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Advancement Of Small Gas Turbine Component Technology Advanced Small Axial Compressor Volume Ii Addendum Aerodynamic Redesign
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Book Synopsis Advancement of Small Gas Turbine Component Technology, Advanced Small Axial Compressor. Volume II. Addendum. Aerodynamic Redesign by : James V. Davis
Download or read book Advancement of Small Gas Turbine Component Technology, Advanced Small Axial Compressor. Volume II. Addendum. Aerodynamic Redesign written by James V. Davis and published by . This book was released on 1970 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: This report presents the redesign analysis of the axial compressor program for the advancement of small gas turbine component technology. A two-stage axial compressor was redesigned using test data from the previous two stage tests together with an analysis of a family of high-pressure-ratio compressor rotors. The major changes made to the original design were reduced solidity in both rotors, increased first-stage rotor aspect ratio, and modified first-stage rotor blade profile.
Book Synopsis Advancement of Small Gas Turbine Component Technology, Advanced Small Axial Compressor. Volume I. Analysis and Design. Addendum by : James V. Davis
Download or read book Advancement of Small Gas Turbine Component Technology, Advanced Small Axial Compressor. Volume I. Analysis and Design. Addendum written by James V. Davis and published by . This book was released on 1969 with total page 36 pages. Available in PDF, EPUB and Kindle. Book excerpt: A complete two-stage aerodynamic axial compressor design capable of being matched with the USAAVLABS advanced centrifugal technology was prepared. Fully variable part span inlet guide vanes were designed. Two transition ducts were also designed to provide an efficient aerodynamic flow path from the axial compressor exit to the centrifugal compressor inlet. (Author).
Book Synopsis Advancement of Small Gas Turbine Component Technology Advanced Small Axial Compressor. Volume II. Test and Redesign by : James V. Davis
Download or read book Advancement of Small Gas Turbine Component Technology Advanced Small Axial Compressor. Volume II. Test and Redesign written by James V. Davis and published by . This book was released on 1970 with total page 173 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents the redesign analysis of a two-stage axial compressor program for the advancement of small gas turbine component technology. The discussion covers fabrication, test, and redesign of the axial compressor which was presented in Volume I. (Author).
Book Synopsis Advancement of Small Gas Turbine Component Technology by : James V. Davis
Download or read book Advancement of Small Gas Turbine Component Technology written by James V. Davis and published by . This book was released on 1970* with total page 14 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report presents the redesign analysis of a two-stage axial compressor program for the advancement of small gas turbine component technology. The discussion covers fabrication, test, and redesign of the axial compressor which was presented in Volume I. (Author).
Book Synopsis Advancement of Small Gas Turbine Component Technology, Advanced Small Axial Compressor. Volume I. Analysis and Design by : James V. Davis
Download or read book Advancement of Small Gas Turbine Component Technology, Advanced Small Axial Compressor. Volume I. Analysis and Design written by James V. Davis and published by . This book was released on 1969 with total page 176 pages. Available in PDF, EPUB and Kindle. Book excerpt: A cursory design study of the gas generator involving the preliminary design and analysis of a family of axial compressors was conducted. Each axial compressor was designed to be capable of match with advanced centrifugal technology. The minimum overall axial-centrifugal design pressure ratio for each compressor configuration was 16:1. The engine performance using the characteristics of the compressor designs was evaluated and an optimum gas generator configuration was selected. The axial compressor for the optimum gas generator configuration was detail designed for test rig evaluation. This axial compressor has two stages and a 3.0:1 design pressure ratio. The design flow rate is 5.0 pound-per-second and the inlet tip radius is 2.72 inches. (Author).
Book Synopsis Single-Stage Axial Compressor Component Development for Small Gas Turbine Engines. Volume II. Rotor Development by : Charles H. Muller
Download or read book Single-Stage Axial Compressor Component Development for Small Gas Turbine Engines. Volume II. Rotor Development written by Charles H. Muller and published by . This book was released on 1969 with total page 116 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes the development of the rotor for the 2.8:1 single stage supersonic axial compressor design. The rotor performance was evaluated through experimental testing with the inlet guide vanes but without the exit stator. The experimental results are analyzed and compared to the design data and criteria. Although a circumferential flow distortion at the rotor exit prevented a very accurate assessment of the performance potential, the data provided ample evidence that the rotor performance goals could be met with uniform exit conditions. The presence of the exit stator during the stage development tests in the subsequent phase was expected to reduce the flow distortion at the rotor exit to near uniform conditions. (Author).
Book Synopsis Single-Stage Axial Compressor Component Development for Small Gas Turbine Engines. Volume I. Design by : Charles H. Muller
Download or read book Single-Stage Axial Compressor Component Development for Small Gas Turbine Engines. Volume I. Design written by Charles H. Muller and published by . This book was released on 1969 with total page 168 pages. Available in PDF, EPUB and Kindle. Book excerpt: The design of a single stage axial supersonic compressor with a predicted performance of 2.8:1 stage pressure ratio at 82% adiabatic efficiency and 4 lb/sec airflow is discussed. The results of a gas generator performance study to evaluate non-regenerated designs with 16:1 pressure ratio compressors and turbine inlet temperatures between 2500 F and 3000 F are presented and discussed. The design point specific fuel consumption of the engines studied ranged from 0.415 to 0.438 lb/hp/hr. At 50% power this range increased to 0.465 and 0.534 respectively. The engine configuration which indicated the lowest specific fuel consumption has a two spool gas generator and variable stator free power turbine. The preliminary designs of a two stage axial/centrifugal compressor and an advanced gas generator which incorporates this compressor are discussed. The predicted performance of the compressor is 16:1 pressure ratio at an adiabatic efficiency of 77.5% and an airflow of 4 lb/sec. The predicted design point specific fuel consumption and power at a 2500 F turbine inlet temperature are 0.431 lb/hp/hr and 785 hp respectively. The results of a preliminary design study for a variable geometry axial compressor rotor concept are also discussed. This concept offers the potential for improved part speed compressor performance and stage matching. (Author).
Book Synopsis Cold-air Performance of Compressor-drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine. 1: Volute-manifold and Stator Performance by :
Download or read book Cold-air Performance of Compressor-drive Turbine of Department of Energy Upgraded Automobile Gas Turbine Engine. 1: Volute-manifold and Stator Performance written by and published by . This book was released on 1981 with total page 24 pages. Available in PDF, EPUB and Kindle. Book excerpt: The aerodynamic performance of the inlet manifold and stator assembly of the compressor-drive turbine was experimentally determined with cold air as the working fluid. The investigation included measurements of mass flow and stator-exit fluid torque as well as radial surveys of total pressure and flow angle at the stator inlet and annulus surveys of total pressure and flow angle at the stator exit. The stator-exit aftermixed flow conditions and overall stator efficiency were obtained and compared with their design values and the experimental results from three other stators. In addition, an analysis was made to determine the constituent aerodynamic losses that made up the stator kinetic energy loss. (Author).
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 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 Dynamic Modeling of Starting Aerodynamics and Stage Matching in an Axi-Centrifugal Compressor by : Kevin Wilkes
Download or read book Dynamic Modeling of Starting Aerodynamics and Stage Matching in an Axi-Centrifugal Compressor written by Kevin Wilkes and published by . This book was released on 1996 with total page 12 pages. Available in PDF, EPUB and Kindle. Book excerpt: Presented at the International Gas Turbine and Aeroengine Congress & Exhibition Birmingham, UK - June 10-13, 1996.
Book Synopsis Single-stage Axial Compressor Component Development for Small Gas Turbines by : Charles H. Muller
Download or read book Single-stage Axial Compressor Component Development for Small Gas Turbines written by Charles H. Muller and published by . This book was released on 1969* with total page 110 pages. Available in PDF, EPUB and Kindle. Book excerpt: The report describes the development of the complete stage for the 2.8:1 supersonic axial compressor design. The performance of the overall stage including the exit stators and interconnecting duct was evaluated through experimental testing with the rotor and inlet guide vanes developed under the previous phase of this program. The experimental results are analyzed and compared with the design data and criteria for each of the blade rows as well as the overall stage. (Author).
Book Synopsis Axial-flow Compressors by : Ronald H. Aungier
Download or read book Axial-flow Compressors written by Ronald H. Aungier and published by American Society of Mechanical Engineers. This book was released on 2003 with total page 386 pages. Available in PDF, EPUB and Kindle. Book excerpt: This book provides a thorough description of an aerodynamic design and analysis systems for Axial-Flow Compressors. It describes the basic fluid dynamic and thermodynamic principles, empirical models and numerical methods used for the full range of procedures and analytical tools that an engineer needs for virtually any tupe of Axial-Flow Compressor, aerodynamic design or analysis activity. It reviews and evaluates several design strategies that have been recommended in the literature or which have been found to be effective. It gives a complete description of an actual working system, such that readers can implement all or part of the system. Engineers responsible for developing, maintaining of improving design and analysis systems can benefit greatly from this type of reference. The technology has become so complex and the role of computers so pervasive that about the only way this can be done today is to concentrate on a specific design and analysis system. The author provides practical methodology as well as the details needed to implement the suggested procedures.
Book Synopsis Advanced Industrial Gas Turbine Technology Readiness Demonstration Program. Phase II. Final Report by :
Download or read book Advanced Industrial Gas Turbine Technology Readiness Demonstration Program. Phase II. Final Report written by and published by . This book was released on 1981 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt: The results of a component technology demonstration program to fabricate, assemble and test an advanced axial/centrifugal compressor are presented. This work was conducted to demonstrate the utilization of advanced aircraft gas turbine cooling and high pressure compressor technology to improve the performance and reliability of future industrial gas turbines. Specific objectives of the compressor component testing were to demonstrate 18:1 pressure ratio on a single spool at 90% polytropic efficiency with 80% fewer airfoils as compared to current industrial gas turbine compressors. The compressor design configuration utilizes low aspect ratio/highly-loaded axial compressor blading combined with a centrifugal backend stage to achieve the 18:1 design pressure ratio in only 7 stages and 281 axial compressor airfoils. Initial testing of the compressor test rig was conducted with a vaneless centrifugal stage diffuser to allow documentation of the axial compressor performance. Peak design speed axial compressor performance demonstrated was 91.8% polytropic efficiency at 6.5:1 pressure ratio. Subsequent documentation of the combined axial/centrifugal performance with a centrifugal stage pipe diffuser resulted in the demonstration of 91.5% polytropic efficiency and 14% stall margin at the 18:1 overall compressor design pressure ratio. The demonstrated performance not only exceeded the contract performance goals, but also represents the highest known demonstrated compressor performance in this pressure ratio and flow class. The performance demonstrated is particularly significant in that it was accomplished at airfoil loading levels approximately 15% higher than that of current production engine compressor designs. The test results provide conclusive verification of the advanced low aspect ratio axial compressor and centrifugal stage technologies utilized.
Book Synopsis Small Gas Turbine Engine Component Technology by : W. Franklin
Download or read book Small Gas Turbine Engine Component Technology written by W. Franklin and published by . This book was released on 1968 with total page pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis A Comparison of Typical National Gas Turbine Establishment and NACA Axial-flow Compressor Blade Sections in Cascade at Low Speed by : A. Richard Felix
Download or read book A Comparison of Typical National Gas Turbine Establishment and NACA Axial-flow Compressor Blade Sections in Cascade at Low Speed written by A. Richard Felix and published by . This book was released on 1953 with total page 50 pages. Available in PDF, EPUB and Kindle. Book excerpt:
Book Synopsis Calculations of the Performance of a Compression-ignition Engine-compressor Turbine Combination by : J. C. Sanders
Download or read book Calculations of the Performance of a Compression-ignition Engine-compressor Turbine Combination written by J. C. Sanders and published by . This book was released on 1945 with total page 28 pages. Available in PDF, EPUB and Kindle. Book excerpt: Small high-speed single-cylinder compression-ignition engines were tested to determine their performance characteristics under high supercharging. Calculations were made on the energy available in the exhaust gas of the compression-ignition engines. The maximum power at any given maximum cylinder pressure was obtained when the compression pressure was equal to the maximum cylinder pressure. Constant-pressure combustion was found possible at an engine speed of 2200 rpm. Exhaust pressures and temperatures were determined from an analysis of indicator cards. The analysis showed that, at rich mixtures with the exhaust back pressure equal to the inlet-air pressure, there is excess energy available for driving a turbine over that required for supercharging. The presence of this excess energy indicates that a highly supercharged compression-ignition engine might be desirable as a compressor and combustion chamber for a turbine.
