometry in a passenger vehicle turbocharger compressor using a gradient-based solution approach employing a non-parametrical adjoint shaping optimisation for ideal gas turbulent compressible flow applications. The adjoint solver is a gradient-based optimisation that can automatically generate a series of iterations of a design so that the mesh gradually changes shape to meet a single goal, like the efficiency of the compressor in this case. The study considers a total of six operating cases on the compressor map to optimise the full and partial load compressor operations, leading to a real-world drive cycle. These cases are the three cases (closer to surge, stable midpoint, and closer to the choke point) on each of the speed lines. A typical result for mid-stable operation on a 150,000 (rpm) speed line shows a gradual increase in efficiency up to a maximum of 2.6% improvement. While, for choke and surge optimisation, the geometry variation of the optimised diffuser is different, in the stable central area for both speed lines, the geometry change is consistent. Therefore, the diffuser can be made to work best for both half and full load engine operation. As a result, the optimum diffuser geometry impacts engine efficiency and the overall performance of a typical passenger car for real drive cycles, increasing power and slightly improving thermal efficiency. When a typical car engine is running at full and half-load in real-world operation, the improved compressor efficiency is expected to make a small difference. This will make the engine more powerful and more efficient by about 0.1%.
Book Synopsis Radial Flow Turbocompressors by : Michael Casey
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.
Book Synopsis Effects of Vaned Diffuser Pressure Recovery on Centrifugal Compressor Stage Performance by : Robyn Monique Eason
Download or read book Effects of Vaned Diffuser Pressure Recovery on Centrifugal Compressor Stage Performance written by Robyn Monique Eason and published by . This book was released on 1985 with total page 228 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis The Effect of Exit-vaned Diffusers on Centrifugal-compressor Performance by : Frank Florian Szczesny
Download or read book The Effect of Exit-vaned Diffusers on Centrifugal-compressor Performance written by Frank Florian Szczesny and published by . This book was released on 1962 with total page 226 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Scalloped Leading Edge Vaned Diffuser Analysis for a Compact High Pressure Ratio Centrifugal Compressor by : Vinod Poonamchand Gehlot
Download or read book Scalloped Leading Edge Vaned Diffuser Analysis for a Compact High Pressure Ratio Centrifugal Compressor written by Vinod Poonamchand Gehlot and published by . This book was released on 2015 with total page 192 pages. Available in PDF, EPUB and Kindle. Book excerpt: Microturbines and small gas turbines are often an attractive option for turbo-hybryd application research in aviation due to their simple design and high power to weight ratio. However, the low operating pressure ratios of microturbines leads to low thermal efficiency, which results in very high fuel consumption. Higher operating pressure ratios in microturbines could vastly improve their current fuel efficiency. This thesis focuses on developing a compact, single stage 8:1 pressure ratio centrifugal compressor stage designed to meet the high-pressure ratio requirements of microturbines and small gas turbine engines in turbo hybrid-electric propulsion applications. The first stage vaned diffuser was modified to include a scalloped leading edge ridge to aid stage total-total compression efficiency improvement. A full 3D Navier-Strokes based CDF solver was used in estimating the delta increase in device total-total efficiency due to scalloped leading edge, from the baseline configuration. The solution obtained using CFD was also used to investigate the ameliorating effects of the scallop ridge.
Book Synopsis Design and Analysis of Centrifugal Compressors by : Rene Van den Braembussche
Download or read book Design and Analysis of Centrifugal Compressors written by Rene Van den Braembussche and published by John Wiley & Sons. This book was released on 2019-04-08 with total page 418 pages. Available in PDF, EPUB and Kindle. Book excerpt: A comprehensive overview of fluid dynamic models and experimental results that can help solve problems in centrifugal compressors and modern techniques for a more efficient aerodynamic design. Design and Analysis of Centrifugal Compressors isacomprehensive overview of the theoretical fluid dynamic models describing the flow in centrifugal compressors and the modern techniques for the design of more efficient centrifugal compressors. The author — a noted expert in the field, with over 40 years of experience — evaluates relevant numerical and analytical prediction models for centrifugal compressors with special attention to their accuracy and limitations. Relevant knowledge from the last century is linked with new insights obtained from modern CFD. Emphasis is to link the flow structure, performance and stability to the geometry of the different compressor components. Design and Analysis of Centrifugal Compressors is an accessible resource that combines theory with experimental data and previous research with recent developments in computational design and optimization. This important resource Covers the basic information concerning fluid dynamics that are specific for centrifugal compressors and clarifies the differences with axial compressors Provides an overview of performance prediction models previously developed in combination with extra results from research conducted by the author Describes helpful numerical and analytical models for the flow in the different components in relation to flow stability, operating range and performance Includes the fundamental information for the aerodynamic design of more efficient centrifugal compressors Explains the use of computational fluid dynamics (CFD) for the design and analysis of centrifugal compressors Written for engineers, researchers and designers in industry as well as for academics specializing in the field, Design and Analysis of Centrifugal Compressors offers an up to date overview of the information needed for the design of more effective centrifugal compressors.
Book Synopsis Return Channel Loss Reduction in Multi-stage Centrifugal Compressors by : Anne-Raphaëlle Aubry
Download or read book Return Channel Loss Reduction in Multi-stage Centrifugal Compressors written by Anne-Raphaëlle Aubry and published by . This book was released on 2012 with total page 63 pages. Available in PDF, EPUB and Kindle. Book excerpt: This thesis presents concepts for improving the performance of return channels in multi-stage centrifugal compressors. Geometries have been developed to reduce both separation and viscous losses. A number of different features with potential to reduce separation have also been investigated. The final proposed geometry uses a vaneless diffuser which narrows on the shroud side at the beginning of the 180' bend, an axially extended 1800 bend with increasing radius of curvature, and return channel vane leading edge radial position at an increased radius compared to the baseline. Three-dimensional calculations showed a 9% loss reduction compared to previous work [1], with a cumulative loss reduction of 19% compared to a baseline geometry. The geometry developed was based on specified inlet conditions. To examine the potential for increased performance if this constraint was removed, a return channel geometry was also defined that incorporated the same features but allowed modified inlet conditions, specifically radial inlet flow. The design of the impeller required for this new inlet flow was not considered. An overall loss reduction of 23% compared to baseline was found from the calculations. Modification of the impeller geometry is thus proposed as future work.
Book Synopsis Characterization of Performance-limiting Flow Mechanisms in a Centrifugal Compressor Stage by : David W. Erickson (S.M.)
Download or read book Characterization of Performance-limiting Flow Mechanisms in a Centrifugal Compressor Stage written by David W. Erickson (S.M.) and published by . This book was released on 2017 with total page 270 pages. Available in PDF, EPUB and Kindle. Book excerpt: This research characterizes the performance of a centrifugal compressor stage with a special focus on the pipe diffuser. Two diffuser configurations are studied, one of which is a truncated version of the other. Experimental data acquired on a research compressor stage is interrogated along with a set of well-designed Reynolds-Averaged Navier Stokes computations, complemented by reduced order flow modeling. The fundamental performance-limiting flow mechanisms in the diffuser are identified and used to physically relate important geometry features and operating conditions to the observed compressor pressure rise, efficiency, and operability characteristics. Despite large differences in their geometry, the two diffuser configurations exhibit similar pressure recovery characteristics due to differences in exit nonuniformity and flow angle which result in similar effective area ratios. Variations in the diffuser pressure recovery coefficient with operating point are found to be most influenced by the diffuser inlet flow angle, and secondly by the inlet Mach number. The diffuser inlet flow angle has the primary effect of setting the diffuser inlet one-dimensional area ratio, increasing diffusion at high flow angles. In addition, the diffuser incidence angle influences the formation of counter-rotating vortex pairs that persist throughout the diffuser passage. Using a two-dimensional integral boundary layer model that is modified to accommodate three-dimensional effects as source terms, these secondary flows are shown to detrimentally impact the diffuser pressure rise capability by accumulating high loss flow along the diffuser wall near the plane of symmetry between the vortices. This contributes to the extent and location of a large diffuser passage separation, especially for the baseline diffuser. The impact of the vortices on the boundary layer growth rate is shown to scale inversely with diffuser aspect ratio. The major performance difference between the two diffuser configurations is that the truncated diffuser configuration experiences enhanced stall margin over the baseline diffuser at the design speed. These differences are traced to reduced secondary flows influence and thus reduced separation extent for the higher aspect ratio truncated diffuser. It is hypothesized that the onset of stall for the baseline diffuser configuration is initiated by the transition of the vortex location and corresponding passage separation between diffuser pressure and suction sides with increasing cusp incidence. Conversely, because the extent of the passage separation in the truncated diffuser is diminished due to the higher aspect ratio, the switch in separation side does not immediately initiate instability. The fact that secondary flows have a large influence on diffuser pressure rise capability and compressor stability is counter to conventional preliminary diffuser design approaches which neglect such 3D effects. The findings of this research may therefore be considered during preliminary design optimization to produce better-performing diffuser designs.
Book Synopsis Performance of a Low-pressure-ratio Centrifugal Compressor with Four Diffuser Designs by : Hugh A. Klassen
Download or read book Performance of a Low-pressure-ratio Centrifugal Compressor with Four Diffuser Designs written by Hugh A. Klassen and published by . This book was released on 1973 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Author :National Aeronautics and Space Administration (NASA) Publisher :Createspace Independent Publishing Platform ISBN 13 :9781719380119 Total Pages :36 pages Book Rating :4.3/5 (81 download)
Book Synopsis Axial and Centrifugal Compressor Mean Line Flow Analysis Method by : National Aeronautics and Space Administration (NASA)
Download or read book Axial and Centrifugal Compressor Mean Line Flow Analysis Method written by National Aeronautics and Space Administration (NASA) and published by Createspace Independent Publishing Platform. This book was released on 2018-05-20 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: This paper describes a method to estimate key aerodynamic parameters of single and multistage axial and centrifugal compressors. This mean-line compressor code COMDES provides the capability of sizing single and multistage compressors quickly during the conceptual design process. Based on the compressible fluid flow equations and the Euler equation, the code can estimate rotor inlet and exit blade angles when run in the design mode. The design point rotor efficiency and stator losses are inputs to the code, and are modeled at off design. When run in the off-design analysis mode, it can be used to generate performance maps based on simple models for losses due to rotor incidence and inlet guide vane reset angle. The code can provide an improved understanding of basic aerodynamic parameters such as diffusion factor, loading levels and incidence, when matching multistage compressor blade rows at design and at part-speed operation. Rotor loading levels and relative velocity ratio are correlated to the onset of compressor surge. NASA Stage 37 and the three-stage NASA 74-A axial compressors were analyzed and the results compared to test data. The code has been used to generate the performance map for the NASA 76-B three-stage axial compressor featuring variable geometry. The compressor stages were aerodynamically matched at off-design speeds by adjusting the variable inlet guide vane and variable stator geometry angles to control the rotor diffusion factor and incidence angles. Veres, Joseph P. Glenn Research Center TURBOCOMPRESSORS; FLUID FLOW; COMPUTATIONAL FLUID DYNAMICS; COMPRESSIBLE FLUIDS; DESIGN ANALYSIS; GUIDE VANES; CENTRIFUGAL COMPRESSORS; SURGES; DIFFUSION; ROTORS; STATORS
Book Synopsis Experimental investigation of unsteady flow phenomena in a centrifugal compressor vaned diffuser of variable geometry, ASME 98-GT-368 by : Friedrich Justen
Download or read book Experimental investigation of unsteady flow phenomena in a centrifugal compressor vaned diffuser of variable geometry, ASME 98-GT-368 written by Friedrich Justen and published by . This book was released on 1998 with total page 0 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine & Aeroengine Congress & Exhibition, Stockholm, Sweden, Jun 2-5, 1998.
Book Synopsis Theoretical and Experimental Investigation of the Flow at the Inlet of the Vaned Diffuser by : G. Verdonk
Download or read book Theoretical and Experimental Investigation of the Flow at the Inlet of the Vaned Diffuser written by G. Verdonk and published by . This book was released on 1978 with total page 70 pages. Available in PDF, EPUB and Kindle. Book excerpt:
