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Analysis Of Stage Matching And Off Design Performance Of Multistage Axial Flow Compressors
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Book Synopsis Analysis of Stage Matching and Off-design Performance of Multistage Axial-flow Compressors by : Harold B. Finger
Download or read book Analysis of Stage Matching and Off-design Performance of Multistage Axial-flow Compressors written by Harold B. Finger and published by . This book was released on 1952 with total page 38 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of the Effects of Design Pressure Ratio Per Stage and Off-design Efficiency on the Operating Range of Multistage Axial-flow Compressors by : Melvyn Savage
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.
Book Synopsis Method for Predicting Off-design Performance of Axial-flow Compressor Blade Rows by : George K. Serovy
Download or read book Method for Predicting Off-design Performance of Axial-flow Compressor Blade Rows written by George K. Serovy and published by . This book was released on 1959 with total page 42 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Design of Axial-flow Compressors by : Lewis Research Center
Download or read book Aerodynamic Design of Axial-flow Compressors written by Lewis Research Center and published by . This book was released on 1965 with total page 542 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Analysis of Off-design Performance of a 16-stage Axial-flow Compressor with Various Blade Modifications by : Arthur A. Medeiros
Download or read book Analysis of Off-design Performance of a 16-stage Axial-flow Compressor with Various Blade Modifications written by Arthur A. Medeiros and published by . This book was released on 1953 with total page 57 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Download or read book NASA Technical Note written by and published by . This book was released on 1971 with total page 528 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Aerodynamic Design of Axial Flow Compressors by : Robert O. Bullock
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:
Book Synopsis Optimizing the Efficiency of a Multi-Stage Axial-Flow Compressor by : Shawn A. Miller
Download or read book Optimizing the Efficiency of a Multi-Stage Axial-Flow Compressor written by Shawn A. Miller and published by . This book was released on 1998-03-01 with total page 94 pages. Available in PDF, EPUB and Kindle. Book excerpt: The development of jet engines has become an integral part of maintaining air superiority. In order to achieve the most advanced engine, research has turned to traditional optimization methods to aid in creating new engine designs. To develop simplified mathematical models representative of the engine, the engine can be separated into its components. A jet engine has three major elements, the compressor, combustion chamber and turbine. This research attempts to make an initial analysis of a two stage compressor to determine values of blade angles and spacing to chord ratios for both stages that produce the highest possible efficiency for the overall two stage compressor. A pitch line model is developed for a two stage compressor and is used in conjunction with a optimization method to solve for the on design air angles and spacing to chord ratios. The results of the model were compared to examples available in current literature to ensure the model properly represents a compressor stage. The off design performance of the results was calculated to determine how the designs for on design operated under off design conditions. Since practical compressors are made up of many stages, consideration is given to which optimization method would be most useful in solving for a multistage compressor.
Book Synopsis Axial and Centrifugal Compressor Mean Line Flow Analysis Method by : Nasa Technical Reports Server (Ntrs)
Download or read book Axial and Centrifugal Compressor Mean Line Flow Analysis Method written by Nasa Technical Reports Server (Ntrs) and published by BiblioGov. This book was released on 2013-07 with total page 40 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.
Download or read book NACA Research Memorandum written by and published by . This book was released on 1958 with total page 338 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Computational Analysis of a Multistage Axial Compressor by : Chaithanya Mamidoju
Download or read book Computational Analysis of a Multistage Axial Compressor written by Chaithanya Mamidoju and published by . This book was released on 2014 with total page 41 pages. Available in PDF, EPUB and Kindle. Book excerpt: Turbomachines are used extensively in Aerospace, Power Generation, and Oil & Gas Industries. Efficiency of these machines is often an important factor and has led to the continuous effort to improve the design to achieve better efficiency. The axial flow compressor is a major component in a gas turbine with the turbine's overall performance depending strongly on compressor performance. Traditional analysis of axial compressors involves through flow calculations, isolated blade passage analysis, Quasi-3D blade-to-blade analysis, single-stage (rotor-stator) analysis, and multi-stage analysis involving larger design cycles. In the current study, the detailed flow through a 15 stage axial compressor is analyzed using a 3-D Navier Stokes CFD solver in a parallel computing environment. Methodology is described for steady state (frozen rotor stator) analysis of one blade passage per component. Various effects such as mesh type and density, boundary conditions, tip clearance and numerical issues such as turbulence model choice, advection model choice, and parallel processing performance are analyzed. A high sensitivity of the predictions to the above was found. Physical explanation to the flow features observed in the computational study are given. The total pressure rise verses mass flow rate was computed.
Book Synopsis Scientific and Technical Aerospace Reports by :
Download or read book Scientific and Technical Aerospace Reports written by and published by . This book was released on 1990 with total page 466 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 National Bureau of Standards Circular by :
Download or read book National Bureau of Standards Circular written by and published by . This book was released on 1954 with total page 122 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Non-uniform Radial Meanline Method for Off-design Performance Estimation of Multistage Axial Compressors by : David Andrew Birkenheier
Download or read book Non-uniform Radial Meanline Method for Off-design Performance Estimation of Multistage Axial Compressors written by David Andrew Birkenheier and published by . This book was released on 2018 with total page 131 pages. Available in PDF, EPUB and Kindle. Book excerpt: The increasing use of renewable energy sources necessitates power-generating gas turbines capable of frequently and rapidly starting up to supplement the energy supply when renewable sources alone cannot meet demand [1], [21. This makes the off-design performance of such gas turbines more important as they spend more of their operational life off the design point. Currently off-design performance cannot be estimated with high fidelity until late in the gas turbine compressor design process at which point the design is largely fixed and only limited changes can be made. This thesis presents a Non-Uniform Radial Meanline method for multistage axial compressor off-design performance estimation, capturing the transfer of radial flow non-uniformity and its impact on compressor blade row performance. This method enables the high-fidelity characterization of blade row performance and the stage matching of multistage compressors with non-uniformity effects included. A new representation of non-uniform radial flow profiles using orthonormal basis functions was developed to provide a compact representation suitable for inclusion in a one-dimensional performance estimation method. The link between radial flow non-uniformity and compressor blade row performance was characterized using three-dimensional embedded stage calculations. An initial implementation of the Non-Uniform Radial Meanline method was demonstrated for different compressor inlet non-uniformities. The computations show that the new approach provides an effective means of incorporating radial flow non-uniformity into a one-dimensional compressor performance estimation method.
Book Synopsis Encyclopedia of Chemical Processing and Design by : John J. McKetta Jr
Download or read book Encyclopedia of Chemical Processing and Design written by John J. McKetta Jr and published by CRC Press. This book was released on 1997-05-05 with total page 590 pages. Available in PDF, EPUB and Kindle. Book excerpt: Trays versus Packings in Separator Design to Underground Gas Storage
Book Synopsis Aerothermodynamics of Aircraft Engine Components by : Gordon C. Oates
Download or read book Aerothermodynamics of Aircraft Engine Components written by Gordon C. Oates and published by AIAA. This book was released on 1985 with total page 568 pages. Available in PDF, EPUB and Kindle. Book excerpt: Annotation Design and R & D engineers and students will value the comprehensive, meticulous coverage in this volume. Beginning with the basic principles and concepts of aeropropulsion combustion, chapters explore specific processes, limitations, and analytical methods as they bear on component design.
